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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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 00.020 seconds)

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

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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 at minimum required thrust Formula

LaTeX Go

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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