Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Shikha Maurya
Indian Institute of Technology (IIT), Bombay
Shikha Maurya has verified this Calculator and 100+ more calculators!

11 Other formulas that you can solve using the same Inputs

Drag Coefficient for given zero-lift drag coefficient
Drag Coefficient=Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Drag Coefficient for given parasite drag coefficient
Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Coefficient of Drag due to lift
Coefficient of drag due to lift=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing) 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-to-weight ratio
Thrust-to-weight ratio=Drag Coefficient/lift coefficient GO
Dynamic pressure based on coefficient of lift
Dynamic Pressure=Lift force/(lift coefficient*Area) GO
Lift for a level, unaccelerated flight at negligible thrust angle
Lift force=Dynamic Pressure*Area*lift coefficient GO
Lift Force
Lift force=lift coefficient*Dynamic Pressure*Area GO
Weight of aircraft for a level, unaccelerated flight at negligible thrust angle
Weight=Dynamic Pressure*Area*lift coefficient GO

5 Other formulas that calculate the same Output

Radius of turn for a given wing loading
Turn Radius=2*Wing Loading/(Freestream density*lift coefficient*[g]) GO
Turn radius
Turn Radius=(Velocity^2)/([g]*sqrt((Load factor^2)-1)) GO
Pull-down maneuver radius
Turn Radius=(Velocity^2)/([g]*(Load factor+1)) GO
Pull-up maneuver radius
Turn Radius=(Velocity^2)/([g]*(Load factor-1)) GO
Turn radius for a high load factor
Turn Radius=(Velocity^2)/([g]*Load factor) GO

Radius of turn for a given lift coefficient Formula

Turn Radius=2*Weight/(Freestream density*Reference Area*[g]*lift coefficient)
R=2*W/(ρ<sub>∞</sub>*S*[g]*C<sub>L</sub>)
More formulas
Turn radius for a high load factor GO
Velocity for a given turn radius for a high load factor GO
Load factor for a given turn radius for a high-performance fighter aircraft GO
Turn rate for a high load factor GO
Velocity for a given turn rate for a high load factor GO
Load factor for a given turn rate for a high-performance fighter aircraft GO
Lift Coefficient for a given turn radius GO
Turn rate for a given lift coefficient GO
Lift Coefficient for a given turn rate GO
Radius of turn for a given wing loading GO
Lift Coefficient for a given wing loading and turn radius GO
Wing loading for a given turn radius GO
Turn rate for a given wing loading GO
Wing loading for a given turn rate GO

What is a wingover?

A wingover is a manoeuvre that provides a fast, 180-degree turn with a minimal turn radius. It consists of a quarter loop into a vertical climb, letting the speed fall as altitude increases, and then a flat-turn over the top, diving to complete a quarter loop at the original altitude, but going in the opposite direction.

How to Calculate Radius of turn for a given lift coefficient?

Radius of turn for a given lift coefficient calculator uses Turn Radius=2*Weight/(Freestream density*Reference Area*[g]*lift coefficient) to calculate the Turn Radius, The Radius of turn for a given lift coefficient of an aircraft is a function of the aircraft's weight and altitude. Turn Radius and is denoted by R symbol.

How to calculate Radius of turn for a given lift coefficient using this online calculator? To use this online calculator for Radius of turn for a given lift coefficient, enter Weight (W), Freestream density ), Reference Area (S) and lift coefficient (CL) and hit the calculate button. Here is how the Radius of turn for a given lift coefficient calculation can be explained with given input values -> 0.332969 = 2*100/(1.225*5*[g]*10).

FAQ

What is Radius of turn for a given lift coefficient?
The Radius of turn for a given lift coefficient of an aircraft is a function of the aircraft's weight and altitude and is represented as R=2*W/(ρ*S*[g]*CL) or Turn Radius=2*Weight/(Freestream density*Reference Area*[g]*lift coefficient). 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 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. .
How to calculate Radius of turn for a given lift coefficient?
The Radius of turn for a given lift coefficient of an aircraft is a function of the aircraft's weight and altitude is calculated using Turn Radius=2*Weight/(Freestream density*Reference Area*[g]*lift coefficient). To calculate Radius of turn for a given lift coefficient, you need Weight (W), Freestream density ), Reference Area (S) and lift coefficient (CL). With our tool, you need to enter the respective value for Weight, Freestream density, Reference Area and 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 Turn Radius?
In this formula, Turn Radius uses Weight, Freestream density, Reference Area and lift coefficient. We can use 5 other way(s) to calculate the same, which is/are as follows -
  • Turn Radius=(Velocity^2)/([g]*sqrt((Load factor^2)-1))
  • Turn Radius=(Velocity^2)/([g]*(Load factor-1))
  • Turn Radius=(Velocity^2)/([g]*(Load factor+1))
  • Turn Radius=(Velocity^2)/([g]*Load factor)
  • Turn Radius=2*Wing Loading/(Freestream density*lift coefficient*[g])
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