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

Category	Physics ↺
Physics	Flight Stability and Control ↺
Flight-Stability-And-Control	Airplane Performance ↺
Airplane-Performance	Thrust Required for Level Unaccelerated Flight ↺

✖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 [T/W]			+10% -10%

✖The lift coefficient (CL) 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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Vinay Mishra

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

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

Sai Venkata Phanindra Chary Arendra

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

Sai Venkata Phanindra Chary Arendra has verified this Calculator and 100+ more calculators!

< 11 Other formulas that you can solve using the same Inputs

Parasite Drag Coefficient at zero lift

Zero-lift drag coefficient=Drag Coefficient-Coefficient of drag due to lift GO

Power required for given aerodynamic coefficients

Power=Weight*Freestream Velocity*Drag Coefficient/lift coefficient GO

Weight of aircraft for given coefficients of lift and drag

Weight=lift coefficient*Thrust of an aircraft/Drag Coefficient GO

Coefficient of Lift for given thrust and weight

lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft GO

Thrust for given coefficients of lift and drag

Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient GO

Thrust required for level, unaccelerated flight

Thrust of an aircraft=Dynamic Pressure*Area*Drag Coefficient GO

Coefficient of Drag for given thrust-to-weight ratio

Drag Coefficient=lift coefficient*Thrust-to-weight ratio GO

Thrust-to-weight ratio

Thrust-to-weight ratio=Drag Coefficient/lift coefficient GO

Dynamic pressure

Dynamic Pressure=Drag Force/(Drag Coefficient*Area) GO

Drag for a level, unaccelerated flight at negligible thrust angle

Drag Force=Dynamic Pressure*Area*Drag Coefficient GO

Drag force

Drag Force=Drag Coefficient*Dynamic Pressure*Area GO

< 11 Other formulas that calculate the same Output

Lift coefficient for given minimum required thrust

lift coefficient=sqrt(pi*Oswald efficiency factor*Aspect Ratio of a wing*((Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Zero-lift drag coefficient)) GO

Total Lift Coefficient of wing-tail combination

lift coefficient=Wing Lift Coefficient+(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area) GO

Lift Coefficient for a given turn rate

lift coefficient=2*Weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area) GO

Lift Coefficient for a given turn radius

lift coefficient=2*Weight/(Freestream density*Reference Area*[g]*Turn Radius) GO

lift coefficient for lift force in a body moving on a fluid

lift coefficient=Lift force/(Reference Area*0.5*Density*(Velocity^2)) GO

Lift Coefficient for a given wing loading and turn radius

lift coefficient=2*Wing Loading/(Freestream density*Turn Radius*[g]) GO

Lift coefficient for a rotating cylinder with circulation

lift coefficient=Circulation/(Cylinder Radius*Freestream Velocity) GO

Coefficient of lift equation with angle of attack

lift coefficient=2*((sin(Angle of attack))^2)*cos(Angle of attack) GO

Coefficient of Lift for given thrust and weight

lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft GO

Coefficient of lift equation with coefficient of normal force

lift coefficient=coefficient of force*cos(Angle of attack) GO

lift coefficient

lift coefficient=Lift force/(Dynamic Pressure*Area) GO

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

lift coefficient=Drag Coefficient/Thrust-to-weight ratio
C<sub>L</sub>=C<sub>D</sub>/T/W

More formulas

Thrust required for level, unaccelerated flight GO

Lift for a level, unaccelerated flight at negligible thrust angle GO

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

Thrust-to-weight ratio GO

Thrust for given coefficients of lift and drag GO

Weight of aircraft for given coefficients of lift and drag GO

Coefficient of Lift for given thrust and weight GO

Minimum Thrust required GO

Minimum Thrust required for given lift coefficient GO

Lift coefficient for given minimum required thrust GO

Minimum Thrust required for given weight GO

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 given by the coefficient of drag divided by the thrust-to-weight ratio of the aircraft. lift coefficient and 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) and Thrust-to-weight ratio (T/W) 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 -> 1.666667 = 100/60.

FAQ

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

The Coefficient of Lift for given thrust-to-weight ratio is given by the coefficient of drag divided by the thrust-to-weight ratio of the aircraft and is represented as C_L=C_D/T/W 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 and 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 given by the coefficient of drag divided by the thrust-to-weight ratio of the aircraft 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) and Thrust-to-weight ratio (T/W). With our tool, you need to enter the respective value for Drag Coefficient and 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 and Thrust-to-weight ratio. We can use 11 other way(s) to calculate the same, which is/are as follows -

lift coefficient=Lift force/(Dynamic Pressure*Area)
lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft
lift coefficient=sqrt(pi*Oswald efficiency factor*Aspect Ratio of a wing*((Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Zero-lift drag coefficient))
lift coefficient=coefficient of force*cos(Angle of attack)
lift coefficient=2*((sin(Angle of attack))^2)*cos(Angle of attack)
lift coefficient=2*Weight/(Freestream density*Reference Area*[g]*Turn Radius)
lift coefficient=2*Weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area)
lift coefficient=2*Wing Loading/(Freestream density*Turn Radius*[g])
lift coefficient=Wing Lift Coefficient+(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area)
lift coefficient=Lift force/(Reference Area*0.5*Density*(Velocity^2))
lift coefficient=Circulation/(Cylinder Radius*Freestream Velocity)

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