Coefficient of Lift for given Thrust-to-Weight Ratio Calculator

✖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 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 00.020 seconds)

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Created by Vinay Mishra

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

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Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad

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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)

Coefficient of Lift for given Thrust-to-Weight Ratio Formula

LaTeX Go

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 suggests that the lift coefficient is inversely proportional to the thrust-to-weight ratio and directly proportional to the drag coefficient, this implies that as the thrust-to-weight ratio decreases, the lift coefficient increases to compensate, and vice versa, this equation represents a balance between aerodynamic forces (lift and drag) and propulsive forces (thrust) to maintain stable flight conditions. 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 suggests that the lift coefficient is inversely proportional to the thrust-to-weight ratio and directly proportional to the drag coefficient, this implies that as the thrust-to-weight ratio decreases, the lift coefficient increases to compensate, and vice versa, this equation represents a balance between aerodynamic forces (lift and drag) and propulsive forces (thrust) to maintain stable flight conditions 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 suggests that the lift coefficient is inversely proportional to the thrust-to-weight ratio and directly proportional to the drag coefficient, this implies that as the thrust-to-weight ratio decreases, the lift coefficient increases to compensate, and vice versa, this equation represents a balance between aerodynamic forces (lift and drag) and propulsive forces (thrust) to maintain stable flight conditions 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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