Thrust-to-weight ratio Calculator

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Thrust and Power Requirements

Lift and Drag Requirements

✖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%
✖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%

✖Thrust-to-weight ratio is a dimensionless ratio of thrust to weight of a rocket, jet engine, propeller engine.ⓘ Thrust-to-weight ratio [TW]

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Formula

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Thrust-to-weight ratio

Formula

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

Example

`"0.454545"="0.5"/"1.1"`

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Thrust-to-weight ratio Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

Thrust-to-Weight Ratio - Thrust-to-weight ratio is a dimensionless ratio of thrust to weight of a rocket, jet engine, propeller engine.
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.
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
Lift Coefficient: 1.1 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

TW = C_D/C_L --> 0.5/1.1

Evaluating ... ...

TW = 0.454545454545455

STEP 3: Convert Result to Output's Unit

0.454545454545455 --> No Conversion Required

FINAL ANSWER

0.454545454545455 ≈ 0.454545 <-- Thrust-to-Weight Ratio

(Calculation completed in 00.004 seconds)

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Credits

Created by Vinay Mishra

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

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has verified this Calculator and 200+ more calculators!

< 19 Thrust and Power Requirements Calculators

Minimum Thrust required for given weight

Go Thrust = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*Area*pi*Oswald Efficiency Factor*Aspect Ratio of a wing))

Minimum Thrust required for given lift coefficient

Go Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)))

Minimum Thrust of aircraft required

Go Thrust = Dynamic Pressure*Reference Area*(Zero Lift Drag Coefficient+Coefficient Of Drag Due to Lift)

Weight of aircraft for given required power

Go Weight of Body = Power*Lift Coefficient/(Freestream Velocity*Drag Coefficient)

Power required for given aerodynamic coefficients

Go Power = Weight of Body*Freestream Velocity*Drag Coefficient/Lift Coefficient

Thrust Angle for Unaccelerated Level Flight for given Lift

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

Weight of aircraft in level, unaccelerated flight

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

Weight of aircraft for given coefficients of lift and drag

Go Weight of Body = Lift Coefficient*Thrust/Drag Coefficient

Thrust for given coefficients of lift and drag

Go Thrust = Drag Coefficient*Weight of Body/Lift Coefficient

Weight of aircraft for level, unaccelerated flight at negligible thrust angle

Go Weight of Body = Dynamic Pressure*Area*Lift Coefficient

Thrust of aircraft required for level, unaccelerated flight

Go Thrust = Dynamic Pressure*Area*Drag Coefficient

Thrust for Level and Unaccelerated Flight

Go Thrust = Drag Force/(cos(Thrust angle))

Thrust Angle for Unaccelerated Level Flight for given Drag

Go Thrust angle = acos(Drag Force/Thrust)

Thrust-to-weight ratio

Go Thrust-to-Weight Ratio = Drag Coefficient/Lift Coefficient

Thrust of aircraft required for given Lift-to-drag ratio

Go Thrust = Weight of Body/Lift-to-drag Ratio

Weight of aircraft for given Lift-to-drag ratio

Go Weight of Body = Thrust*Lift-to-drag Ratio

Power required for given total drag force

Go Power = Drag Force*Freestream Velocity

Power required for given required thrust of aircraft

Go Power = Freestream Velocity*Thrust

Thrust of aircraft required for given required power

Go Thrust = Power/Freestream Velocity

Thrust-to-weight ratio Formula

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

What is a good thrust to weight ratio for rockets?

For rockets, a minimum acceptable Thrust to weight(rocket and installed motors) ratio of 5:1 is typically required.

How to Calculate Thrust-to-weight ratio?

Thrust-to-weight ratio calculator uses Thrust-to-Weight Ratio = Drag Coefficient/Lift Coefficient to calculate the Thrust-to-Weight Ratio, Thrust-to-weight ratio is equal to the ratio of coefficient of drag to coefficient of lift of an aircraft. Thrust-to-Weight Ratio is denoted by TW symbol.

How to calculate Thrust-to-weight ratio using this online calculator? To use this online calculator for Thrust-to-weight ratio, enter Drag Coefficient (C_D) & Lift Coefficient (C_L) and hit the calculate button. Here is how the Thrust-to-weight ratio calculation can be explained with given input values -> 0.454545 = 0.5/1.1.

FAQ

What is Thrust-to-weight ratio?

Thrust-to-weight ratio is equal to the ratio of coefficient of drag to coefficient of lift of an aircraft and is represented as TW = C_D/C_L or Thrust-to-Weight Ratio = Drag Coefficient/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 & 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-to-weight ratio?

Thrust-to-weight ratio is equal to the ratio of coefficient of drag to coefficient of lift of an aircraft is calculated using Thrust-to-Weight Ratio = Drag Coefficient/Lift Coefficient. To calculate Thrust-to-weight ratio, you need Drag Coefficient (C_D) & Lift Coefficient (C_L). With our tool, you need to enter the respective value for Drag Coefficient & Lift Coefficient 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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