Coefficient of Drag due to lift for minimum power required Solution

STEP 0: Pre-Calculation Summary
Formula Used
Coefficient Of Drag Due to Lift = 3*Zero Lift Drag Coefficient
CD,i = 3*CD,0
This formula uses 2 Variables
Variables Used
Coefficient Of Drag Due to Lift - 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.
Zero Lift Drag Coefficient - Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift.
STEP 1: Convert Input(s) to Base Unit
Zero Lift Drag Coefficient: 0.31 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
CD,i = 3*CD,0 --> 3*0.31
Evaluating ... ...
CD,i = 0.93
STEP 3: Convert Result to Output's Unit
0.93 --> No Conversion Required
FINAL ANSWER
0.93 <-- Coefficient Of Drag Due to Lift
(Calculation completed in 00.004 seconds)

Credits

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

19 Lift and Drag Requirements Calculators

Lift coefficient for given minimum required thrust
Go Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient))
Zero-lift drag coefficient for given lift coefficient
Go Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing))
Zero-lift drag coefficient at minimum required thrust
Go Zero Lift Drag Coefficient = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)
Lift-induced drag coefficient for given required thrust
Go Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient
Zero-lift drag coefficient for given required thrust
Go Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Reference Area))-Coefficient Of Drag Due to Lift
Lift for Unaccelerated Flight
Go Lift Force = Weight of Body-Thrust*sin(Thrust angle)
Coefficient of Drag for given thrust and weight
Go Drag Coefficient = Thrust*Lift Coefficient/Weight of Body
Coefficient of Lift for given thrust and weight
Go Lift Coefficient = Weight of Body*Drag Coefficient/Thrust
Drag for Level and Unaccelerated Flight at Negligible Thrust Angle
Go Drag Force = Dynamic Pressure*Area*Drag Coefficient
Lift for Level and Unaccelerated Flight at Negligible Thrust Angle
Go Lift Force = Dynamic Pressure*Area*Lift Coefficient
Drag for Level and Unaccelerated Flight
Go Drag Force = Thrust*(cos(Thrust angle))
Coefficient of Drag for given thrust-to-weight ratio
Go Drag Coefficient = Lift Coefficient*Thrust-to-Weight Ratio
Coefficient of Lift for given thrust-to-weight ratio
Go Lift Coefficient = Drag Coefficient/Thrust-to-Weight Ratio
Lift-to-drag ratio for given required thrust of aircraft
Go Lift-to-drag Ratio = Weight of Body/Thrust
Freestream Velocity for given total drag force
Go Freestream Velocity = Power/Drag Force
Total drag force for given required power
Go Drag Force = Power/Freestream Velocity
Freestream velocity for given required power
Go Freestream Velocity = Power/Thrust
Coefficient of Drag due to lift for minimum power required
Go Coefficient Of Drag Due to Lift = 3*Zero Lift Drag Coefficient
Zero-lift drag coefficient for minimum power required
Go Zero Lift Drag Coefficient = Coefficient Of Drag Due to Lift/3

Coefficient of Drag due to lift for minimum power required Formula

Coefficient Of Drag Due to Lift = 3*Zero Lift Drag Coefficient
CD,i = 3*CD,0

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 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 -> 0.93 = 3*0.31.

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. Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift.
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 1 other way(s) to calculate the same, which is/are as follows -
  • Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient
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