Zero-Lift Drag Coefficient for Minimum Power required Calculator

✖The Coefficient of Drag Due to Lift represents the contribution of lift-induced drag to the total drag experienced by an aircraft.ⓘ Coefficient Of Drag Due to Lift [C_D,i]

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✖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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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 represents the contribution of lift-induced drag to the total drag experienced by an aircraft.

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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< Lift and Drag Requirements Calculators

Lift for Unaccelerated Flight

LaTeX Go Lift Force = Weight of Body-Thrust*sin(Thrust Angle)

Drag for Level and Unaccelerated Flight at Negligible Thrust Angle

LaTeX Go Drag Force = Dynamic Pressure*Area*Drag Coefficient

Lift for Level and Unaccelerated Flight at Negligible Thrust Angle

LaTeX Go Lift Force = Dynamic Pressure*Area*Lift Coefficient

Drag for Level and Unaccelerated Flight

LaTeX Go Drag Force = Thrust*cos(Thrust Angle)

Zero-Lift Drag Coefficient for Minimum Power required Formula

LaTeX Go

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 typically represents the baseline drag of the aircraft, excluding the effects of lift, therefore, it's often associated with the minimum drag configuration and consequently the minimum power required for level flight. 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 typically represents the baseline drag of the aircraft, excluding the effects of lift, therefore, it's often associated with the minimum drag configuration and consequently the minimum power required for level flight 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 represents the contribution of lift-induced drag to the total drag experienced by an aircraft.

How to calculate Zero-Lift Drag Coefficient for Minimum Power required?

The Zero-Lift Drag Coefficient for Minimum Power required typically represents the baseline drag of the aircraft, excluding the effects of lift, therefore, it's often associated with the minimum drag configuration and consequently the minimum power required for level flight 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 2 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))

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