Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 200+ 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
Weight of aircraft for given coefficients of lift and drag
Weight=lift coefficient*Thrust of an aircraft/Drag Coefficient GO
Thrust for given coefficients of lift and drag
Thrust of an aircraft=Drag Coefficient*Weight/lift 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 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 lift coefficient
Turn Radius=2*Weight/(Freestream density*Reference Area*[g]*lift coefficient) 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 wing loading Formula

Turn Radius=2*Wing Loading/(Freestream density*lift coefficient*[g])
R=2*W<sub>S</sub>/(ρ<sub>∞</sub>*C<sub>L</sub>*[g])
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
Load factor for a given turn rate for a high-performance fighter aircraft GO
Radius of turn for a given lift coefficient GO
Turn rate for a given lift coefficient GO
Lift Coefficient for a given turn rate 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

How do you calculate wing area?

In aerodynamics, the surface area of a wing is calculated by looking at the wing from a top-down view and measuring the wing area. This surface area is also known as the planform area. The planform area is a significant value when calculating the performance of an aeroplane.

How to Calculate Radius of turn for a given wing loading?

Radius of turn for a given wing loading calculator uses Turn Radius=2*Wing Loading/(Freestream density*lift coefficient*[g]) to calculate the Turn Radius, The Radius of turn for a given wing loading depends upon the altitude, lift coefficient and wing loading of the aircraft. Turn Radius and is denoted by R symbol.

How to calculate Radius of turn for a given wing loading using this online calculator? To use this online calculator for Radius of turn for a given wing loading, enter Wing Loading (WS), Freestream density ) and lift coefficient (CL) and hit the calculate button. Here is how the Radius of turn for a given wing loading calculation can be explained with given input values -> 0.083242 = 2*5/(1.225*10*[g]).

FAQ

What is Radius of turn for a given wing loading?
The Radius of turn for a given wing loading depends upon the altitude, lift coefficient and wing loading of the aircraft and is represented as R=2*WS/(ρ*CL*[g]) or Turn Radius=2*Wing Loading/(Freestream density*lift coefficient*[g]). Wing Loading is the loaded weight of the aircraft divided by the area of the wing, Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude 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 wing loading?
The Radius of turn for a given wing loading depends upon the altitude, lift coefficient and wing loading of the aircraft is calculated using Turn Radius=2*Wing Loading/(Freestream density*lift coefficient*[g]). To calculate Radius of turn for a given wing loading, you need Wing Loading (WS), Freestream density ) and lift coefficient (CL). With our tool, you need to enter the respective value for Wing Loading, Freestream density 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 Wing Loading, Freestream density 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*Weight/(Freestream density*Reference Area*[g]*lift coefficient)
Share Image
Let Others Know
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!