Lift Coefficient for given turn rate Solution

STEP 0: Pre-Calculation Summary
Formula Used
Lift Coefficient = 2*Aircraft weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area)
CL = 2*W*(ฯ‰^2)/(([g]^2)*ฯโˆž*n*S)
This formula uses 1 Constants, 6 Variables
Constants Used
[g] - Gravitational acceleration on Earth Value Taken As 9.80665
Variables Used
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.
Aircraft weight - (Measured in Newton) - Aircraft weight is the total aircraft weight at any moment during the flight or ground operation.
Turn Rate - (Measured in Radian per Second) - Turn Rate is the rate at which an aircraft executes a turn expressed in degrees per second.
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.
Load factor - Load factor is the ratio of the aerodynamic force on the aircraft to the gross weight of the aircraft.
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.
STEP 1: Convert Input(s) to Base Unit
Aircraft weight: 1800 Newton --> 1800 Newton No Conversion Required
Turn Rate: 1.14 Degree per Second --> 0.0198967534727316 Radian per Second (Check conversion here)
Freestream density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Load factor: 1.2 --> No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
CL = 2*W*(ฯ‰^2)/(([g]^2)*ฯโˆž*n*S) --> 2*1800*(0.0198967534727316^2)/(([g]^2)*1.225*1.2*5.08)
Evaluating ... ...
CL = 0.0019844700116055
STEP 3: Convert Result to Output's Unit
0.0019844700116055 --> No Conversion Required
FINAL ANSWER
0.0019844700116055 โ‰ˆ 0.001984 <-- Lift Coefficient
(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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Indian Institute of Technology (IIT), Bombay
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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

Lift Coefficient for given turn rate Formula

Lift Coefficient = 2*Aircraft weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area)
CL = 2*W*(ฯ‰^2)/(([g]^2)*ฯโˆž*n*S)

What is adverse yaw?

Adverse yaw is the natural and undesirable tendency for an aircraft to yaw in the opposite direction of a roll. It is caused by the difference in lift and drag of each wing.

How to Calculate Lift Coefficient for given turn rate?

Lift Coefficient for given turn rate calculator uses Lift Coefficient = 2*Aircraft weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area) to calculate the Lift Coefficient, The Lift Coefficient for given turn rate of an aircraft depends on its weight, altitude, and load factor. Lift Coefficient is denoted by CL symbol.

How to calculate Lift Coefficient for given turn rate using this online calculator? To use this online calculator for Lift Coefficient for given turn rate, enter Aircraft weight (W), Turn Rate (ฯ‰), Freestream density (ฯโˆž), Load factor (n) & Reference Area (S) and hit the calculate button. Here is how the Lift Coefficient for given turn rate calculation can be explained with given input values -> 0.013743 = 2*1800*(0.0198967534727316^2)/(([g]^2)*1.225*1.2*5.08).

FAQ

What is Lift Coefficient for given turn rate?
The Lift Coefficient for given turn rate of an aircraft depends on its weight, altitude, and load factor and is represented as CL = 2*W*(ฯ‰^2)/(([g]^2)*ฯโˆž*n*S) or Lift Coefficient = 2*Aircraft weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area). Aircraft weight is the total aircraft weight at any moment during the flight or ground operation, Turn Rate is the rate at which an aircraft executes a turn expressed in degrees per second, Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, Load factor is the ratio of the aerodynamic force on the aircraft to the gross weight of the aircraft & 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.
How to calculate Lift Coefficient for given turn rate?
The Lift Coefficient for given turn rate of an aircraft depends on its weight, altitude, and load factor is calculated using Lift Coefficient = 2*Aircraft weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area). To calculate Lift Coefficient for given turn rate, you need Aircraft weight (W), Turn Rate (ฯ‰), Freestream density (ฯโˆž), Load factor (n) & Reference Area (S). With our tool, you need to enter the respective value for Aircraft weight, Turn Rate, Freestream density, Load factor & Reference Area 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 Lift Coefficient?
In this formula, Lift Coefficient uses Aircraft weight, Turn Rate, Freestream density, Load factor & Reference Area. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Lift Coefficient = Aircraft weight/(0.5*Freestream density*Reference Area*[g]*Turn Radius)
  • Lift Coefficient = 2*Wing Loading/(Freestream density*Turn Radius*[g])
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