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
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

Turn rate for a given lift coefficient
Turn Rate=[g]*(sqrt((Reference Area*Freestream density*lift coefficient*Load factor)/(2*Weight))) GO
Turn rate
Turn Rate=[g]*(sqrt((Load factor^2)-1))/Velocity GO
Pull-down maneuver rate
Turn Rate=[g]*(1+Load factor)/Velocity GO
Pull-up maneuver rate
Turn Rate=[g]*(Load factor-1)/Velocity GO
Turn rate for a high load factor
Turn Rate=[g]*Load factor/Velocity GO

Turn rate for a given wing loading Formula

Turn Rate=[g]*(sqrt(Freestream density*lift coefficient*Load factor/(2*Wing Loading)))
ω=[g]*(sqrt(ρ<sub>∞</sub>*C<sub>L</sub>*n/(2*W<sub>S</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
Radius of turn for a given lift coefficient 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
Wing loading for a given turn rate GO

Can we estimate thrust loading based on wing loading?

Thrust loading and wing loading are one of the crucial parameters of an aircraft design. A designer can find both of them either by estimating thrust loading and then evaluating the wing loading or vice-versa.

How to Calculate Turn rate for a given wing loading?

Turn rate for a given wing loading calculator uses Turn Rate=[g]*(sqrt(Freestream density*lift coefficient*Load factor/(2*Wing Loading))) to calculate the Turn Rate, The Turn rate for a given wing loading depends on the altitude, lift coefficient, load factor and wing loading of the aircraft. Turn Rate and is denoted by ω symbol.

How to calculate Turn rate for a given wing loading using this online calculator? To use this online calculator for Turn rate for a given wing loading, enter Freestream density ), lift coefficient (CL), Load factor (n) and Wing Loading (WS) and hit the calculate button. Here is how the Turn rate for a given wing loading calculation can be explained with given input values -> 681.2429 = [g]*(sqrt(1.225*10*1.2/(2*5))).

FAQ

What is Turn rate for a given wing loading?
The Turn rate for a given wing loading depends on the altitude, lift coefficient, load factor and wing loading of the aircraft and is represented as ω=[g]*(sqrt(ρ*CL*n/(2*WS))) or Turn Rate=[g]*(sqrt(Freestream density*lift coefficient*Load factor/(2*Wing Loading))). Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, 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. , Load factor is the ratio of the aerodynamic force on the aircraft to the gross weight of the aircraft and Wing Loading is the loaded weight of the aircraft divided by the area of the wing.
How to calculate Turn rate for a given wing loading?
The Turn rate for a given wing loading depends on the altitude, lift coefficient, load factor and wing loading of the aircraft is calculated using Turn Rate=[g]*(sqrt(Freestream density*lift coefficient*Load factor/(2*Wing Loading))). To calculate Turn rate for a given wing loading, you need Freestream density ), lift coefficient (CL), Load factor (n) and Wing Loading (WS). With our tool, you need to enter the respective value for Freestream density, lift coefficient, Load factor and Wing Loading 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 Rate?
In this formula, Turn Rate uses Freestream density, lift coefficient, Load factor and Wing Loading. We can use 5 other way(s) to calculate the same, which is/are as follows -
  • Turn Rate=[g]*(sqrt((Load factor^2)-1))/Velocity
  • Turn Rate=[g]*(Load factor-1)/Velocity
  • Turn Rate=[g]*(1+Load factor)/Velocity
  • Turn Rate=[g]*Load factor/Velocity
  • Turn Rate=[g]*(sqrt((Reference Area*Freestream density*lift coefficient*Load factor)/(2*Weight)))
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