Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
Maiarutselvan V has verified this Calculator and 200+ more calculators!

11 Other formulas that you can solve using the same Inputs

Drag in an accelerated flight
Drag Force=(Thrust of an aircraft*cos(Thrust angle))-(Mass*[g]*(sin(Flight path angle)))-(Mass*Acceleration) GO
Parasite Drag Coefficient at zero lift
Zero-lift drag coefficient=Drag Coefficient-Coefficient of drag due to lift GO
Lift for an unaccelerated flight
Lift force=Weight-(Thrust of an aircraft*sin(Thrust angle)) GO
Thrust angle for an unaccelerated flight for given lift
Thrust angle=asin((Weight-Lift force)/Thrust of an aircraft) GO
Thrust required for level, unaccelerated flight
Thrust of an aircraft=Dynamic Pressure*Area*Drag Coefficient GO
Weight of aircraft in level, unaccelerated flight
Weight=Lift force+(Thrust of an aircraft*sin(Thrust angle)) GO
Thrust-to-weight ratio
Thrust-to-weight ratio=Drag Coefficient/lift coefficient GO
Drag for a level, unaccelerated flight
Drag Force=Thrust of an aircraft*(cos(Thrust angle)) 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 equation with coefficient of normal force
lift coefficient=coefficient of force*cos(Angle of attack) GO
Coefficient of Lift for given thrust-to-weight ratio
lift coefficient=Drag Coefficient/Thrust-to-weight ratio GO
lift coefficient
lift coefficient=Lift force/(Dynamic Pressure*Area) GO

Coefficient of Lift for given thrust and weight Formula

lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft
C<sub>L</sub>=W*C<sub>D</sub>/T
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-to-weight ratio 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 vary during a flight?

The thrust-to-weight ratio varies continually during a flight. Thrust varies with throttle setting, airspeed, altitude and air temperature. Weight varies with fuel burn and payload changes.

How to Calculate Coefficient of Lift for given thrust and weight?

Coefficient of Lift for given thrust and weight calculator uses lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft to calculate the lift coefficient, The Coefficient of Lift for given thrust and weight in a steady, level flight is given by weight times coefficient of drag divided by the required thrust of an aircraft. lift coefficient and is denoted by CL symbol.

How to calculate Coefficient of Lift for given thrust and weight using this online calculator? To use this online calculator for Coefficient of Lift for given thrust and weight, enter Weight (W), Drag Coefficient (CD) and Thrust of an aircraft (T) and hit the calculate button. Here is how the Coefficient of Lift for given thrust and weight calculation can be explained with given input values -> 100 = 100*100/100.

FAQ

What is Coefficient of Lift for given thrust and weight?
The Coefficient of Lift for given thrust and weight in a steady, level flight is given by weight times coefficient of drag divided by the required thrust of an aircraft and is represented as CL=W*CD/T or lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft. Weight is a vector quantity and defined as the product of mass and acceleration acting on that mass, 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 The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.
How to calculate Coefficient of Lift for given thrust and weight?
The Coefficient of Lift for given thrust and weight in a steady, level flight is given by weight times coefficient of drag divided by the required thrust of an aircraft is calculated using lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft. To calculate Coefficient of Lift for given thrust and weight, you need Weight (W), Drag Coefficient (CD) and Thrust of an aircraft (T). With our tool, you need to enter the respective value for Weight, Drag Coefficient and Thrust of an aircraft 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 Weight, Drag Coefficient and Thrust of an aircraft. 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=Drag Coefficient/Thrust-to-weight ratio
  • 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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