Lift Coefficient for given wing loading and turn radius Calculator

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High Load Factor Maneuver

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✖Wing Loading is the loaded weight of the aircraft divided by the area of the wing.ⓘ Wing Loading [W_S]			+10% -10%
✖Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.ⓘ Freestream density [ρ_∞]			+10% -10%
✖Turn Radius is the radius of the flight path causing the airplane to turn in a circular path.ⓘ Turn Radius [R]			+10% -10%

✖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.ⓘ Lift Coefficient for given wing loading and turn radius [C_L]

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Formula

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Lift Coefficient for given wing loading and turn radius

Formula

`"C"_{"L"} = 2*"W"_{"S"}/("ρ"_{"∞"}*"R"*"[g]")`

Example

`"0.002775"=2*"5Pa"/("1.225kg/m³"*"300m"*"[g]")`

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Lift Coefficient for given wing loading and turn radius Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift Coefficient = 2*Wing Loading/(Freestream density*Turn Radius*[g])
C_L = 2*W_S/(ρ_∞*R*[g])
This formula uses 1 Constants, 4 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.
Wing Loading - (Measured in Pascal) - Wing Loading is the loaded weight of the aircraft divided by the area of the wing.
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.
Turn Radius - (Measured in Meter) - Turn Radius is the radius of the flight path causing the airplane to turn in a circular path.

STEP 1: Convert Input(s) to Base Unit

Wing Loading: 5 Pascal --> 5 Pascal No Conversion Required
Freestream density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Turn Radius: 300 Meter --> 300 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_L = 2*W_S/(ρ_∞*R*[g]) --> 2*5/(1.225*300*[g])

Evaluating ... ...

C_L = 0.00277473799449776

STEP 3: Convert Result to Output's Unit

0.00277473799449776 --> No Conversion Required

FINAL ANSWER

0.00277473799449776 ≈ 0.002775 <-- Lift Coefficient

(Calculation completed in 00.009 seconds)

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Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

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Amrita School of Engineering (ASE), Vallikavu

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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 wing loading and turn radius Formula

Lift Coefficient = 2*Wing Loading/(Freestream density*Turn Radius*[g])
C_L = 2*W_S/(ρ_∞*R*[g])

What is the significance of wing loading?

The faster an aircraft flies, the more lift is produced by each unit of wing area, so a smaller wing can carry the same weight in level flight, operating at a higher wing loading.

How to Calculate Lift Coefficient for given wing loading and turn radius?

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

How to calculate Lift Coefficient for given wing loading and turn radius using this online calculator? To use this online calculator for Lift Coefficient for given wing loading and turn radius, enter Wing Loading (W_S), Freestream density (ρ_∞) & Turn Radius (R) and hit the calculate button. Here is how the Lift Coefficient for given wing loading and turn radius calculation can be explained with given input values -> 0.002775 = 2*5/(1.225*300*[g]).

FAQ

What is Lift Coefficient for given wing loading and turn radius?

The Lift Coefficient for given wing loading and turn radius depends upon the altitude, turn radius, and wing loading of the aircraft and is represented as C_L = 2*W_S/(ρ_∞*R*[g]) or Lift Coefficient = 2*Wing Loading/(Freestream density*Turn Radius*[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 & Turn Radius is the radius of the flight path causing the airplane to turn in a circular path.

How to calculate Lift Coefficient for given wing loading and turn radius?

The Lift Coefficient for given wing loading and turn radius depends upon the altitude, turn radius, and wing loading of the aircraft is calculated using Lift Coefficient = 2*Wing Loading/(Freestream density*Turn Radius*[g]). To calculate Lift Coefficient for given wing loading and turn radius, you need Wing Loading (W_S), Freestream density (ρ_∞) & Turn Radius (R). With our tool, you need to enter the respective value for Wing Loading, Freestream density & Turn Radius 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 Wing Loading, Freestream density & Turn Radius. 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*Aircraft weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area)

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