Lift Coefficient for given Turn Radius Calculator

⤿

Aircraft Performance

Aircraft Design

Introduction and Governing Equations

Static Stability and Control

⤿

⤿

High Load Factor Maneuver

Pull Up and Pull Down Maneuver

✖Aircraft weight is the total aircraft weight at any moment during the flight or ground operation.ⓘ Aircraft weight [W]			+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 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.ⓘ Reference Area [S]			+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 Turn Radius [C_L]

⎘ Copy

👎

Formula

✖

Lift Coefficient for given Turn Radius

Formula

`"C"_{"L"} = "W"/(0.5*"ρ"_{"∞"}*"S"*"[g]"*"R")`

Example

`"0.196635"="1800N"/(0.5*"1.225kg/m³"*"5.08m²"*"[g]"*"300m")`

Calculator

LaTeX

Reset

👍

Download Physics Formula PDF PDF Image

Lift Coefficient for given Turn Radius Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift Coefficient = Aircraft weight/(0.5*Freestream density*Reference Area*[g]*Turn Radius)
C_L = W/(0.5*ρ_∞*S*[g]*R)
This formula uses 1 Constants, 5 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.
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.
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

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
Turn Radius: 300 Meter --> 300 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_L = W/(0.5*ρ_∞*S*[g]*R) --> 1800/(0.5*1.225*5.08*[g]*300)

Evaluating ... ...

C_L = 0.196634975988031

STEP 3: Convert Result to Output's Unit

0.196634975988031 --> No Conversion Required

FINAL ANSWER

0.196634975988031 ≈ 0.196635 <-- Lift Coefficient

(Calculation completed in 00.007 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Aircraft Performance » Maneuvering Flight » High Load Factor Maneuver » Lift Coefficient 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 Sai Venkata Phanindra Chary Arendra

Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad

Sai Venkata Phanindra Chary Arendra has verified this Calculator and 300+ 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

Lift Coefficient for given Turn Radius Formula

Lift Coefficient = Aircraft weight/(0.5*Freestream density*Reference Area*[g]*Turn Radius)
C_L = W/(0.5*ρ_∞*S*[g]*R)

What is a coordinated flight?

In aviation, a coordinated flight of an aircraft is flight without sideslip. When an aircraft is flying with zero sideslip a turn and bank indicator installed on the aircraft's instrument panel usually shows the ball in the centre of the spirit level.

How to Calculate Lift Coefficient for given Turn Radius?

Lift Coefficient for given Turn Radius calculator uses Lift Coefficient = Aircraft weight/(0.5*Freestream density*Reference Area*[g]*Turn Radius) to calculate the Lift Coefficient, The Lift Coefficient for given turn radius of an aircraft is a function of the altitude and weight of the aircraft. Lift Coefficient is denoted by C_L symbol.

How to calculate Lift Coefficient for given Turn Radius using this online calculator? To use this online calculator for Lift Coefficient for given Turn Radius, enter Aircraft weight (W), Freestream density (ρ_∞), Reference Area (S) & Turn Radius (R) and hit the calculate button. Here is how the Lift Coefficient for given Turn Radius calculation can be explained with given input values -> 0.001966 = Weight_of_aircraft_/(0.5*1.225*5.08*[g]*300).

FAQ

What is Lift Coefficient for given Turn Radius?

The Lift Coefficient for given turn radius of an aircraft is a function of the altitude and weight of the aircraft and is represented as C_L = W/(0.5*ρ_∞*S*[g]*R) or Lift Coefficient = Aircraft weight/(0.5*Freestream density*Reference Area*[g]*Turn Radius). 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 & 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 Turn Radius?

The Lift Coefficient for given turn radius of an aircraft is a function of the altitude and weight of the aircraft is calculated using Lift Coefficient = Aircraft weight/(0.5*Freestream density*Reference Area*[g]*Turn Radius). To calculate Lift Coefficient for given Turn Radius, you need Aircraft weight (W), Freestream density (ρ_∞), Reference Area (S) & Turn Radius (R). With our tool, you need to enter the respective value for Aircraft weight, Freestream density, Reference Area & 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 Aircraft weight, Freestream density, Reference Area & Turn Radius. We can use 2 other way(s) to calculate the same, which is/are as follows -

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

Home

FREE PDFs

🔍 Search