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Calculators Created by Shikha Maurya

Shikha Maurya
Indian Institute of Technology (IIT), Bombay
https://www.linkedin.com/in/shikha-maurya-eager-to-learn/
108
Formulas Created
176
Formulas Verified
48
Across Categories

List of Calculators by Shikha Maurya

Following is a combined list of all the calculators that have been created and verified by Shikha Maurya. Shikha Maurya has created 108 and verified 176 calculators across 48 different categories till date.
Aerodynamic Nomenclature (9)
Verified Aerodynamic axial force
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Verified Aerodynamic normal force
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Verified Aerodynamic side force
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Verified Angle of attack
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Verified Axial force coefficient
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Verified Pitching moment
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Verified Pitching moment coefficient
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Verified Side force coefficient
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Verified Sideslip angle
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9 More Aerodynamic Nomenclature Calculators
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Altitude Effects on Power Required and Available (3)
Verified Power required at sea-level condition
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Verified Velocity at an altitude for given velocity at sea-level condition
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Verified Velocity at sea-level condition
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3 More Altitude Effects on Power Required and Available Calculators
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Basic Compressible Flow (3)
Created Critical Density
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Created Critical Pressure
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Created Critical Temperature
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3 More Basic Compressible Flow Calculators
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Basics (1)
Created Isentropic compressibility for given density and speed of sound
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6 More Basics Calculators
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Bending Stresses (1)
Verified Section Modulus of Steel Beam when Stress in Steel for Unshored Members is Given
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8 More Bending Stresses Calculators
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Blast-wave part 2 (3)
Verified Pressure coefficient combined with blast wave for the shuttle
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Verified Pressure coefficient combined with blast wave for the shuttle at angle of attack
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Verified Pressure coefficient for Blunt-nosed cylinder:
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3 More Blast-wave part 2 Calculators
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Bodies connected by a string - one hanging free, other lying on a rough horizontal plane (1)
Verified Acceleration of the system
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1 More Bodies connected by a string - one hanging free, other lying on a rough horizontal plane Calculators
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Bodies connected by a string - one hanging free, other lying on a smooth horizontal plane (2)
Verified Acceleration in the system
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Verified Tension in the string
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Bodies connected by a string and passing over a smooth pulley (3)
Verified Acceleration of the bodies
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Verified Mass of body B (smaller mass)
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Verified Tension in the string
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Boundary layer flow (5)
Verified Coefficient of drag for Reynold number in the laminar boundary layer flow
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Verified Drag force on the plate in boundary layer flow
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Verified Reynold number for drag force on the plate in boundary layer flow
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Verified Viscosity of liquid for drag force on the plate in boundary layer flow
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Verified Width of the plate for drag force on the plate in boundary layer flow
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16 More Boundary layer flow Calculators
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Boundary-Layer Equations for Hypersonic Flow: Self-Similar Solutions (5)
Verified Adiabatic wall enthalpy using Stanton number
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Verified Enthalpy of wall using Stanton number
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Verified Nusselt number for hypersonic vehicle
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Verified Reynolds number for given Nusselt's number, Stanton number and Prandtl number
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Verified Skin friction coefficient for incompressible flow
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15 More Boundary-Layer Equations for Hypersonic Flow: Self-Similar Solutions Calculators
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Compressible flow (3)
Verified Mach angle for the compressible fluid flow
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Verified Velocity of fluid considering the Mach angle in the compressible fluid flow
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Verified Velocity of sound wave considering Mach angle in the compressible fluid flow
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21 More Compressible flow Calculators
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Contribution of Aircraft Components (Part 1) (6)
Verified Moment produced by vertical tail for given lift curve slope
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Verified Moment produced by vertical tail for given side force
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Verified Sideslip angle for given moment produced by vertical tail
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Verified Vertical tail angle of attack
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Verified Vertical tail moment arm for given side force
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Verified Vertical tail side force for given moment
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9 More Contribution of Aircraft Components (Part 1) Calculators
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Contribution of Aircraft Components (Part 2) (3)
Verified Moment produced by vertical tail for given moment coefficient
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Verified Vertical tail area for given moment
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Verified Yawing moment coefficient
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11 More Contribution of Aircraft Components (Part 2) Calculators
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Contribution of Aircraft Components (Part 3) (6)
Verified Vertical tail area for given vertical tail volume ratio
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Verified Vertical tail moment arm for given vertical tail volume ratio
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Verified Vertical tail volume ratio
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Verified Wing area for given vertical tail volume ratio
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Verified Wing area for given yawing moment coefficient
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Verified Wingspan for given vertical tail volume ratio
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9 More Contribution of Aircraft Components (Part 3) Calculators
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Dynamics of fluid flow (2)
Verified Coefficient of pitot-tube for velocity at any point
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Verified Resultant force on bend for force along x and y-direction
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4 More Dynamics of fluid flow Calculators
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Elevator Hinge Moment (1)
Verified Elevator chord length for given hinge moment coefficient
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4 More Elevator Hinge Moment Calculators
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Flat-Plate for Viscous flow case (1)
Verified Total enthalpy in the inviscid flow outside the boundary layer
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14 More Flat-Plate for Viscous flow case Calculators
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Flight Envelope (5)
Verified Lift Coefficient for a given turn rate
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Verified Load factor for a given turn rate for a high-performance fighter aircraft
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Verified Radius of turn for a given lift coefficient
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Verified Radius of turn for a given wing loading
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Verified Turn rate for a given wing loading
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10 More Flight Envelope Calculators
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Flow through pipes (14)
Verified Area of the nozzle at outlet for maximum power transmission through nozzle
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Verified Area of the pipe for maximum power transmission through nozzle
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Verified Diameter of nozzle for maximum power transmission through nozzle
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Verified Diameter of the equivalent pipe
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Verified Discharge in the equivalent pipe
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Verified Efficiency of power transmission through nozzle for velocity and total head
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Verified Efficiency of power transmission through the nozzle
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Verified Length of pipe for maximum power transmission through nozzle
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Verified Length of the equivalent pipe
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Verified Loss of head at the entrance of a pipe
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Verified Loss of head in the equivalent pipe
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Verified Velocity of flow at the outlet of the nozzle
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Verified Velocity of flow at the outlet of the nozzle for efficiency and head
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Verified Velocity of fluid in pipe for head loss at the entrance of a pipe
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25 More Flow through pipes Calculators
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Forces on sub-merged bodies (9)
Verified Angle of attack for circulation developed on the airfoil
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Verified Area of the body for lift force in a body moving on a fluid
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Verified Chord length for circulation developed on the airfoil
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Verified Circulation developed on the airfoil
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Verified lift coefficient for lift force in a body moving on a fluid
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Verified Lift force for a body moving in a fluid of certain density
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Verified Pressure drag from total drag force on a sphere
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Verified Skin friction drag from total drag force on a sphere
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Verified Velocity of airfoil for circulation developed on the airfoil
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22 More Forces on sub-merged bodies Calculators
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Fundamentals of Inviscid Incompressible flow (47)
Created 2-D Lift coefficient for cylinder
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Created Airspeed measurement by Pitot tube for low-speed incompressible flow
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Created Airspeed measurement by venturi
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Created Circulation by Kutta-Joukowski theorem
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Created Dynamic pressure in incompressible flow
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Created Freestream density by Kutta-Joukowski theorem
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Created Freestream velocity by Kutta-Joukowski theorem
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Created Height difference of manometric fluid for given pressure difference
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Created Lift per unit span by Kutta-Joukowski theorem
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Created Location of stagnation point outside the cylinder for lifting flow
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Created Pressure at a downstream point on streamline by Bernoulli's equation
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Created Pressure at an upstream point on streamline by Bernoulli's equation
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Created Pressure Coefficient
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Created Pressure coefficient in terms of velocity ratio for inncompressible flow
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Created Pressure difference in the low-speed wind tunnel for given test section velocity
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Created Pressure difference measured by manometer in the low-speed wind tunnel
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Created Radial velocity for 2-D incompressible source flow
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Created Radial velocity for lifting flow over circular cylinder
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Created Radial velocity for non-lifting flow over circular cylinder
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Created Radius of cylinder for non-lifting flow
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Created Source Strength for 2-D incompressible source flow
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Created Stagnation streamline equation for flow over semi-infinite body
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Created Static pressure in incompressible flow
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Created Stream function for 2-D Doublet flow
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Created Stream function for 2-D incompressible source flow
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Created Stream function for 2-D Vortex flow
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Created Stream function for flow over Rankine oval
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Created Stream function for lifting flow over a circular cylinder
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Created Stream function for non-lifting flow over a circular cylinder
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Created Stream function for semi-infinite body
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Created Stream function for uniform incompressible flow
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Created Stream function for uniform incompressible flow in polar coordinates
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Created Surface pressure coefficient for lifting flow over circular cylinder
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Created Surface pressure coefficient for non-lifting flow over circular cylinder
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Created Surface pressure on the body in terms of Pressure coefficient
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Created Tangential velocity for 2-D Vortex flow
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Created Tangential velocity for lifting flow over circular cylinder
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Created Tangential velocity for non-lifting flow over circular cylinder
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Created Test section velocity for low sped wind tunnel in terms of height difference of manometric fluid
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Created Test section velocity in low-speed wind tunnel
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Created Total pressure in incompressible flow
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Created Velocity at a point on airfoil for given pressure coefficient and free-stream velocity
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Created Velocity potential for 2-D doublet flow
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Created Velocity potential for 2-D source flow
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Created Velocity potential for 2-D Vortex flow
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Created Velocity potential for uniform incompressible flow
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Created Velocity potential for uniform incompressible flow in polar coordinates
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Hypersonic Equivalence Principle and Blast-Wave Theory (3)
Verified Modified pressure equation for cylindrical blast wave
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Verified Pressure ratio for blunt cylinder blast wave
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Verified Pressure ratio for blunt slab blast wave
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13 More Hypersonic Equivalence Principle and Blast-Wave Theory Calculators
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Hypersonic Flight Paths: Velocity-Altitude Map (1)
Verified Blunt-nosed radial coordinate flat plate (first approximation):
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8 More Hypersonic Flight Paths: Velocity-Altitude Map Calculators
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Hypersonic Inviscid Flowfields: Exact Methods (7)
Verified Density before shock formation for compression wave
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Verified Local shock velocity equation
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Verified Mach wave behind the shock
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Verified Mach wave behind the shock with mach infinity
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Verified New pressure after the shock formation, subtracted to velocity for expansion wave
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Verified Pressure ratio for unsteady waves with subtracted induced mass motion for expansion waves
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Verified Temperature ratio for unsteady compression waves
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11 More Hypersonic Inviscid Flowfields: Exact Methods Calculators
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Ideal flow or Potential flow (1)
Verified Distance of stagnation point S from source in flow past a half body
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14 More Ideal flow or Potential flow Calculators
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Incompressible flow over airfoil (8)
Created Boundary layer thickness for laminar flow
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Created Boundary layer thickness for Turbulent flow
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Created Center of pressure location for cambered airfoil
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Created Lift coefficient for cambered airfoil
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Created Lift coefficient for symmetrical airfoil by Thin airfoil theory
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Created Moment coefficient about leading-edge for symmetrical airfoil by thin airfoil theory
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Created Skin friction drag coefficient for flat plate in laminar flow
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Created Skin friction drag coefficient for flat plate in Turbulent flow
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Landing Performance (1)
Verified Stall velocity for given touchdown velocity
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4 More Landing Performance Calculators
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Maneuvering Flight (1)
Verified Velocity for a given pull-down maneuver radius
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11 More Maneuvering Flight Calculators
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Merchant Force Circle (Mechanics of Orthogonal metal cutting) (12)
Created Cutting force for given force along shear force, shear,friction & normal rake angles
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Created Cutting force for given resultant force in merchant circle, friction angle and normal rake angle
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Created Cutting force for shear stress,width of cut,uncut chip thickness,friction,normal rake & shear angles
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Created Force along shear force for given R of merchant circle, shear, friction and normal rake angles
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Created Friction angle for given R of merchant circle, force along shear force,shear & normal rake angles
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Created Normal rake angle for given Resultant force, force along shear force, shear & friction angles
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Created R in merchant circle for given force along the shear force, shear, friction & normal rake angles
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Created Resultant force in merchant circle for given cutting force, friction and normal rake angles
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Created Shear angle for given Resultant force ,force along shear force,friction & normal rake angles
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Created Shear stress for cutting force,width of cut,uncut chip thickness,friction,normal rake & shear angles
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Created Uncut chip thickness for cutting force,shear stress,width of cut,friction,normal rake & shear angles
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Created Width of cut for cutting force,shear stress,uncut chip thickness,friction,normal rake & shear angles
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26 More Merchant Force Circle (Mechanics of Orthogonal metal cutting) Calculators
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Normal Shock Waves (21)
Created Critical speed of sound from Prandtl relation
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Created Density ahead of normal shock using normal shock momentum equation
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Created Density behind normal shock for given upstream density and Mach number
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Created Density behind normal shock using normal shock momentum equation
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Created Density ratio across a normal shock
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Created Enthalpy ahead of normal shock from normal shock energy equation
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Created Enthalpy behind of normal shock from normal shock energy equation
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Created Pressure ratio across a normal shock
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Created Stagnation pressure behind normal shock by Rayleigh Pitot tube formula
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Created Static enthalpy behind normal shock for given upstream enthalpy and Mach number
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Created Static enthalpy ratio across a normal shock
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Created Static Pressure ahead of normal shock using normal shock momentum equation
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Created Static pressure behind normal shock for given upstream pressure and Mach number
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Created Static Pressure behind of normal shock using normal shock momentum equation
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Created Static temperature behind normal shock for given upstream temperature and Mach number
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Created Temperature ratio across a normal shock
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Created Velocity ahead of normal shock by normal shock momentum equation
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Created Velocity ahead of normal shock from normal shock energy equation
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Created Velocity behind of normal shock by normal shock momentum equation
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Created Velocity behind of normal shock from normal shock energy equation
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Created Velocity upstream of shock using Prandtl relation
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8 More Normal Shock Waves Calculators
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Notches and Weirs (8)
Verified Discharge over rectangle weir considering Bazin's formula
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Verified Discharge over rectangle weir considering Francis's formula
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Verified Discharge with velocity of approach
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Verified Discharge without velocity of approach
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Verified Length of weir considering Bazin's formula without velocity approach
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Verified Length of weir considering Francis's formula
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Verified Length of weir or notch for velocity of approach
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Verified Length of weir or notch without velocity of approach
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19 More Notches and Weirs Calculators
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Number of Connectors in Bridges (5)
Verified Effective Concrete Area when Force in Slab is Given
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Verified Force in Slab at Maximum Positive Moments when Minimum Number of Connectors for Bridges is Given
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Verified Force in Slab when Effective Concrete Area is Given
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Verified Minimum Number of Connectors for Bridges
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Verified Steel Yield Strength when Total Area of Steel Section is Given
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13 More Number of Connectors in Bridges Calculators
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Oblique Shock and Expansion Waves (16)
Created Component of downstream Mach no. normal to oblique shock for given normal upstream Mach no.
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Created Density behind oblique shock for given upstream density & normal upstream Mach no.
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Created Density ratio across the oblique shock
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Created Flow deflection angle in terms of Prandtl Meyer function
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Created Forward Mach angle of expansion fan
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Created Prandtl Meyer function
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Created Prandtl Meyer function at upstream Mach no.
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Created Pressure behind expansion fan
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Created Pressure behind oblique shock for given upstream pressure & normal upstream Mach no
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Created Pressure ratio across the expansion fan
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Created Pressure ratio across the oblique shock
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Created Rearward Mach angle of the expansion fan
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Created Temperature behind expansion fan
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Created Temperature behind oblique shock for given upstream temperature & normal upstream Mach no.
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Created Temperature ratio across the expansion fan
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Created Temperature ratio across the oblique shock
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3 More Oblique Shock and Expansion Waves Calculators
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Rate of Climb (2)
Verified Excess power
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Verified Total Drag for given excess power
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8 More Rate of Climb Calculators
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Reference Temperature Method (1)
Verified Overall skin-friction drag coefficient
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15 More Reference Temperature Method Calculators
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Relationship between Stick Force and Hinge Moment (5)
Verified Elevator deflection angle for given stick force
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Verified Elevator Stick Force
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Verified Elevator stick force for given hinge moment coefficient
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Verified Gearing ratio for given stick force
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Verified Stick deflection angle for given gearing ratio
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13 More Relationship between Stick Force and Hinge Moment Calculators
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Shear Range (1)
Verified Horizontal Shear Range at the juncture of Slab and Beam
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11 More Shear Range Calculators
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Space-Marching Finite Difference Method: Additional Solutions of the Euler Equations (3)
Verified Enthalpy equation using coefficient of pressure for calorically perfect gas
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Verified Free stream enthalpy
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Verified Total enthalpy
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8 More Space-Marching Finite Difference Method: Additional Solutions of the Euler Equations Calculators
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Tail Contribution (5)
Verified Angle of attack at the tail
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Verified Downwash angle
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Verified Pitching moment due to tail
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Verified Tail Pitching moment for given moment coefficient
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Verified Total Lift Coefficient of wing-tail combination
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16 More Tail Contribution Calculators
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Tail Contribution (Contd.) (5)
Verified Horizontal tail area for given tail volume ratio
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Verified Horizontal tail volume ratio
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Verified Tail moment arm for given horizontal tail volume ratio
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Verified Wing Mean aerodynamic chord for given horizontal tail volume ratio
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Verified Wing Reference area for given horizontal tail volume ratio
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9 More Tail Contribution (Contd.) Calculators
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Takeoff Performance (10)
Verified Coefficient of rolling friction during ground roll
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Verified Drag during ground effect
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Verified Ground effect factor
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Verified Lift acting on aircraft during ground roll
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Verified Liftoff distance
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Verified Maximum Lift coefficient for given liftoff velocity
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Verified Resistance force during ground roll
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Verified Stall velocity for given weight
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Verified Thrust for given liftoff distance
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Verified Weight of aircraft during ground roll
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4 More Takeoff Performance Calculators
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The Atmosphere (5)
Verified Absolute altitude
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Verified Geometric altitude
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Verified Geometric altitude for given geopotential altitude
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Verified Geopotential altitude
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Verified Lapse rate
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Turbulent flow (3)
Verified Average height of irregularities for turbulent flow in pipes
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Verified Power required to maintain the turbulent flow
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Verified Roughness Reynold number for turbulent flow in pipes
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4 More Turbulent flow Calculators
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Turning Flight (7)
Verified Bank angle during level turn
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Verified Load factor
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Verified Load factor for a given turn radius
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Verified Turn rate
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Verified Velocity for a given turn radius
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Verified Velocity for a given turn rate
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Verified Weight for a given load factor
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5 More Turning Flight Calculators
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Ultimate Shear Strength of Connectors in Bridges (3)
Verified Channel Web Thickness when Ultimate Shear Connector Strength for Channels is Given
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Verified Elastic Modulus of Concrete when Ultimate Shear Connector Strength for Welded Studs is Given
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Verified Ultimate Shear Strength for Welded Studs
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6 More Ultimate Shear Strength of Connectors in Bridges Calculators
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Viscous flow (14)
Verified Diameter of capillary tube
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Verified Difference of pressure for viscous flow between two parallel plates
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Verified Discharge in capillary tube method
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Verified Length for difference of pressure in viscous flow between two parallel plates
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Verified Length for pressure head loss in viscous flow between two parallel plates
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Verified Length of tube in capillary tube method
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Verified Loss of pressure head for viscous flow between two parallel plates
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Verified Power absorbed in overcoming viscous resistance in journal bearing
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Verified Rotational speed considering power absorbed and torque in journal bearing
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Verified Shear force for torque and diameter of shaft in journal bearing
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Verified Shear stress in the fluid or oil of journal bearing
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Verified Torque required considering power absorbed in journal bearing
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Verified Torque required to overcome the shear force in journal bearing
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Verified Viscosity of fluid or oil for capillary tube method
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38 More Viscous flow Calculators
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Viscous Flow: Basic Aspects, Boundary Layer Results, and Aerodynamic Heating (3)
Verified Non dimensional internal energy parameter using wall-to-freestream temperature ratio
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Verified Non dimensional static enthalpy
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Verified Stanton equation using Overall skin friction coefficient for incompressible flow
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13 More Viscous Flow: Basic Aspects, Boundary Layer Results, and Aerodynamic Heating Calculators
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