Radius of turn for given lift coefficient Solution

STEP 0: Pre-Calculation Summary
Formula Used
Turn Radius = 2*Aircraft weight/(Freestream density*Reference Area*[g]*Lift Coefficient)
R = 2*W/(ฯโˆž*S*[g]*CL)
This formula uses 1 Constants, 5 Variables
Constants Used
[g] - Gravitational acceleration on Earth Value Taken As 9.80665
Variables Used
Turn Radius - (Measured in Meter) - Turn Radius is the radius of the flight path causing the airplane to turn in a circular path.
Aircraft weight - (Measured in Newton) - Aircraft weight is the total aircraft weight at any moment during the flight or ground operation.
Freestream density - (Measured in Kilogram per Cubic Meter) - Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.
Reference Area - (Measured in Square Meter) - 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.
Lift Coefficient - The Lift Coefficient 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.
STEP 1: Convert Input(s) to Base Unit
Aircraft weight: 1800 Newton --> 1800 Newton No Conversion Required
Freestream density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Lift Coefficient: 0.002 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
R = 2*W/(ฯโˆž*S*[g]*CL) --> 2*1800/(1.225*5.08*[g]*0.002)
Evaluating ... ...
R = 29495.2463982046
STEP 3: Convert Result to Output's Unit
29495.2463982046 Meter --> No Conversion Required
FINAL ANSWER
29495.2463982046 โ‰ˆ 29495.25 Meter <-- Turn Radius
(Calculation completed in 00.004 seconds)

Credits

Created by Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
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25 High Load Factor Maneuver Calculators

Turn rate for given lift coefficient
Go Turn Rate = [g]*(sqrt((Reference Area*Freestream density*Lift Coefficient*Load factor)/(2*Aircraft weight)))
Turn rate for given wing loading
Go Turn Rate = [g]*(sqrt(Freestream density*Lift Coefficient*Load factor/(2*Wing Loading)))
Lift Coefficient for given turn rate
Go Lift Coefficient = 2*Aircraft weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area)
Lift Coefficient for given Turn Radius
Go Lift Coefficient = Aircraft weight/(0.5*Freestream density*Reference Area*[g]*Turn Radius)
Radius of turn for given lift coefficient
Go Turn Radius = 2*Aircraft weight/(Freestream density*Reference Area*[g]*Lift Coefficient)
Wing loading for given turn rate
Go Wing Loading = ([g]^2)*Freestream density*Lift Coefficient*Load factor/(2*(Turn Rate^2))
Lift Coefficient for given wing loading and turn radius
Go Lift Coefficient = 2*Wing Loading/(Freestream density*Turn Radius*[g])
Radius of turn for given wing loading
Go Turn Radius = 2*Wing Loading/(Freestream density*Lift Coefficient*[g])
Wing loading for given turn radius
Go Wing Loading = (Turn Radius*Freestream density*Lift Coefficient*[g])/2
Velocity for given pull-up maneuver radius
Go Velocity = sqrt(Turn Radius*[g]*(Load factor-1))
Velocity given Pull-down Maneuver Radius
Go Velocity = sqrt(Turn Radius*[g]*(Load factor+1))
Velocity given Turn Radius for High Load Factor
Go Velocity = sqrt(Turn Radius*Load factor*[g])
Change in Angle of Attack due to Upward Gust
Go Change in Angle of Attack = tan(Gust Velocity/Flight Velocity)
Load Factor given Pull-down Maneuver Radius
Go Load factor = ((Velocity^2)/(Turn Radius*[g]))-1
Load Factor given Pull-UP Maneuver Radius
Go Load factor = 1+((Velocity^2)/(Turn Radius*[g]))
Pull-down maneuver radius
Go Turn Radius = (Velocity^2)/([g]*(Load factor+1))
Pull-up maneuver radius
Go Turn Radius = (Velocity^2)/([g]*(Load factor-1))
Load factor for given turn radius for high-performance fighter aircraft
Go Load factor = (Velocity^2)/([g]*Turn Radius)
Turn radius for high load factor
Go Turn Radius = (Velocity^2)/([g]*Load factor)
Velocity for given pull-up maneuver rate
Go Velocity = [g]*(Load factor-1)/Turn Rate
Load Factor given Pull-Up Maneuver Rate
Go Load factor = 1+(Velocity*Turn Rate/[g])
Pull-down maneuver rate
Go Turn Rate = [g]*(1+Load factor)/Velocity
Pull-up maneuver rate
Go Turn Rate = [g]*(Load factor-1)/Velocity
Load factor for given turn rate for high-performance fighter aircraft
Go Load factor = Velocity*Turn Rate/[g]
Turn rate for high load factor
Go Turn Rate = [g]*Load factor/Velocity

Radius of turn for given lift coefficient Formula

Turn Radius = 2*Aircraft weight/(Freestream density*Reference Area*[g]*Lift Coefficient)
R = 2*W/(ฯโˆž*S*[g]*CL)

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 given lift coefficient?

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

How to calculate Radius of turn for given lift coefficient using this online calculator? To use this online calculator for Radius of turn for given lift coefficient, enter Aircraft weight (W), Freestream density (ฯโˆž), Reference Area (S) & Lift Coefficient (CL) and hit the calculate button. Here is how the Radius of turn for given lift coefficient calculation can be explained with given input values -> 294.9525 = 2*Weight_of_aircraft_/(1.225*5.08*[g]*0.002).

FAQ

What is Radius of turn for given lift coefficient?
The Radius of turn for given lift coefficient of an aircraft is a function of the aircraft's weight and altitude and is represented as R = 2*W/(ฯโˆž*S*[g]*CL) or Turn Radius = 2*Aircraft weight/(Freestream density*Reference Area*[g]*Lift Coefficient). Aircraft weight is the total aircraft weight at any moment during the flight or ground operation, 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 & The Lift Coefficient 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 given lift coefficient?
The Radius of turn for given lift coefficient of an aircraft is a function of the aircraft's weight and altitude is calculated using Turn Radius = 2*Aircraft weight/(Freestream density*Reference Area*[g]*Lift Coefficient). To calculate Radius of turn for given lift coefficient, you need Aircraft weight (W), Freestream density (ฯโˆž), Reference Area (S) & Lift Coefficient (CL). With our tool, you need to enter the respective value for Aircraft weight, Freestream density, Reference Area & 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 Aircraft weight, Freestream density, Reference Area & Lift Coefficient. We can use 4 other way(s) to calculate the same, which is/are as follows -
  • Turn Radius = (Velocity^2)/([g]*Load factor)
  • Turn Radius = 2*Wing Loading/(Freestream density*Lift Coefficient*[g])
  • Turn Radius = (Velocity^2)/([g]*(Load factor-1))
  • Turn Radius = (Velocity^2)/([g]*(Load factor+1))
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