Wing loading for given turn radius Calculator

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High Load Factor Maneuver

Pull Up and Pull Down Maneuver

✖Turn Radius is the radius of the flight path causing the airplane to turn in a circular path.ⓘ Turn Radius [R]			+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%
✖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 [C_L]			+10% -10%

✖Wing Loading is the loaded weight of the aircraft divided by the area of the wing.ⓘ Wing loading for given turn radius [W_S]

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Formula

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Wing loading for given turn radius

Formula

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

Example

`"3.603944Pa"=("300m"*"1.225kg/m³"*"0.002"*"[g]")/2`

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Wing loading for given turn radius Solution

STEP 0: Pre-Calculation Summary

Formula Used

Wing Loading = (Turn Radius*Freestream density*Lift Coefficient*[g])/2
W_S = (R*ρ_∞*C_L*[g])/2
This formula uses 1 Constants, 4 Variables

Constants Used

[g] - Gravitational acceleration on Earth Value Taken As 9.80665

Variables Used

Wing Loading - (Measured in Pascal) - Wing Loading is the loaded weight of the aircraft divided by the area of the wing.
Turn Radius - (Measured in Meter) - Turn Radius is the radius of the flight path causing the airplane to turn in a circular path.
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.
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

Turn Radius: 300 Meter --> 300 Meter No Conversion Required
Freestream density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Lift Coefficient: 0.002 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

W_S = (R*ρ_∞*C_L*[g])/2 --> (300*1.225*0.002*[g])/2

Evaluating ... ...

W_S = 3.603943875

STEP 3: Convert Result to Output's Unit

3.603943875 Pascal --> No Conversion Required

FINAL ANSWER

3.603943875 ≈ 3.603944 Pascal <-- Wing Loading

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Aircraft Performance » Maneuvering Flight » High Load Factor Maneuver » Wing loading for given turn radius

Credits

Created by Vinay Mishra

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

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has verified this Calculator and 200+ more calculators!

< 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

Wing loading for given turn radius Formula

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

Why is wing loading important?

Wing loading is a useful measure of the stalling speed of an aircraft. Wings generate lift owing to the motion of air around the wing. Larger wings move more air, so an aircraft with a large wing area relative to its mass (i.e., low wing loading) will have a lower stalling speed.

How to Calculate Wing loading for given turn radius?

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

How to calculate Wing loading for given turn radius using this online calculator? To use this online calculator for Wing loading for given turn radius, enter Turn Radius (R), Freestream density (ρ_∞) & Lift Coefficient (C_L) and hit the calculate button. Here is how the Wing loading for given turn radius calculation can be explained with given input values -> 3.603944 = (300*1.225*0.002*[g])/2.

FAQ

What is Wing loading for given turn radius?

The Wing loading for given turn radius of the aircraft depends upon the turn radius, altitude and lift coefficient and is represented as W_S = (R*ρ_∞*C_L*[g])/2 or Wing Loading = (Turn Radius*Freestream density*Lift Coefficient*[g])/2. Turn Radius is the radius of the flight path causing the airplane to turn in a circular path, Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude & 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 Wing loading for given turn radius?

The Wing loading for given turn radius of the aircraft depends upon the turn radius, altitude and lift coefficient is calculated using Wing Loading = (Turn Radius*Freestream density*Lift Coefficient*[g])/2. To calculate Wing loading for given turn radius, you need Turn Radius (R), Freestream density (ρ_∞) & Lift Coefficient (C_L). With our tool, you need to enter the respective value for Turn Radius, Freestream density & 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 Wing Loading?

In this formula, Wing Loading uses Turn Radius, Freestream density & Lift Coefficient. We can use 1 other way(s) to calculate the same, which is/are as follows -

Wing Loading = ([g]^2)*Freestream density*Lift Coefficient*Load factor/(2*(Turn Rate^2))

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