Zero-lift drag coefficient for given lift coefficient Calculator

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Lift and Drag Requirements

Thrust and Power Requirements

✖The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.ⓘ Thrust [T]			+10% -10%
✖Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.ⓘ Dynamic Pressure [P_dynamic]			+10% -10%
✖The area is the amount of two-dimensional space taken up by an object.ⓘ Area [A]			+10% -10%
✖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.ⓘ Lift Coefficient [C_L]			+10% -10%
✖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.ⓘ Oswald Efficiency Factor [e]			+10% -10%
✖The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.ⓘ Aspect Ratio of a wing [AR]			+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 given lift coefficient [C_D,0]

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Formula

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Zero-lift drag coefficient for given lift coefficient

Formula

`"C"_{"D,0"} = ("T"/("P"_{"dynamic"}*"A"))-(("C"_{"L"}^2)/(pi*"e"*"AR"))`

Example

`"0.311199"=("100N"/("10Pa"*"20m²"))-((("1.1")^2)/(pi*"0.51"*"4"))`

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Zero-lift drag coefficient for given lift coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing))
C_D,0 = (T/(P_dynamic*A))-((C_L^2)/(pi*e*AR))
This formula uses 1 Constants, 7 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.
Thrust - (Measured in Newton) - The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.
Dynamic Pressure - (Measured in Pascal) - Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.
Area - (Measured in Square Meter) - The area is the amount of two-dimensional space taken up by an object.
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

Thrust: 100 Newton --> 100 Newton No Conversion Required
Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
Area: 20 Square Meter --> 20 Square Meter No Conversion Required
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

C_D,0 = (T/(P_dynamic*A))-((C_L^2)/(pi*e*AR)) --> (100/(10*20))-((1.1^2)/(pi*0.51*4))

Evaluating ... ...

C_D,0 = 0.311198547900791

STEP 3: Convert Result to Output's Unit

0.311198547900791 --> No Conversion Required

FINAL ANSWER

0.311198547900791 ≈ 0.311199 <-- Zero Lift Drag Coefficient

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Aircraft Performance » Level Flight » Lift and Drag Requirements » Zero-lift drag coefficient for given lift coefficient

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 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 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

Zero-lift drag coefficient for given lift coefficient Formula

Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing))
C_D,0 = (T/(P_dynamic*A))-((C_L^2)/(pi*e*AR))

How is the reference area chosen?

The reference area is arbitrary in principle. It is chosen as the area that is characteristic of the object considered. As an example, in aircraft aerodynamics, typically the planform area of the wing is chosen as the reference area for both lift and drag coefficients of the wing.

How to Calculate Zero-lift drag coefficient for given lift coefficient?

Zero-lift drag coefficient for given lift coefficient calculator uses Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)) to calculate the Zero Lift Drag Coefficient, The Zero-lift drag coefficient for given lift coefficient for a steady, level flight is a function of required thrust, dynamic pressure, reference area, Oswald efficiency factor, and aspect ratio of the wing of the aircraft. Zero Lift Drag Coefficient is denoted by C_D,0 symbol.

How to calculate Zero-lift drag coefficient for given lift coefficient using this online calculator? To use this online calculator for Zero-lift drag coefficient for given lift coefficient, enter Thrust (T), Dynamic Pressure (P_dynamic), Area (A), Lift Coefficient (C_L), Oswald Efficiency Factor (e) & Aspect Ratio of a wing (AR) and hit the calculate button. Here is how the Zero-lift drag coefficient for given lift coefficient calculation can be explained with given input values -> 0.311199 = (100/(10*20))-((1.1^2)/(pi*0.51*4)).

FAQ

What is Zero-lift drag coefficient for given lift coefficient?

The Zero-lift drag coefficient for given lift coefficient for a steady, level flight is a function of required thrust, dynamic pressure, reference area, Oswald efficiency factor, and aspect ratio of the wing of the aircraft and is represented as C_D,0 = (T/(P_dynamic*A))-((C_L^2)/(pi*e*AR)) or Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)). The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air, Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid, The area is the amount of two-dimensional space taken up by an object, 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 for given lift coefficient?

The Zero-lift drag coefficient for given lift coefficient for a steady, level flight is a function of required thrust, dynamic pressure, reference area, Oswald efficiency factor, and aspect ratio of the wing of the aircraft is calculated using Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)). To calculate Zero-lift drag coefficient for given lift coefficient, you need Thrust (T), Dynamic Pressure (P_dynamic), Area (A), Lift Coefficient (C_L), Oswald Efficiency Factor (e) & Aspect Ratio of a wing (AR). With our tool, you need to enter the respective value for Thrust, Dynamic Pressure, Area, 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 Thrust, Dynamic Pressure, Area, 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 = (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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