Lift-induced drag coefficient for given required thrust 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 Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+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 [C_D,0]			+10% -10%

✖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.ⓘ Lift-induced drag coefficient for given required thrust [C_D,i]

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Formula

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Lift-induced drag coefficient for given required thrust

Formula

`"C"_{"D,i"} = ("T"/("P"_{"dynamic"}*"S"))-"C"_{"D,0"}`

Example

`"0.94"=("100N"/("10Pa"*"8m²"))-"0.31"`

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Lift-induced drag coefficient for given required thrust Solution

STEP 0: Pre-Calculation Summary

Formula Used

Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient
C_D,i = (T/(P_dynamic*S))-C_D,0
This formula uses 5 Variables

Variables Used

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.
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.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
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.

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
Reference Area: 8 Square Meter --> 8 Square Meter No Conversion Required
Zero Lift Drag Coefficient: 0.31 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_D,i = (T/(P_dynamic*S))-C_D,0 --> (100/(10*8))-0.31

Evaluating ... ...

C_D,i = 0.94

STEP 3: Convert Result to Output's Unit

0.94 --> No Conversion Required

FINAL ANSWER

0.94 <-- Coefficient Of Drag Due to Lift

(Calculation completed in 00.009 seconds)

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

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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

Lift-induced drag coefficient for given required thrust Formula

Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient
C_D,i = (T/(P_dynamic*S))-C_D,0

How to obtain total drag for an aircraft?

Induced drag (also called drag due to lift) must be added to the parasitic drag to find the total drag on an aircraft

How to Calculate Lift-induced drag coefficient for given required thrust?

Lift-induced drag coefficient for given required thrust calculator uses Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient to calculate the Coefficient Of Drag Due to Lift, The Lift-induced drag coefficient for given required thrust in a steady, level flight depends upon the zero-lift drag coefficient of an aircraft. Coefficient Of Drag Due to Lift is denoted by C_D,i symbol.

How to calculate Lift-induced drag coefficient for given required thrust using this online calculator? To use this online calculator for Lift-induced drag coefficient for given required thrust, enter Thrust (T), Dynamic Pressure (P_dynamic), Reference Area (S) & Zero Lift Drag Coefficient (C_D,0) and hit the calculate button. Here is how the Lift-induced drag coefficient for given required thrust calculation can be explained with given input values -> 0.94 = (100/(10*8))-0.31.

FAQ

What is Lift-induced drag coefficient for given required thrust?

The Lift-induced drag coefficient for given required thrust in a steady, level flight depends upon the zero-lift drag coefficient of an aircraft and is represented as C_D,i = (T/(P_dynamic*S))-C_D,0 or Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient. 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 Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area & Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift.

How to calculate Lift-induced drag coefficient for given required thrust?

The Lift-induced drag coefficient for given required thrust in a steady, level flight depends upon the zero-lift drag coefficient of an aircraft is calculated using Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient. To calculate Lift-induced drag coefficient for given required thrust, you need Thrust (T), Dynamic Pressure (P_dynamic), Reference Area (S) & Zero Lift Drag Coefficient (C_D,0). With our tool, you need to enter the respective value for Thrust, Dynamic Pressure, Reference Area & Zero Lift Drag Coefficient 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 Coefficient Of Drag Due to Lift?

In this formula, Coefficient Of Drag Due to Lift uses Thrust, Dynamic Pressure, Reference Area & Zero Lift Drag Coefficient. We can use 1 other way(s) to calculate the same, which is/are as follows -

Coefficient Of Drag Due to Lift = 3*Zero Lift Drag Coefficient

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