Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Chilvera Bhanu Teja
Institute of Aeronautical Engineering (IARE), Hyderabad
Chilvera Bhanu Teja has verified this Calculator and 200+ more calculators!

11 Other formulas that you can solve using the same Inputs

Zero-lift drag coefficient for given required thrust
Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Coefficient of drag due to lift GO
Minimum Thrust required
Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+Coefficient of drag due to lift) GO
Weight of aircraft for given coefficients of lift and drag
Weight=lift coefficient*Thrust of an aircraft/Drag Coefficient GO
Coefficient of Lift for given thrust and weight
lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft GO
Thrust for given coefficients of lift and drag
Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient GO
Thrust required for level, unaccelerated flight
Thrust of an aircraft=Dynamic Pressure*Area*Drag Coefficient GO
Coefficient of Lift for given thrust-to-weight ratio
lift coefficient=Drag Coefficient/Thrust-to-weight ratio GO
Thrust-to-weight ratio
Thrust-to-weight ratio=Drag Coefficient/lift coefficient GO
Dynamic pressure
Dynamic Pressure=Drag Force/(Drag Coefficient*Area) GO
Drag for a level, unaccelerated flight at negligible thrust angle
Drag Force=Dynamic Pressure*Area*Drag Coefficient GO
Drag force
Drag Force=Drag Coefficient*Dynamic Pressure*Area GO

4 Other formulas that calculate the same Output

Zero-lift drag coefficient for given lift coefficient
Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Area))-((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Zero-lift drag coefficient for given required thrust
Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Coefficient of drag due to lift GO
Zero-lift drag coefficient at minimum required thrust
Zero-lift drag coefficient=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing) GO
Zero-lift drag coefficient for minimum power required
Zero-lift drag coefficient=Coefficient of drag due to lift/3 GO

Parasite Drag Coefficient at zero lift Formula

Zero-lift drag coefficient=Drag Coefficient-Coefficient of drag due to lift
C<sub>D,0</sub>=C<sub>D</sub>-C<sub>D,i</sub>
More formulas
Drag Coefficient for given parasite drag coefficient GO
Drag Coefficient for given zero-lift drag coefficient GO
Coefficient of Drag due to 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

How do you stop a parasitic drag?

There are two ways to decrease friction drag: the first is to shape the moving body so that laminar flow is possible. The second method is to increase the length and decrease the cross-section of the moving object as much as practicable.

How to Calculate Parasite Drag Coefficient at zero lift?

Parasite Drag Coefficient at zero lift calculator uses Zero-lift drag coefficient=Drag Coefficient-Coefficient of drag due to lift to calculate the Zero-lift drag coefficient, The Parasite Drag Coefficient at zero lift is the difference between total drag coefficient and coefficient of drag due to lift. Zero-lift drag coefficient and is denoted by CD,0 symbol.

How to calculate Parasite Drag Coefficient at zero lift using this online calculator? To use this online calculator for Parasite Drag Coefficient at zero lift, enter Drag Coefficient (CD) and Coefficient of drag due to lift (CD,i) and hit the calculate button. Here is how the Parasite Drag Coefficient at zero lift calculation can be explained with given input values -> 99.2 = 100-0.8.

FAQ

What is Parasite Drag Coefficient at zero lift?
The Parasite Drag Coefficient at zero lift is the difference between total drag coefficient and coefficient of drag due to lift and is represented as CD,0=CD-CD,i or Zero-lift drag coefficient=Drag Coefficient-Coefficient of drag due to lift. Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water and The Coefficient of drag due to lift is the sum of the coefficients of induced drag and the increment in parasite drag due to the angle of attack different from the zero-lift angle of attack.
How to calculate Parasite Drag Coefficient at zero lift?
The Parasite Drag Coefficient at zero lift is the difference between total drag coefficient and coefficient of drag due to lift is calculated using Zero-lift drag coefficient=Drag Coefficient-Coefficient of drag due to lift. To calculate Parasite Drag Coefficient at zero lift, you need Drag Coefficient (CD) and Coefficient of drag due to lift (CD,i). With our tool, you need to enter the respective value for Drag Coefficient and Coefficient of drag due to lift 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 Zero-lift drag coefficient?
In this formula, Zero-lift drag coefficient uses Drag Coefficient and Coefficient of drag due to lift. We can use 4 other way(s) to calculate the same, which is/are as follows -
  • Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Coefficient of drag due to lift
  • Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Area))-((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))
  • Zero-lift drag coefficient=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)
  • Zero-lift drag coefficient=Coefficient of drag due to lift/3
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