Thrust for given coefficients of lift and drag 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%
✖Weight of Body is the force acting on the object due to gravity.ⓘ Weight of Body [W_body]			+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.ⓘ Lift Coefficient [C_L]			+10% -10%

✖The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.ⓘ Thrust for given coefficients of lift and drag [T]

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Thrust for given coefficients of lift and drag Solution

STEP 0: Pre-Calculation Summary

Formula Used

Thrust = Drag Coefficient*Weight of Body/Lift Coefficient
T = C_D*W_body/C_L
This formula uses 4 Variables

Variables Used

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.
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.
Weight of Body - (Measured in Newton) - Weight of Body is the force acting on the object due to gravity.
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.

STEP 1: Convert Input(s) to Base Unit

Drag Coefficient: 0.5 --> No Conversion Required
Weight of Body: 221 Newton --> 221 Newton No Conversion Required
Lift Coefficient: 1.1 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

T = C_D*W_body/C_L --> 0.5*221/1.1

Evaluating ... ...

T = 100.454545454545

STEP 3: Convert Result to Output's Unit

100.454545454545 Newton --> No Conversion Required

FINAL ANSWER

100.454545454545 ≈ 100.4545 Newton <-- 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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< Thrust and Power Requirements Calculators

Thrust Angle for Unaccelerated Level Flight for given Lift

LaTeX Go Thrust Angle = asin((Weight of Body-Lift Force)/Thrust)

Weight of Aircraft in Level, Unaccelerated Flight

LaTeX Go Weight of Body = Lift Force+(Thrust*sin(Thrust Angle))

Thrust for Level and Unaccelerated Flight

LaTeX Go Thrust = Drag Force/(cos(Thrust Angle))

Thrust Angle for Unaccelerated Level Flight for given Drag

LaTeX Go Thrust Angle = acos(Drag Force/Thrust)

Thrust for given coefficients of lift and drag Formula

LaTeX Go

Thrust = Drag Coefficient*Weight of Body/Lift Coefficient
T = C_D*W_body/C_L

What are the parameters in determining the performance of an aircraft?

The thrust-to-weight ratio and wing loading are the two most important parameters in determining the performance of an aircraft.

How to Calculate Thrust for given coefficients of lift and drag?

Thrust for given coefficients of lift and drag calculator uses Thrust = Drag Coefficient*Weight of Body/Lift Coefficient to calculate the Thrust, The Thrust for given coefficients of lift and drag is the amount of propulsive force needed to maintain level flight while producing the specified lift and overcoming aerodynamic drag, in level flight, the thrust required is equal to the drag experienced by the aircraft, the drag force is determined by the aerodynamic coefficients of lift and drag, as well as other factors such as air density, velocity, and reference area. Thrust is denoted by T symbol.

How to calculate Thrust for given coefficients of lift and drag using this online calculator? To use this online calculator for Thrust for given coefficients of lift and drag, enter Drag Coefficient (C_D), Weight of Body (W_body) & Lift Coefficient (C_L) and hit the calculate button. Here is how the Thrust for given coefficients of lift and drag calculation can be explained with given input values -> 6027.273 = 0.5*221/1.1.

FAQ

What is Thrust for given coefficients of lift and drag?

The Thrust for given coefficients of lift and drag is the amount of propulsive force needed to maintain level flight while producing the specified lift and overcoming aerodynamic drag, in level flight, the thrust required is equal to the drag experienced by the aircraft, the drag force is determined by the aerodynamic coefficients of lift and drag, as well as other factors such as air density, velocity, and reference area and is represented as T = C_D*W_body/C_L or Thrust = Drag Coefficient*Weight of Body/Lift 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, Weight of Body is the force acting on the object due to gravity & 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.

How to calculate Thrust for given coefficients of lift and drag?

The Thrust for given coefficients of lift and drag is the amount of propulsive force needed to maintain level flight while producing the specified lift and overcoming aerodynamic drag, in level flight, the thrust required is equal to the drag experienced by the aircraft, the drag force is determined by the aerodynamic coefficients of lift and drag, as well as other factors such as air density, velocity, and reference area is calculated using Thrust = Drag Coefficient*Weight of Body/Lift Coefficient. To calculate Thrust for given coefficients of lift and drag, you need Drag Coefficient (C_D), Weight of Body (W_body) & Lift Coefficient (C_L). With our tool, you need to enter the respective value for Drag Coefficient, Weight of Body & Lift 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 Thrust?

In this formula, Thrust uses Drag Coefficient, Weight of Body & Lift Coefficient. We can use 3 other way(s) to calculate the same, which is/are as follows -

Thrust = Drag Force/(cos(Thrust Angle))
Thrust = Dynamic Pressure*Area*Drag Coefficient
Thrust = Weight of Body/Lift-to-Drag Ratio

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