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!

8 Other formulas that you can solve using the same Inputs

Landing ground roll distance using thrust reversal
Landing Roll=1.69*(Weight^2)*(1/([g]*Freestream density*Reference Area*Maximum Lift Coefficient))*(1/((0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*(Zero-lift drag coefficient+(Ground effect factor*(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))))+(Reverse thrust)+(Coefficient of Rolling Friction*(Weight-(0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*lift coefficient))))) GO
Landing ground roll distance
Landing Roll=1.69*(Weight^2)*(1/([g]*Freestream density*Reference Area*Maximum Lift Coefficient))*(1/((0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*(Zero-lift drag coefficient+(Ground effect factor*(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))))+(Coefficient of Rolling Friction*(Weight-(0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*lift coefficient))))) GO
Minimum Thrust required for given weight
Thrust of an aircraft=(Dynamic Pressure*Reference Area*Zero-lift drag coefficient)+((Weight^2)/(Dynamic Pressure*Reference Area*pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Lift coefficient for given minimum required thrust
lift coefficient=sqrt(pi*Oswald efficiency factor*Aspect Ratio of a wing*((Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Zero-lift drag coefficient)) GO
Minimum Thrust required for given lift coefficient
Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))) GO
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
Lift-induced drag coefficient for given required thrust
Coefficient of drag due to lift=(Thrust of an aircraft/(Dynamic Pressure*Area))-Zero-lift drag coefficient GO
Minimum Thrust required
Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+Coefficient of drag due to lift) GO

2 Other formulas that calculate the same Output

Lift-induced drag coefficient for given required thrust
Coefficient of drag due to lift=(Thrust of an aircraft/(Dynamic Pressure*Area))-Zero-lift drag coefficient 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

Coefficient of Drag due to lift for minimum power required Formula

Coefficient of drag due to lift=3*Zero-lift drag coefficient
C<sub>D,i</sub>=3*C<sub>D,0</sub>
More formulas
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
Power required for given total drag GO
Total drag for given required power GO
Freestream Velocity for given total drag GO

What is a lift-induced drag?

In aerodynamics, lift-induced drag, induced drag, vortex drag, or sometimes drag due to lift, is an aerodynamic drag force that occurs whenever a moving object redirects the airflow coming at it.

How to Calculate Coefficient of Drag due to lift for minimum power required?

Coefficient of Drag due to lift for minimum power required calculator uses Coefficient of drag due to lift=3*Zero-lift drag coefficient to calculate the Coefficient of drag due to lift, The Coefficient of Drag due to lift for minimum power required in a steady, level flight is thrice of zero-lift drag coefficient of the aircraft. Coefficient of drag due to lift and is denoted by CD,i symbol.

How to calculate Coefficient of Drag due to lift for minimum power required using this online calculator? To use this online calculator for Coefficient of Drag due to lift for minimum power required, enter Zero-lift drag coefficient (CD,0) and hit the calculate button. Here is how the Coefficient of Drag due to lift for minimum power required calculation can be explained with given input values -> 0.0483 = 3*0.0161.

FAQ

What is Coefficient of Drag due to lift for minimum power required?
The Coefficient of Drag due to lift for minimum power required in a steady, level flight is thrice of zero-lift drag coefficient of the aircraft and is represented as CD,i=3*CD,0 or Coefficient of drag due to lift=3*Zero-lift drag coefficient. The Zero-lift drag coefficient is a dimensionless parameter that relates an aircraft's zero-lift drag force to its size, speed, and flying altitude.
How to calculate Coefficient of Drag due to lift for minimum power required?
The Coefficient of Drag due to lift for minimum power required in a steady, level flight is thrice of zero-lift drag coefficient of the aircraft is calculated using Coefficient of drag due to lift=3*Zero-lift drag coefficient. To calculate Coefficient of Drag due to lift for minimum power required, you need Zero-lift drag coefficient (CD,0). With our tool, you need to enter the respective value for Zero-lift drag coefficient 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 Coefficient of drag due to lift?
In this formula, Coefficient of drag due to lift uses Zero-lift drag coefficient. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Coefficient of drag due to lift=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)
  • Coefficient of drag due to lift=(Thrust of an aircraft/(Dynamic Pressure*Area))-Zero-lift drag coefficient
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