Radius of Turn for given Lift Coefficient 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%
✖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%

✖Turn Radius is the radius of the flight path causing the airplane to turn in a circular path.ⓘ Radius of Turn for given Lift Coefficient [R]

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Radius of Turn for given Lift Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Turn Radius = 2*Aircraft Weight/(Freestream Density*Reference Area*[g]*Lift Coefficient)
R = 2*W/(ρ_∞*S*[g]*C_L)
This formula uses 1 Constants, 5 Variables

Constants Used

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

Variables Used

Turn Radius - (Measured in Meter) - Turn Radius is the radius of the flight path causing the airplane to turn in a circular path.
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.
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

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
Lift Coefficient: 0.002 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

R = 2*W/(ρ_∞*S*[g]*C_L) --> 2*1800/(1.225*5.08*[g]*0.002)

Evaluating ... ...

R = 29495.2463982046

STEP 3: Convert Result to Output's Unit

29495.2463982046 Meter --> No Conversion Required

FINAL ANSWER

29495.2463982046 ≈ 29495.25 Meter <-- Turn Radius

(Calculation completed in 00.008 seconds)

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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 Shikha Maurya

Indian Institute of Technology (IIT), Bombay

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< High Load Factor Maneuver Calculators

Velocity given Turn Radius for High Load Factor

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

Load factor for given turn radius for high-performance fighter aircraft

LaTeX Go Load Factor = (Velocity^2)/([g]*Turn Radius)

Turn radius for high load factor

LaTeX Go Turn Radius = (Velocity^2)/([g]*Load Factor)

Turn Rate for High Load Factor

LaTeX Go Turn Rate = [g]*Load Factor/Velocity

Radius of Turn for given Lift Coefficient Formula

LaTeX Go

Turn Radius = 2*Aircraft Weight/(Freestream Density*Reference Area*[g]*Lift Coefficient)
R = 2*W/(ρ_∞*S*[g]*C_L)

What is a wingover?

A wingover is a manoeuvre that provides a fast, 180-degree turn with a minimal turn radius. It consists of a quarter loop into a vertical climb, letting the speed fall as altitude increases, and then a flat-turn over the top, diving to complete a quarter loop at the original altitude, but going in the opposite direction.

How to Calculate Radius of Turn for given Lift Coefficient?

Radius of Turn for given Lift Coefficient calculator uses Turn Radius = 2*Aircraft Weight/(Freestream Density*Reference Area*[g]*Lift Coefficient) to calculate the Turn Radius, Radius of Turn for given Lift Coefficient is a measure of the turning radius required for an aircraft to maintain a specific lift coefficient. This formula relates the turn radius to aircraft weight, freestream density, reference area, gravitational acceleration, and the desired lift coefficient. Understanding and applying this formula is essential for pilots and engineers in optimizing aircraft maneuverability and stability based on desired lift characteristics. Turn Radius is denoted by R symbol.

How to calculate Radius of Turn for given Lift Coefficient using this online calculator? To use this online calculator for Radius of Turn for given Lift Coefficient, enter Aircraft Weight (W), Freestream Density (ρ_∞), Reference Area (S) & Lift Coefficient (C_L) and hit the calculate button. Here is how the Radius of Turn for given Lift Coefficient calculation can be explained with given input values -> 29495.25 = 2*1800/(1.225*5.08*[g]*0.002).

FAQ

What is Radius of Turn for given Lift Coefficient?

Radius of Turn for given Lift Coefficient is a measure of the turning radius required for an aircraft to maintain a specific lift coefficient. This formula relates the turn radius to aircraft weight, freestream density, reference area, gravitational acceleration, and the desired lift coefficient. Understanding and applying this formula is essential for pilots and engineers in optimizing aircraft maneuverability and stability based on desired lift characteristics and is represented as R = 2*W/(ρ_∞*S*[g]*C_L) or Turn Radius = 2*Aircraft Weight/(Freestream Density*Reference Area*[g]*Lift Coefficient). 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 & 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 Radius of Turn for given Lift Coefficient?

Radius of Turn for given Lift Coefficient is a measure of the turning radius required for an aircraft to maintain a specific lift coefficient. This formula relates the turn radius to aircraft weight, freestream density, reference area, gravitational acceleration, and the desired lift coefficient. Understanding and applying this formula is essential for pilots and engineers in optimizing aircraft maneuverability and stability based on desired lift characteristics is calculated using Turn Radius = 2*Aircraft Weight/(Freestream Density*Reference Area*[g]*Lift Coefficient). To calculate Radius of Turn for given Lift Coefficient, you need Aircraft Weight (W), Freestream Density (ρ_∞), Reference Area (S) & Lift Coefficient (C_L). With our tool, you need to enter the respective value for Aircraft Weight, Freestream Density, Reference Area & 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 Turn Radius?

In this formula, Turn Radius uses Aircraft Weight, Freestream Density, Reference Area & Lift Coefficient. We can use 2 other way(s) to calculate the same, which is/are as follows -

Turn Radius = (Velocity^2)/([g]*Load Factor)
Turn Radius = 2*Wing Loading/(Freestream Density*Lift Coefficient*[g])

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