Calculator A to Z
🔍
🔍

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
175
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 175 calculators across 48 different categories till date.
Aerodynamic Nomenclature (8)
Verified Aerodynamic axial force
Go
Verified Aerodynamic normal force
Go
Verified Aerodynamic side force
Go
Verified Angle of attack
Go
Verified Pitching moment
Go
Verified Pitching moment coefficient
Go
Verified Side force coefficient
Go
Verified Sideslip angle
Go
9 More Aerodynamic Nomenclature Calculators
Go
Altitude Effects on Power Required and Available (3)
Verified Power required at sea-level condition
Go
Verified Velocity at an altitude for given velocity at sea-level condition
Go
Verified Velocity at sea-level condition
Go
3 More Altitude Effects on Power Required and Available Calculators
Go
Basic Compressible Flow (3)
Created Critical Density
Go
Created Critical Pressure
Go
Created Critical Temperature
Go
3 More Basic Compressible Flow Calculators
Go
Basics (1)
Created Isentropic compressibility for given density and speed of sound
Go
6 More Basics Calculators
Go
Bending Stresses (1)
Verified Section Modulus of Steel Beam when Stress in Steel for Unshored Members is Given
Go
8 More Bending Stresses Calculators
Go
Blast-wave part 2 (3)
Verified Pressure coefficient combined with blast wave for the shuttle
Go
Verified Pressure coefficient combined with blast wave for the shuttle at angle of attack
Go
Verified Pressure coefficient for Blunt-nosed cylinder:
Go
3 More Blast-wave part 2 Calculators
Go
Bodies connected by a string - one hanging free, other lying on a rough horizontal plane (1)
Verified Acceleration of the system with bodies one hanging free and other lying on a rough horizontal plane
Go
1 More Bodies connected by a string - one hanging free, other lying on a rough horizontal plane Calculators
Go
Bodies connected by a string - one hanging free, other lying on a smooth horizontal plane (2)
Verified Acceleration in the system
Go
Verified Tension in the string if only one body is freely suspended
Go
Bodies connected by a string and passing over a smooth pulley (3)
Verified Acceleration of the bodies
Go
Verified Mass of body B (smaller mass)
Go
Verified Tension in the string if both the bodies are freely hanging
Go
Boundary layer flow (5)
Verified Coefficient of drag for Reynold number in the laminar boundary layer flow
Go
Verified Drag force on the plate in boundary layer flow
Go
Verified Reynold number for drag force on the plate in boundary layer flow
Go
Verified Viscosity of liquid for drag force on the plate in boundary layer flow
Go
Verified Width of the plate for drag force on the plate in boundary layer flow
Go
16 More Boundary layer flow Calculators
Go
Boundary-Layer Equations for Hypersonic Flow: Self-Similar Solutions (5)
Verified Adiabatic wall enthalpy using Stanton number
Go
Verified Enthalpy of wall using Stanton number
Go
Verified Nusselt number for hypersonic vehicle
Go
Verified Reynolds number for given Nusselt's number, Stanton number and Prandtl number
Go
Verified Skin friction coefficient for incompressible flow
Go
15 More Boundary-Layer Equations for Hypersonic Flow: Self-Similar Solutions Calculators
Go
Compressible flow (3)
Verified Mach angle for the compressible fluid flow
Go
Verified Velocity of fluid considering the Mach angle in the compressible fluid flow
Go
Verified Velocity of sound wave considering Mach angle in the compressible fluid flow
Go
21 More Compressible flow Calculators
Go
Contribution of Aircraft Components (Part 1) (6)
Verified Moment produced by vertical tail for given lift curve slope
Go
Verified Moment produced by vertical tail for given side force
Go
Verified Sideslip angle for given moment produced by vertical tail
Go
Verified Vertical tail angle of attack
Go
Verified Vertical tail moment arm for given side force
Go
Verified Vertical tail side force for given moment
Go
9 More Contribution of Aircraft Components (Part 1) Calculators
Go
Contribution of Aircraft Components (Part 2) (3)
Verified Moment produced by vertical tail for given moment coefficient
Go
Verified Vertical tail area for given moment
Go
Verified Yawing moment coefficient when wingspan is given
Go
11 More Contribution of Aircraft Components (Part 2) Calculators
Go
Contribution of Aircraft Components (Part 3) (6)
Verified Vertical tail area for given vertical tail volume ratio
Go
Verified Vertical tail moment arm for given vertical tail volume ratio
Go
Verified Vertical tail volume ratio
Go
Verified Wing area for given vertical tail volume ratio
Go
Verified Wing area for given yawing moment coefficient
Go
Verified Wingspan for given vertical tail volume ratio
Go
9 More Contribution of Aircraft Components (Part 3) Calculators
Go
Dynamics of fluid flow (2)
Verified Coefficient of pitot-tube for velocity at any point
Go
Verified Resultant force on bend for force along x and y-direction
Go
4 More Dynamics of fluid flow Calculators
Go
Elevator Hinge Moment (1)
Verified Elevator chord length for given hinge moment coefficient
Go
4 More Elevator Hinge Moment Calculators
Go
Flat-Plate for Viscous flow case (1)
Verified Total enthalpy in the inviscid flow outside the boundary layer
Go
14 More Flat-Plate for Viscous flow case Calculators
Go
Flight Envelope (5)
Verified Lift Coefficient for a given turn rate
Go
Verified Load factor for a given turn rate for a high-performance fighter aircraft
Go
Verified Radius of turn for a given lift coefficient
Go
Verified Radius of turn for a given wing loading
Go
Verified Turn rate for a given wing loading
Go
10 More Flight Envelope Calculators
Go
Flow through pipes (14)
Verified Area of the nozzle at outlet for maximum power transmission through nozzle
Go
Verified Area of the pipe for maximum power transmission through nozzle
Go
Verified Diameter of nozzle for maximum power transmission through nozzle
Go
Verified Diameter of the equivalent pipe
Go
Verified Discharge in the equivalent pipe
Go
Verified Efficiency of power transmission through nozzle for velocity and total head
Go
Verified Efficiency of power transmission through the nozzle
Go
Verified Length of pipe for maximum power transmission through nozzle
Go
Verified Length of the equivalent pipe
Go
Verified Loss of head at the entrance of a pipe
Go
Verified Loss of head in the equivalent pipe
Go
Verified Velocity of flow at the outlet of the nozzle
Go
Verified Velocity of flow at the outlet of the nozzle for efficiency and head
Go
Verified Velocity of fluid in pipe for head loss at the entrance of a pipe
Go
25 More Flow through pipes Calculators
Go
Forces on sub-merged bodies (9)
Verified Angle of attack for circulation developed on the airfoil
Go
Verified Area of the body for lift force in a body moving on a fluid
Go
Verified Chord length for circulation developed on the airfoil
Go
Verified Circulation developed on the airfoil
Go
Verified lift coefficient for lift force in a body moving on a fluid
Go
Verified Lift force for a body moving in a fluid of certain density
Go
Verified Pressure drag from total drag force on a sphere
Go
Verified Skin friction drag from total drag force on a sphere
Go
Verified Velocity of airfoil for circulation developed on the airfoil
Go
22 More Forces on sub-merged bodies Calculators
Go
Fundamentals of Inviscid Incompressible flow (47)
Created 2-D Lift coefficient for cylinder
Go
Created Airspeed measurement by Pitot tube for low-speed incompressible flow
Go
Created Airspeed measurement by venturi
Go
Created Circulation by Kutta-Joukowski theorem
Go
Created Dynamic pressure in incompressible flow
Go
Created Freestream density by Kutta-Joukowski theorem
Go
Created Freestream velocity by Kutta-Joukowski theorem
Go
Created Height difference of manometric fluid for given pressure difference
Go
Created Lift per unit span by Kutta-Joukowski theorem
Go
Created Location of stagnation point outside the cylinder for lifting flow
Go
Created Pressure at a downstream point on streamline by Bernoulli's equation
Go
Created Pressure at an upstream point on streamline by Bernoulli's equation
Go
Created Pressure Coefficient
Go
Created Pressure coefficient in terms of velocity ratio for inncompressible flow
Go
Created Pressure difference in the low-speed wind tunnel for given test section velocity
Go
Created Pressure difference measured by manometer in the low-speed wind tunnel
Go
Created Radial velocity for 2-D incompressible source flow
Go
Created Radial velocity for lifting flow over circular cylinder
Go
Created Radial velocity for non-lifting flow over circular cylinder
Go
Created Radius of cylinder for non-lifting flow
Go
Created Source Strength for 2-D incompressible source flow
Go
Created Stagnation streamline equation for flow over semi-infinite body
Go
Created Static pressure in incompressible flow
Go
Created Stream function for 2-D Doublet flow
Go
Created Stream function for 2-D incompressible source flow
Go
Created Stream function for 2-D Vortex flow
Go
Created Stream function for flow over Rankine oval
Go
Created Stream function for lifting flow over a circular cylinder
Go
Created Stream function for non-lifting flow over a circular cylinder
Go
Created Stream function for semi-infinite body
Go
Created Stream function for uniform incompressible flow
Go
Created Stream function for uniform incompressible flow in polar coordinates
Go
Created Surface pressure coefficient for lifting flow over circular cylinder
Go
Created Surface pressure coefficient for non-lifting flow over circular cylinder
Go
Created Surface pressure on the body in terms of Pressure coefficient
Go
Created Tangential velocity for 2-D Vortex flow
Go
Created Tangential velocity for lifting flow over circular cylinder
Go
Created Tangential velocity for non-lifting flow over circular cylinder
Go
Created Test section velocity for low sped wind tunnel in terms of height difference of manometric fluid
Go
Created Test section velocity in low-speed wind tunnel
Go
Created Total pressure in incompressible flow
Go
Created Velocity at a point on airfoil for given pressure coefficient and free-stream velocity
Go
Created Velocity potential for 2-D doublet flow
Go
Created Velocity potential for 2-D source flow
Go
Created Velocity potential for 2-D Vortex flow
Go
Created Velocity potential for uniform incompressible flow
Go
Created Velocity potential for uniform incompressible flow in polar coordinates
Go
Hypersonic Equivalence Principle and Blast-Wave Theory (3)
Verified Modified pressure equation for cylindrical blast wave
Go
Verified Pressure ratio for blunt cylinder blast wave
Go
Verified Pressure ratio for blunt slab blast wave
Go
13 More Hypersonic Equivalence Principle and Blast-Wave Theory Calculators
Go
Hypersonic Flight Paths: Velocity-Altitude Map (1)
Verified Blunt-nosed radial coordinate flat plate (first approximation):
Go
8 More Hypersonic Flight Paths: Velocity-Altitude Map Calculators
Go
Hypersonic Inviscid Flowfields: Exact Methods (7)
Verified Density before shock formation for compression wave
Go
Verified Local shock velocity equation
Go
Verified Mach wave behind the shock
Go
Verified Mach wave behind the shock with mach infinity
Go
Verified New pressure after the shock formation, subtracted to velocity for expansion wave
Go
Verified Pressure ratio for unsteady waves with subtracted induced mass motion for expansion waves
Go
Verified Temperature ratio for unsteady compression waves
Go
11 More Hypersonic Inviscid Flowfields: Exact Methods Calculators
Go
Ideal flow or Potential flow (1)
Verified Distance of stagnation point S from source in flow past a half body
Go
14 More Ideal flow or Potential flow Calculators
Go
Incompressible flow over airfoil (8)
Created Boundary layer thickness for laminar flow
Go
Created Boundary layer thickness for Turbulent flow
Go
Created Center of pressure location for cambered airfoil
Go
Created Lift coefficient for cambered airfoil
Go
Created Lift coefficient for symmetrical airfoil by Thin airfoil theory
Go
Created Moment coefficient about leading-edge for symmetrical airfoil by thin airfoil theory
Go
Created Skin friction drag coefficient for flat plate in laminar flow
Go
Created Skin friction drag coefficient for flat plate in Turbulent flow
Go
Landing Performance (1)
Verified Stall velocity for given touchdown velocity
Go
4 More Landing Performance Calculators
Go
Maneuvering Flight (1)
Verified Velocity for a given pull-down maneuver radius
Go
11 More Maneuvering Flight Calculators
Go
Merchant Force Circle (Mechanics of Orthogonal metal cutting) (12)
Created Cutting force for given force along shear force, shear,friction & normal rake angles
Go
Created Cutting force for given resultant force in merchant circle, friction angle and normal rake angle
Go
Created Cutting force for shear stress,width of cut,uncut chip thickness,friction,normal rake & shear angles
Go
Created Force along shear force for given R of merchant circle, shear, friction and normal rake angles
Go
Created Friction angle for given R of merchant circle, force along shear force,shear & normal rake angles
Go
Created Normal rake angle for given Resultant force, force along shear force, shear & friction angles
Go
Created R in merchant circle for given force along the shear force, shear, friction & normal rake angles
Go
Created Resultant force in merchant circle for given cutting force, friction and normal rake angles
Go
Created Shear angle for given Resultant force ,force along shear force,friction & normal rake angles
Go
Created Shear stress for cutting force,width of cut,uncut chip thickness,friction,normal rake & shear angles
Go
Created Uncut chip thickness for cutting force,shear stress,width of cut,friction,normal rake & shear angles
Go
Created Width of cut for cutting force,shear stress,uncut chip thickness,friction,normal rake & shear angles
Go
26 More Merchant Force Circle (Mechanics of Orthogonal metal cutting) Calculators
Go
Normal Shock Waves (21)
Created Critical speed of sound from Prandtl relation
Go
Created Density ahead of normal shock using normal shock momentum equation
Go
Created Density behind normal shock for given upstream density and Mach number
Go
Created Density behind normal shock using normal shock momentum equation
Go
Created Density ratio across a normal shock
Go
Created Enthalpy ahead of normal shock from normal shock energy equation
Go
Created Enthalpy behind of normal shock from normal shock energy equation
Go
Created Pressure ratio across a normal shock
Go
Created Stagnation pressure behind normal shock by Rayleigh Pitot tube formula
Go
Created Static enthalpy behind normal shock for given upstream enthalpy and Mach number
Go
Created Static enthalpy ratio across a normal shock
Go
Created Static Pressure ahead of normal shock using normal shock momentum equation
Go
Created Static pressure behind normal shock for given upstream pressure and Mach number
Go
Created Static Pressure behind of normal shock using normal shock momentum equation
Go
Created Static temperature behind normal shock for given upstream temperature and Mach number
Go
Created Temperature ratio across a normal shock
Go
Created Velocity ahead of normal shock by normal shock momentum equation
Go
Created Velocity ahead of normal shock from normal shock energy equation
Go
Created Velocity behind of normal shock by normal shock momentum equation
Go
Created Velocity behind of normal shock from normal shock energy equation
Go
Created Velocity upstream of shock using Prandtl relation
Go
8 More Normal Shock Waves Calculators
Go
Notches and Weirs (8)
Verified Discharge over rectangle weir considering Bazin's formula
Go
Verified Discharge over rectangle weir considering Francis's formula
Go
Verified Discharge with velocity of approach
Go
Verified Discharge without velocity of approach
Go
Verified Length of weir considering Bazin's formula without velocity approach
Go
Verified Length of weir considering Francis's formula
Go
Verified Length of weir or notch for velocity of approach
Go
Verified Length of weir or notch without velocity of approach
Go
19 More Notches and Weirs Calculators
Go
Number of Connectors in Bridges (5)
Verified Effective Concrete Area when Force in Slab is Given
Go
Verified Force in Slab at Maximum Positive Moments when Minimum Number of Connectors for Bridges is Given
Go
Verified Force in Slab when Effective Concrete Area is Given
Go
Verified Minimum Number of Connectors for Bridges
Go
Verified Steel Yield Strength when Total Area of Steel Section is Given
Go
13 More Number of Connectors in Bridges Calculators
Go
Oblique Shock and Expansion Waves (16)
Created Component of downstream Mach no. normal to oblique shock for given normal upstream Mach no.
Go
Created Density behind oblique shock for given upstream density & normal upstream Mach no.
Go
Created Density ratio across the oblique shock
Go
Created Flow deflection angle in terms of Prandtl Meyer function
Go
Created Forward Mach angle of expansion fan
Go
Created Prandtl Meyer function
Go
Created Prandtl Meyer function at upstream Mach no.
Go
Created Pressure behind expansion fan
Go
Created Pressure behind oblique shock for given upstream pressure & normal upstream Mach no
Go
Created Pressure ratio across the expansion fan
Go
Created Pressure ratio across the oblique shock
Go
Created Rearward Mach angle of the expansion fan
Go
Created Temperature behind expansion fan
Go
Created Temperature behind oblique shock for given upstream temperature & normal upstream Mach no.
Go
Created Temperature ratio across the expansion fan
Go
Created Temperature ratio across the oblique shock
Go
3 More Oblique Shock and Expansion Waves Calculators
Go
Rate of Climb (2)
Verified Excess power
Go
Verified Total Drag for given excess power
Go
8 More Rate of Climb Calculators
Go
Reference Temperature Method (1)
Verified Overall skin-friction drag coefficient
Go
14 More Reference Temperature Method Calculators
Go
Relationship between Stick Force and Hinge Moment (5)
Verified Elevator deflection angle for given stick force
Go
Verified Elevator Stick Force
Go
Verified Elevator stick force for given hinge moment coefficient
Go
Verified Gearing ratio for given stick force
Go
Verified Stick deflection angle for given gearing ratio
Go
13 More Relationship between Stick Force and Hinge Moment Calculators
Go
Shear Range (1)
Verified Horizontal Shear Range at the juncture of Slab and Beam
Go
11 More Shear Range Calculators
Go
Space-Marching Finite Difference Method: Additional Solutions of the Euler Equations (3)
Verified Enthalpy equation using coefficient of pressure for calorically perfect gas
Go
Verified Free stream enthalpy
Go
Verified Total enthalpy
Go
8 More Space-Marching Finite Difference Method: Additional Solutions of the Euler Equations Calculators
Go
Tail Contribution (5)
Verified Angle of attack at the tail
Go
Verified Downwash angle
Go
Verified Pitching moment due to tail
Go
Verified Tail Pitching moment for given moment coefficient
Go
Verified Total Lift Coefficient of wing-tail combination
Go
16 More Tail Contribution Calculators
Go
Tail Contribution (Contd.) (5)
Verified Horizontal tail area for given tail volume ratio
Go
Verified Horizontal tail volume ratio
Go
Verified Tail moment arm for given horizontal tail volume ratio
Go
Verified Wing Mean aerodynamic chord for given horizontal tail volume ratio
Go
Verified Wing Reference area for given horizontal tail volume ratio
Go
9 More Tail Contribution (Contd.) Calculators
Go
Takeoff Performance (10)
Verified Coefficient of rolling friction during ground roll
Go
Verified Drag during ground effect
Go
Verified Ground effect factor
Go
Verified Lift acting on aircraft during ground roll
Go
Verified Liftoff distance
Go
Verified Maximum Lift coefficient for given liftoff velocity
Go
Verified Resistance force during ground roll
Go
Verified Stall velocity for given weight
Go
Verified Thrust for given liftoff distance
Go
Verified Weight of aircraft during ground roll
Go
4 More Takeoff Performance Calculators
Go
The Atmosphere (5)
Verified Absolute altitude
Go
Verified Geometric altitude
Go
Verified Geometric altitude for given geopotential altitude
Go
Verified Geopotential altitude
Go
Verified Lapse rate
Go
Turbulent flow (3)
Verified Average height of irregularities for turbulent flow in pipes
Go
Verified Power required to maintain the turbulent flow
Go
Verified Roughness Reynold number for turbulent flow in pipes
Go
4 More Turbulent flow Calculators
Go
Turning Flight (7)
Verified Bank angle during level turn
Go
Verified Load factor for a given turn radius
Go
Verified Load factor when Lift Force and Weight is Given
Go
Verified Turn rate
Go
Verified Velocity for a given turn radius
Go
Verified Velocity for a given turn rate
Go
Verified Weight for a given load factor
Go
5 More Turning Flight Calculators
Go
Ultimate Shear Strength of Connectors in Bridges (3)
Verified Channel Web Thickness when Ultimate Shear Connector Strength for Channels is Given
Go
Verified Elastic Modulus of Concrete when Ultimate Shear Connector Strength for Welded Studs is Given
Go
Verified Ultimate Shear Strength for Welded Studs
Go
6 More Ultimate Shear Strength of Connectors in Bridges Calculators
Go
Viscous flow (14)
Verified Diameter of capillary tube
Go
Verified Difference of pressure for viscous flow between two parallel plates
Go
Verified Discharge in capillary tube method
Go
Verified Length for difference of pressure in viscous flow between two parallel plates
Go
Verified Length for pressure head loss in viscous flow between two parallel plates
Go
Verified Length of tube in capillary tube method
Go
Verified Loss of pressure head for viscous flow between two parallel plates
Go
Verified Power absorbed in overcoming viscous resistance in journal bearing
Go
Verified Rotational speed considering power absorbed and torque in journal bearing
Go
Verified Shear force for torque and diameter of shaft in journal bearing
Go
Verified Shear stress in the fluid or oil of journal bearing
Go
Verified Torque required considering power absorbed in journal bearing
Go
Verified Torque required to overcome the shear force in journal bearing
Go
Verified Viscosity of fluid or oil for capillary tube method
Go
38 More Viscous flow Calculators
Go
Viscous Flow: Basic Aspects, Boundary Layer Results, and Aerodynamic Heating (3)
Verified Non dimensional internal energy parameter using wall-to-freestream temperature ratio
Go
Verified Non dimensional static enthalpy
Go
Verified Stanton equation using Overall skin friction coefficient for incompressible flow
Go
13 More Viscous Flow: Basic Aspects, Boundary Layer Results, and Aerodynamic Heating Calculators
Go
About | Contact | Disclaimer | Terms
© 2011-2021 A softusvista inc. venture!


Share Image
Let Others Know
✖
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!