Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 200+ 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 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

3 Other formulas that calculate the same Output

Turn rate for a given wing loading
Turn Rate=[g]*(sqrt(Freestream density*lift coefficient*Load factor/(2*Wing Loading))) GO
Turn rate
Turn Rate=[g]*(sqrt((Load factor^2)-1))/Velocity GO
Pull-up maneuver rate
Turn Rate=[g]*(Load factor-1)/Velocity GO

Turn rate for a given lift coefficient Formula

Turn Rate=[g]*(sqrt((Reference Area*Freestream density*lift coefficient*Load factor)/(2*Weight)))
ω=[g]*(sqrt((S*ρ<sub>∞</sub>*C<sub>L</sub>*n)/(2*W)))
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
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

What are the three axes of rotation of an aircraft?

An aeroplane has three axes of rotation: Pitch, Yaw and Roll. Coordinated flight requires the pilot to use pitch, roll and yaw control simultaneously.

How to Calculate Turn rate for a given lift coefficient?

Turn rate for a given lift coefficient calculator uses Turn Rate=[g]*(sqrt((Reference Area*Freestream density*lift coefficient*Load factor)/(2*Weight))) to calculate the Turn Rate, The Turn rate for a given lift coefficient of an aircraft depends upon the altitude, load factor and weight of the aircraft. Turn Rate and is denoted by ω symbol.

How to calculate Turn rate for a given lift coefficient using this online calculator? To use this online calculator for Turn rate for a given lift coefficient, enter Reference Area (S), Freestream density ), lift coefficient (CL), Load factor (n) and Weight (W) and hit the calculate button. Here is how the Turn rate for a given lift coefficient calculation can be explained with given input values -> 340.6214 = [g]*(sqrt((5*1.225*10*1.2)/(2*100))).

FAQ

What is Turn rate for a given lift coefficient?
The Turn rate for a given lift coefficient of an aircraft depends upon the altitude, load factor and weight of the aircraft and is represented as ω=[g]*(sqrt((S*ρ*CL*n)/(2*W))) or Turn Rate=[g]*(sqrt((Reference Area*Freestream density*lift coefficient*Load factor)/(2*Weight))). 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, 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 Weight is a vector quantity and defined as the product of mass and acceleration acting on that mass.
How to calculate Turn rate for a given lift coefficient?
The Turn rate for a given lift coefficient of an aircraft depends upon the altitude, load factor and weight of the aircraft is calculated using Turn Rate=[g]*(sqrt((Reference Area*Freestream density*lift coefficient*Load factor)/(2*Weight))). To calculate Turn rate for a given lift coefficient, you need Reference Area (S), Freestream density ), lift coefficient (CL), Load factor (n) and Weight (W). With our tool, you need to enter the respective value for Reference Area, Freestream density, lift coefficient, Load factor and Weight 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 Reference Area, Freestream density, lift coefficient, Load factor and Weight. We can use 3 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]*(sqrt(Freestream density*lift coefficient*Load factor/(2*Wing Loading)))
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