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

Minimum Thrust required for given weight
Thrust of an aircraft=(Dynamic Pressure*Reference Area*Zero-lift drag coefficient)+((Weight^2)/(Dynamic Pressure*Reference Area*pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
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
Zero-lift drag coefficient for given required thrust
Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Coefficient of drag due to lift GO
Power required for given aerodynamic coefficients
Power=Weight*Freestream Velocity*Drag Coefficient/lift coefficient GO
Coefficient of Drag for given thrust and weight
Drag Coefficient=Thrust of an aircraft*lift coefficient/Weight 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
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 given Lift-to-drag ratio
Thrust of an aircraft=Weight/Lift-to-drag ratio GO
Lift-to-drag ratio for given required thrust
Lift-to-drag ratio=Weight/Thrust of an aircraft GO

1 Other formulas that calculate the same Output

Maximum Lift coefficient for given liftoff velocity
Maximum Lift Coefficient=2.88*Weight/(Freestream density*Reference Area*(Liftoff velocity^2)) GO

Maximum Lift coefficient for given stall velocity Formula

Maximum Lift Coefficient=2*Weight/(Freestream density*Reference Area*(Stall Velocity^2))
C<sub>L,max</sub>=2*W/(ρ<sub>∞</sub>*S*(V<sub>stall</sub>^2))
More formulas
Resistance force during ground roll GO
Coefficient of rolling friction during ground roll GO
Weight of aircraft during ground roll GO
Lift acting on aircraft during ground roll GO
Ground effect factor GO
Drag during ground effect GO
Liftoff velocity for given stall velocity GO
Stall velocity for given liftoff velocity GO
Liftoff velocity for given weight GO
Stall velocity for given weight GO
Maximum Lift coefficient for given liftoff velocity GO
Liftoff distance GO
Thrust for given liftoff distance GO

Does air density affect lift?

Lift and drag depend linearly on the density of the fluid. Halving the density halves the lift, halving the density halves the drag.

How to Calculate Maximum Lift coefficient for given stall velocity?

Maximum Lift coefficient for given stall velocity calculator uses Maximum Lift Coefficient=2*Weight/(Freestream density*Reference Area*(Stall Velocity^2)) to calculate the Maximum Lift Coefficient, The Maximum Lift coefficient for given stall velocity of an aircraft depends upon the instantaneous weight and altitude of the aircraft. Maximum Lift Coefficient and is denoted by CL,max symbol.

How to calculate Maximum Lift coefficient for given stall velocity using this online calculator? To use this online calculator for Maximum Lift coefficient for given stall velocity, enter Weight (W), Freestream density ), Reference Area (S) and Stall Velocity (Vstall) and hit the calculate button. Here is how the Maximum Lift coefficient for given stall velocity calculation can be explained with given input values -> 0.003265 = 2*100/(1.225*5*(100^2)).

FAQ

What is Maximum Lift coefficient for given stall velocity?
The Maximum Lift coefficient for given stall velocity of an aircraft depends upon the instantaneous weight and altitude of the aircraft and is represented as CL,max=2*W/(ρ*S*(Vstall^2)) or Maximum Lift Coefficient=2*Weight/(Freestream density*Reference Area*(Stall Velocity^2)). Weight is a vector quantity and defined as the product of mass and acceleration acting on that mass, Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area and Stall Velocity is defined as the velocity of an airplane in steady flight at its maximum lift coefficient.
How to calculate Maximum Lift coefficient for given stall velocity?
The Maximum Lift coefficient for given stall velocity of an aircraft depends upon the instantaneous weight and altitude of the aircraft is calculated using Maximum Lift Coefficient=2*Weight/(Freestream density*Reference Area*(Stall Velocity^2)). To calculate Maximum Lift coefficient for given stall velocity, you need Weight (W), Freestream density ), Reference Area (S) and Stall Velocity (Vstall). With our tool, you need to enter the respective value for Weight, Freestream density, Reference Area and Stall Velocity 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 Maximum Lift Coefficient?
In this formula, Maximum Lift Coefficient uses Weight, Freestream density, Reference Area and Stall Velocity. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Maximum Lift Coefficient=2.88*Weight/(Freestream density*Reference Area*(Liftoff velocity^2))
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