Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Sai Venkata Phanindra Chary Arendra
Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad
Sai Venkata Phanindra Chary Arendra has verified this Calculator and 100+ more calculators!

11 Other formulas that you can solve using the same Inputs

Drag Coefficient for given zero-lift drag coefficient
Drag Coefficient=Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Coefficient of Drag due to lift
Coefficient of drag due to lift=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing) GO
Weight of aircraft for given coefficients of lift and drag
Weight=lift coefficient*Thrust of an aircraft/Drag Coefficient GO
Coefficient of Drag for given thrust and weight
Drag Coefficient=Thrust of an aircraft*lift coefficient/Weight GO
Thrust for given coefficients of lift and drag
Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient GO
Coefficient of Drag for given thrust-to-weight ratio
Drag Coefficient=lift coefficient*Thrust-to-weight ratio GO
Thrust-to-weight ratio
Thrust-to-weight ratio=Drag Coefficient/lift coefficient GO
Dynamic pressure based on coefficient of lift
Dynamic Pressure=Lift force/(lift coefficient*Area) GO
Lift for a level, unaccelerated flight at negligible thrust angle
Lift force=Dynamic Pressure*Area*lift coefficient GO
Lift Force
Lift force=lift coefficient*Dynamic Pressure*Area GO
Weight of aircraft for a level, unaccelerated flight at negligible thrust angle
Weight=Dynamic Pressure*Area*lift coefficient GO

11 Other formulas that calculate the same Output

Drag Coefficient for given zero-lift drag coefficient
Drag Coefficient=Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Drag coefficient of flat plate laminar flow given Schmidt number
Drag Coefficient=(2*Convective mass transfer coefficient*(Schmidt Number^0.67))/Free stream velocity GO
Coefficient of drag equation using energy released from blast wave
Drag Coefficient=Energy/(0.5*Freestream density*(Freestream Velocity^2)*Diameter ) GO
Coefficient of Drag for given thrust and weight
Drag Coefficient=Thrust of an aircraft*lift coefficient/Weight GO
Coefficient of drag equation with coefficient of normal force
Drag Coefficient=coefficient of force*sin(Angle of attack) GO
Coefficient of Drag for given thrust-to-weight ratio
Drag Coefficient=lift coefficient*Thrust-to-weight ratio GO
Coefficient of drag
Drag Coefficient=Drag Force/(Dynamic Pressure*Area) GO
Drag coefficient of flat plate in combined laminar turbulent flow
Drag Coefficient=0.0571/(Reynolds Number^0.2) GO
Drag coefficient of flat plate laminar flow
Drag Coefficient=0.644/(Reynolds Number^0.5) GO
Coefficient of drag equation with angle of attack
Drag Coefficient=2*(sin(Angle of attack))^3 GO
drag coefficient of flat plate laminar flow given friction factor
Drag Coefficient=Friction factor/4 GO

Drag Coefficient for given parasite drag coefficient Formula

Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))
C<sub>D</sub>=C<sub>D,e</sub>+((C<sub>L</sub>^2)/(pi*e*AR))
More formulas
Drag Coefficient for given zero-lift drag coefficient GO
Coefficient of Drag due to lift GO
Parasite Drag Coefficient at zero lift GO
Thrust in an accelerated flight GO
Drag in an accelerated flight GO
Lift in an accelerated flight GO
Centrifugal Force in an accelerated flight GO
Velocity in an accelerated flight GO
Thrust for a level, unaccelerated flight GO
Drag for a level, unaccelerated flight GO
Thrust angle for an unaccelerated flight for given drag GO
Lift for an unaccelerated flight GO
Weight of aircraft in level, unaccelerated flight GO
Thrust angle for an unaccelerated flight for given lift GO
Thrust required for level, unaccelerated flight GO
Drag for a level, unaccelerated flight at negligible thrust angle GO
Lift for a level, unaccelerated flight at negligible thrust angle GO
Weight of aircraft for a level, unaccelerated flight at negligible thrust angle GO
Thrust-to-weight ratio GO
Thrust for given coefficients of lift and drag GO
Weight of aircraft for given coefficients of lift and drag GO
Coefficient of Drag for given thrust-to-weight ratio GO
Coefficient of Lift for given thrust-to-weight ratio GO
Coefficient of Drag for given thrust and weight GO
Coefficient of Lift for given thrust and weight GO
Thrust required for given Lift-to-drag ratio GO
Weight of aircraft for given Lift-to-drag ratio GO
Lift-to-drag ratio for given required thrust GO
Minimum Thrust required GO
Zero-lift drag coefficient for given required thrust GO
Lift-induced drag coefficient for given required thrust GO
Minimum Thrust required for given lift coefficient GO
Zero-lift drag coefficient for given lift coefficient GO
Lift coefficient for given minimum required thrust GO
Minimum Thrust required for given weight GO
Zero-lift drag coefficient at minimum required thrust GO
Power required for given required thrust GO
Thrust required for given required power GO
Freestream velocity for given required power GO
Power required for given aerodynamic coefficients GO
Weight of aircraft for given required power GO
Zero-lift drag coefficient for minimum power required GO
Coefficient of Drag due to lift for minimum power required GO
Power required for given total drag GO
Total drag for given required power GO
Freestream Velocity for given total drag GO
Power available for reciprocating engine-propeller combination GO
Shaft brake power for reciprocating engine-propeller combination GO
Propeller efficiency for reciprocating engine-propeller combination GO
Rate of Climb GO
Velocity of aircraft at a given rate of climb GO
Flight path angle at a given rate of climb GO
Velocity at sea-level condition GO
Power required at sea-level condition GO
Velocity at an altitude GO
Power required at an altitude GO
Velocity at an altitude for given velocity at sea-level condition GO
Power required at an altitude for given power required at sea-level condition GO
Excess power GO
Thrust available for given excess power GO
Total Drag for given excess power GO
Velocity of aircraft for given excess power GO
Rate of Climb for given excess power GO
Excess power for given rate of climb GO
Weight of aircraft for given excess power GO
Glide angle GO
Glide angle for given lift-to-drag ratio GO
Lift-to-drag ratio for given glide angle GO
Lift for given glide angle GO
Drag for given glide angle GO
Range of Propeller-Driven Airplane GO
Propeller Efficiency for given Range of Propeller-Driven Airplane GO
Specific Fuel Consumption for given Range of Propeller-Driven Airplane GO
Range of Propeller-Driven Airplane for given lift-to-drag ratio GO
Propeller Efficiency for given Range and lift-to-drag ratio of Propeller-Driven Airplane GO
Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane GO
Lift-to-Drag ratio for given Range of Propeller-Driven Airplane GO
Endurance of Propeller-Driven Airplane GO
Propeller Efficiency for given Endurance of Propeller-Driven Airplane GO
Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane GO
Endurance of Jet Airplane GO
Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane GO
Endurance for given Lift-to-Drag ratio of Jet Airplane GO
Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag ratio of Jet Airplane GO
Lift-to-Drag ratio for given Endurance of Jet Airplane GO
Range of Jet Airplane GO
Thrust-Specific Fuel Consumption for given Range of Jet Airplane GO
Resistance force during ground roll GO
Coefficient of rolling friction during ground roll GO
Weight of aircraft during ground roll GO
Lift acting on aircraft during ground roll GO
Ground effect factor GO
Drag during ground effect GO
Liftoff velocity for given stall velocity GO
Stall velocity for given liftoff velocity GO
Liftoff velocity for given weight GO
Stall velocity for given weight GO
Maximum Lift coefficient for given stall velocity GO
Maximum Lift coefficient for given liftoff velocity GO
Liftoff distance GO
Thrust for given liftoff distance GO
Lift during level turn GO
Bank angle during level turn GO
Weight during level turn GO
Load factor GO
Landing ground roll distance using thrust reversal GO
Touchdown velocity GO
Touchdown velocity for given stall velocity GO
Stall velocity for given touchdown velocity GO
Landing ground roll distance GO
Lift for a given load factor GO
Weight for a given load factor GO
Turn radius GO
Velocity for a given turn radius GO
Load factor for a given turn radius GO
Turn rate GO
Velocity for a given turn rate GO
Load factor for a given turn rate GO
Pull-up maneuver radius GO
Velocity for a given pull-up maneuver radius GO
Load factor for a given pull-up maneuver radius GO
Pull-up maneuver rate GO
Load factor for a given pull-up maneuver rate GO
Velocity for a given pull-up maneuver rate GO
Pull-down maneuver radius GO
Velocity for a given pull-down maneuver radius GO
Load factor for a given pull-down maneuver radius GO
Pull-down maneuver rate GO
Velocity for a given pull-down maneuver rate GO
Load factor for a given pull-down maneuver rate GO
Turn radius for a high load factor GO
Velocity for a given turn radius for a high load factor GO
Load factor for a given turn radius for a high-performance fighter aircraft GO
Turn rate for a high load factor GO
Velocity for a given turn rate for a high load factor GO
Load factor for a given turn rate for a high-performance fighter aircraft GO
Radius of turn for a given lift coefficient GO
Lift Coefficient for a given turn radius GO
Turn rate for a given lift coefficient GO
Lift Coefficient for a given turn rate GO
Radius of turn for a given wing loading GO
Lift Coefficient for a given wing loading and turn radius GO
Wing loading for a given turn radius GO
Turn rate for a given wing loading GO
Wing loading for a given turn rate GO

What is parasite drag on an airplane?

Parasite (Parasitic) Drag is defined as the total drag of an airplane that is not associated with the production of lift.

How to Calculate Drag Coefficient for given parasite drag coefficient?

Drag Coefficient for given parasite drag coefficient calculator uses Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) to calculate the Drag Coefficient, The Drag Coefficient for given parasite drag coefficient is the drag coefficient of the complete airplane as a function of the total lift coefficient and the parasitic drag coefficient. Drag Coefficient and is denoted by CD symbol.

How to calculate Drag Coefficient for given parasite drag coefficient using this online calculator? To use this online calculator for Drag Coefficient for given parasite drag coefficient, enter Parasite Drag coefficient (CD,e), lift coefficient (CL), Oswald efficiency factor (e) and Aspect Ratio of a wing (AR) and hit the calculate button. Here is how the Drag Coefficient for given parasite drag coefficient calculation can be explained with given input values -> 20.91549 = 5+((10^2)/(pi*0.5*4)).

FAQ

What is Drag Coefficient for given parasite drag coefficient?
The Drag Coefficient for given parasite drag coefficient is the drag coefficient of the complete airplane as a function of the total lift coefficient and the parasitic drag coefficient and is represented as CD=CD,e+((CL^2)/(pi*e*AR)) or Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)). The parasite Drag coefficient is defined as the combination of coefficients of form drag and skin friction drag, The lift coefficient (CL) is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area. , The Oswald efficiency factor is a correction factor that represents the change in drag with lift of a three-dimensional wing or airplane, as compared with an ideal wing having the same aspect ratio and The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.
How to calculate Drag Coefficient for given parasite drag coefficient?
The Drag Coefficient for given parasite drag coefficient is the drag coefficient of the complete airplane as a function of the total lift coefficient and the parasitic drag coefficient is calculated using Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)). To calculate Drag Coefficient for given parasite drag coefficient, you need Parasite Drag coefficient (CD,e), lift coefficient (CL), Oswald efficiency factor (e) and Aspect Ratio of a wing (AR). With our tool, you need to enter the respective value for Parasite Drag coefficient, lift coefficient, Oswald efficiency factor and Aspect Ratio of a wing and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
How many ways are there to calculate Drag Coefficient?
In this formula, Drag Coefficient uses Parasite Drag coefficient, lift coefficient, Oswald efficiency factor and Aspect Ratio of a wing. We can use 11 other way(s) to calculate the same, which is/are as follows -
  • Drag Coefficient=Drag Force/(Dynamic Pressure*Area)
  • Drag Coefficient=Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))
  • Drag Coefficient=lift coefficient*Thrust-to-weight ratio
  • Drag Coefficient=Thrust of an aircraft*lift coefficient/Weight
  • Drag Coefficient=coefficient of force*sin(Angle of attack)
  • Drag Coefficient=2*(sin(Angle of attack))^3
  • Drag Coefficient=Energy/(0.5*Freestream density*(Freestream Velocity^2)*Diameter )
  • Drag Coefficient=0.644/(Reynolds Number^0.5)
  • Drag Coefficient=(2*Convective mass transfer coefficient*(Schmidt Number^0.67))/Free stream velocity
  • Drag Coefficient=Friction factor/4
  • Drag Coefficient=0.0571/(Reynolds Number^0.2)
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