Lift Coefficient for given Turn Radius Calculator

✖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 = \frac{W}{0.5 \cdot ρ ∞ \cdot S \cdot [g] \cdot R}

Example

0.002 = \frac{1800 N}{0.5 \cdot 1.225 kg/m³ \cdot 5.08 m² \cdot [g] \cdot 29495.25 m}

Calculator

LaTeX

Reset

👍

Download High Load Factor Maneuver Formulas 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: 29495.25 Meter --> 29495.25 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]*29495.25)

Evaluating ... ...

C_L = 0.00199999975577115

STEP 3: Convert Result to Output's Unit

0.00199999975577115 --> No Conversion Required

FINAL ANSWER

0.00199999975577115 ≈ 0.002 <-- Lift Coefficient

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Aircraft Performance » Maneuvering Flight » Aerospace » 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!

< High Load Factor Maneuver Calculators

Velocity given Turn Radius for High Load Factor

Go Velocity = sqrt(Turn Radius*Load Factor*[g])

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)

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 is a dimensionless quantity that describes the lift generated by an airfoil or a body moving through a fluid, typically air, this equation shows how the lift coefficient is influenced by these factors in the context of a turning 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 -> 0.196635 = 1800/(0.5*1.225*5.08*[g]*29495.25).

FAQ

What is Lift Coefficient for given Turn Radius?

The Lift Coefficient for given turn radius is a dimensionless quantity that describes the lift generated by an airfoil or a body moving through a fluid, typically air, this equation shows how the lift coefficient is influenced by these factors in the context of a turning 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 is a dimensionless quantity that describes the lift generated by an airfoil or a body moving through a fluid, typically air, this equation shows how the lift coefficient is influenced by these factors in the context of a turning 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