Coefficient of Lift for given thrust-to-weight ratio Calculator

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Lift and Drag Requirements

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✖Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.ⓘ Drag Coefficient [C_D]			+10% -10%
✖Thrust-to-weight ratio is a dimensionless ratio of thrust to weight of a rocket, jet engine, propeller engine.ⓘ Thrust-to-Weight Ratio [TW]			+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.ⓘ Coefficient of Lift for given thrust-to-weight ratio [C_L]

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Coefficient of Lift for given thrust-to-weight ratio

Formula

`"C"_{"L"} = "C"_{"D"}/"TW"`

Example

`"1.111111"="0.5"/"0.45"`

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Coefficient of Lift for given thrust-to-weight ratio Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift Coefficient = Drag Coefficient/Thrust-to-Weight Ratio
C_L = C_D/TW
This formula uses 3 Variables

Variables Used

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.
Drag Coefficient - Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.
Thrust-to-Weight Ratio - Thrust-to-weight ratio is a dimensionless ratio of thrust to weight of a rocket, jet engine, propeller engine.

STEP 1: Convert Input(s) to Base Unit

Drag Coefficient: 0.5 --> No Conversion Required
Thrust-to-Weight Ratio: 0.45 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_L = C_D/TW --> 0.5/0.45

Evaluating ... ...

C_L = 1.11111111111111

STEP 3: Convert Result to Output's Unit

1.11111111111111 --> No Conversion Required

FINAL ANSWER

1.11111111111111 ≈ 1.111111 <-- Lift 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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< 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

Coefficient of Lift for given thrust-to-weight ratio Formula

Lift Coefficient = Drag Coefficient/Thrust-to-Weight Ratio
C_L = C_D/TW

How does the thrust-to-weight ratio of rocket engines vary from that of jet engines?

The thrust-to-weight ratio of rockets typically greatly exceeds that of airbreathing jet engines because the comparatively far greater density of rocket fuel eliminates the need for much engineering materials to pressurize it.

How to Calculate Coefficient of Lift for given thrust-to-weight ratio?

Coefficient of Lift for given thrust-to-weight ratio calculator uses Lift Coefficient = Drag Coefficient/Thrust-to-Weight Ratio to calculate the Lift Coefficient, The Coefficient of Lift for given thrust-to-weight ratio is a number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and some flow conditions on the lift. Lift Coefficient is denoted by C_L symbol.

How to calculate Coefficient of Lift for given thrust-to-weight ratio using this online calculator? To use this online calculator for Coefficient of Lift for given thrust-to-weight ratio, enter Drag Coefficient (C_D) & Thrust-to-Weight Ratio (TW) and hit the calculate button. Here is how the Coefficient of Lift for given thrust-to-weight ratio calculation can be explained with given input values -> 0.008333 = 0.5/0.45.

FAQ

What is Coefficient of Lift for given thrust-to-weight ratio?

The Coefficient of Lift for given thrust-to-weight ratio is a number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and some flow conditions on the lift and is represented as C_L = C_D/TW or Lift Coefficient = Drag Coefficient/Thrust-to-Weight Ratio. Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water & Thrust-to-weight ratio is a dimensionless ratio of thrust to weight of a rocket, jet engine, propeller engine.

How to calculate Coefficient of Lift for given thrust-to-weight ratio?

The Coefficient of Lift for given thrust-to-weight ratio is a number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and some flow conditions on the lift is calculated using Lift Coefficient = Drag Coefficient/Thrust-to-Weight Ratio. To calculate Coefficient of Lift for given thrust-to-weight ratio, you need Drag Coefficient (C_D) & Thrust-to-Weight Ratio (TW). With our tool, you need to enter the respective value for Drag Coefficient & Thrust-to-Weight Ratio 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 Lift Coefficient?

In this formula, Lift Coefficient uses Drag Coefficient & Thrust-to-Weight Ratio. We can use 2 other way(s) to calculate the same, which is/are as follows -

Lift Coefficient = Weight of Body*Drag Coefficient/Thrust
Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient))

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