Zero-lift drag coefficient for minimum power required Calculator

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Lift and Drag Requirements

Thrust and Power Requirements

✖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.ⓘ Coefficient Of Drag Due to Lift [C_D,i]

+10%

-10%

✖Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift.ⓘ Zero-lift drag coefficient for minimum power required [C_D,0]

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Formula

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Zero-lift drag coefficient for minimum power required

Formula

`"C"_{"D,0"} = "C"_{"D,i"}/3`

Example

`"0.31"="0.93"/3`

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Zero-lift drag coefficient for minimum power required Solution

STEP 0: Pre-Calculation Summary

Formula Used

Zero Lift Drag Coefficient = Coefficient Of Drag Due to Lift/3
C_D,0 = C_D,i/3
This formula uses 2 Variables

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.
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.

STEP 1: Convert Input(s) to Base Unit

Coefficient Of Drag Due to Lift: 0.93 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_D,0 = C_D,i/3 --> 0.93/3

Evaluating ... ...

C_D,0 = 0.31

STEP 3: Convert Result to Output's Unit

0.31 --> No Conversion Required

FINAL ANSWER

0.31 <-- Zero Lift Drag Coefficient

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

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Verified by Sai Venkata Phanindra Chary Arendra

Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad

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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 for minimum power required Formula

Zero Lift Drag Coefficient = Coefficient Of Drag Due to Lift/3
C_D,0 = C_D,i/3

What does the zero-lift drag coefficient indicate?

The value of the zero-lift drag coefficient is often used as an indicator of the aerodynamic cleanness or refinement of an aircraft.

How to Calculate Zero-lift drag coefficient for minimum power required?

Zero-lift drag coefficient for minimum power required calculator uses Zero Lift Drag Coefficient = Coefficient Of Drag Due to Lift/3 to calculate the Zero Lift Drag Coefficient, The Zero-lift drag coefficient for minimum power required in steady, level flight is one-third of the coefficient of drag due to lift. Zero Lift Drag Coefficient is denoted by C_D,0 symbol.

How to calculate Zero-lift drag coefficient for minimum power required using this online calculator? To use this online calculator for Zero-lift drag coefficient for minimum power required, enter Coefficient Of Drag Due to Lift (C_D,i) and hit the calculate button. Here is how the Zero-lift drag coefficient for minimum power required calculation can be explained with given input values -> 0.188 = 0.93/3.

FAQ

What is Zero-lift drag coefficient for minimum power required?

The Zero-lift drag coefficient for minimum power required in steady, level flight is one-third of the coefficient of drag due to lift and is represented as C_D,0 = C_D,i/3 or Zero Lift Drag Coefficient = Coefficient Of Drag Due to Lift/3. 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 Zero-lift drag coefficient for minimum power required?

The Zero-lift drag coefficient for minimum power required in steady, level flight is one-third of the coefficient of drag due to lift is calculated using Zero Lift Drag Coefficient = Coefficient Of Drag Due to Lift/3. To calculate Zero-lift drag coefficient for minimum power required, you need Coefficient Of Drag Due to Lift (C_D,i). With our tool, you need to enter the respective value for 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 Coefficient Of Drag Due to Lift. 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 = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)

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