Zero-lift drag coefficient at minimum required thrust Solution

STEP 0: Pre-Calculation Summary
Formula Used
Zero Lift Drag Coefficient = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)
CD,0 = (CL^2)/(pi*e*AR)
This formula uses 1 Constants, 4 Variables
Constants Used
pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288
Variables Used
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.
Lift Coefficient - The Lift Coefficient 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.
Oswald Efficiency Factor - 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.
Aspect Ratio of a wing - The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.
STEP 1: Convert Input(s) to Base Unit
Lift Coefficient: 1.1 --> No Conversion Required
Oswald Efficiency Factor: 0.51 --> No Conversion Required
Aspect Ratio of a wing: 4 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
CD,0 = (CL^2)/(pi*e*AR) --> (1.1^2)/(pi*0.51*4)
Evaluating ... ...
CD,0 = 0.188801452099209
STEP 3: Convert Result to Output's Unit
0.188801452099209 --> No Conversion Required
FINAL ANSWER
0.188801452099209 0.188801 <-- Zero Lift Drag Coefficient
(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!
Verified by Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
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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

Zero-lift drag coefficient at minimum required thrust Formula

Zero Lift Drag Coefficient = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)
CD,0 = (CL^2)/(pi*e*AR)

What does the Drag Coefficient indicate?

The drag coefficient indicates not only the complex dependencies of object shape and inclination but also the effects of air viscosity and compressibility.

How to Calculate Zero-lift drag coefficient at minimum required thrust?

Zero-lift drag coefficient at minimum required thrust calculator uses Zero Lift Drag Coefficient = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing) to calculate the Zero Lift Drag Coefficient, The Zero-lift drag coefficient at minimum required thrust for steady, level flight condition is equal to the coefficient of drag due to lift (or induced drag). Zero Lift Drag Coefficient is denoted by CD,0 symbol.

How to calculate Zero-lift drag coefficient at minimum required thrust using this online calculator? To use this online calculator for Zero-lift drag coefficient at minimum required thrust, enter Lift Coefficient (CL), Oswald Efficiency Factor (e) & Aspect Ratio of a wing (AR) and hit the calculate button. Here is how the Zero-lift drag coefficient at minimum required thrust calculation can be explained with given input values -> 0.188801 = (1.1^2)/(pi*0.51*4).

FAQ

What is Zero-lift drag coefficient at minimum required thrust?
The Zero-lift drag coefficient at minimum required thrust for steady, level flight condition is equal to the coefficient of drag due to lift (or induced drag) and is represented as CD,0 = (CL^2)/(pi*e*AR) or Zero Lift Drag Coefficient = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing). The Lift Coefficient 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 & The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.
How to calculate Zero-lift drag coefficient at minimum required thrust?
The Zero-lift drag coefficient at minimum required thrust for steady, level flight condition is equal to the coefficient of drag due to lift (or induced drag) is calculated using Zero Lift Drag Coefficient = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing). To calculate Zero-lift drag coefficient at minimum required thrust, you need Lift Coefficient (CL), Oswald Efficiency Factor (e) & Aspect Ratio of a wing (AR). With our tool, you need to enter the respective value for Lift Coefficient, Oswald Efficiency Factor & 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 Zero Lift Drag Coefficient?
In this formula, Zero Lift Drag Coefficient uses Lift Coefficient, Oswald Efficiency Factor & Aspect Ratio of a wing. We can use 3 other way(s) to calculate the same, which is/are as follows -
  • Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Reference Area))-Coefficient Of Drag Due to Lift
  • Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((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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