Zero-lift drag coefficient at minimum required thrust Calculator

✖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%

✖The Zero-Lift Drag Coefficient at Minimum Thrust represents the drag coefficient of an aircraft when it is producing zero lift and operating at the minimum thrust required for level flight.ⓘ Zero-lift drag coefficient at minimum required thrust [C_D0,min]

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Formula

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Zero-lift drag coefficient at minimum required thrust

Formula

`"C"_{"D0,min"} = ("C"_{"L"}^2)/(pi*"e"*"AR")`

Example

`"0.188801"=(("1.1")^2)/(pi*"0.51"*"4")`

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Zero-lift drag coefficient at minimum required thrust Solution

STEP 0: Pre-Calculation Summary

Formula Used

Zero-Lift Drag Coefficient at Minimum Thrust = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)
C_D0,min = (C_L^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 at Minimum Thrust - The Zero-Lift Drag Coefficient at Minimum Thrust represents the drag coefficient of an aircraft when it is producing zero lift and operating at the minimum thrust required for level flight.
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

C_D0,min = (C_L^2)/(pi*e*AR) --> (1.1^2)/(pi*0.51*4)

Evaluating ... ...

C_D0,min = 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 at Minimum Thrust

(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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PSG College of Technology (PSGCT), Coimbatore

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< 19 Lift and Drag Requirements Calculators

Lift Coefficient 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 at Minimum Thrust = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)

Lift-Induced Drag Coefficient given required Thrust

Go Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient

Zero-Lift Drag Coefficient 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 given required Thrust of Aircraft

Go Lift-to-Drag Ratio = Weight of Body/Thrust

Freestream Velocity given Total Drag Force

Go Freestream Velocity = Power/Drag Force

Total Drag Force given required Power

Go Drag Force = Power/Freestream Velocity

Freestream Velocity 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 at Minimum Thrust = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)
C_D0,min = (C_L^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 at Minimum Thrust = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing) to calculate the Zero-Lift Drag Coefficient at Minimum Thrust, The Zero-lift drag coefficient at minimum required thrust refers to a specific aerodynamic parameter of an aircraft, it represents the drag force produced by an aircraft when it generates zero lift and is typically measured at a specific condition such as zero angle of attack, the minimum required thrust refers to the lowest amount of engine thrust necessary to maintain level flight at a certain speed. Zero-Lift Drag Coefficient at Minimum Thrust is denoted by C_D0,min 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 (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 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 refers to a specific aerodynamic parameter of an aircraft, it represents the drag force produced by an aircraft when it generates zero lift and is typically measured at a specific condition such as zero angle of attack, the minimum required thrust refers to the lowest amount of engine thrust necessary to maintain level flight at a certain speed and is represented as C_D0,min = (C_L^2)/(pi*e*AR) or Zero-Lift Drag Coefficient at Minimum Thrust = (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 refers to a specific aerodynamic parameter of an aircraft, it represents the drag force produced by an aircraft when it generates zero lift and is typically measured at a specific condition such as zero angle of attack, the minimum required thrust refers to the lowest amount of engine thrust necessary to maintain level flight at a certain speed is calculated using Zero-Lift Drag Coefficient at Minimum Thrust = (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 (C_L), 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.

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