Turn Rate for given Lift Coefficient Calculator

✖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%
✖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%
✖Load Factor is the ratio of the aerodynamic force on the aircraft to the gross weight of the aircraft.ⓘ Load Factor [n]			+10% -10%
✖Aircraft Weight is the total aircraft weight at any moment during the flight or ground operation.ⓘ Aircraft Weight [W]			+10% -10%

✖Turn Rate is the rate at which an aircraft executes a turn expressed in degrees per second.ⓘ Turn Rate for given Lift Coefficient [ω]

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Turn Rate for given Lift Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Turn Rate = [g]*(sqrt((Reference Area*Freestream Density*Lift Coefficient*Load Factor)/(2*Aircraft Weight)))
ω = [g]*(sqrt((S*ρ_∞*C_L*n)/(2*W)))
This formula uses 1 Constants, 1 Functions, 6 Variables

Constants Used

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

Functions Used

sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)

Variables Used

Turn Rate - (Measured in Radian per Second) - Turn Rate is the rate at which an aircraft executes a turn expressed in degrees per second.
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.
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.
Load Factor - Load Factor is the ratio of the aerodynamic force on the aircraft to the gross weight of the aircraft.
Aircraft Weight - (Measured in Newton) - Aircraft Weight is the total aircraft weight at any moment during the flight or ground operation.

STEP 1: Convert Input(s) to Base Unit

Reference Area: 5.08 Square Meter --> 5.08 Square 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
Load Factor: 1.2 --> No Conversion Required
Aircraft Weight: 1800 Newton --> 1800 Newton No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

ω = [g]*(sqrt((S*ρ_∞*C_L*n)/(2*W))) --> [g]*(sqrt((5.08*1.225*0.002*1.2)/(2*1800)))

Evaluating ... ...

ω = 0.0199744553704078

STEP 3: Convert Result to Output's Unit

0.0199744553704078 Radian per Second -->1.144451990797 Degree per Second (Check conversion here)

FINAL ANSWER

1.144451990797 ≈ 1.144452 Degree per Second <-- Turn Rate

(Calculation completed in 00.004 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 Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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< High Load Factor Maneuver Calculators

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

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Turn Rate for given Lift Coefficient Formula

LaTeX Go

Turn Rate = [g]*(sqrt((Reference Area*Freestream Density*Lift Coefficient*Load Factor)/(2*Aircraft Weight)))
ω = [g]*(sqrt((S*ρ_∞*C_L*n)/(2*W)))

What are the three axes of rotation of an aircraft?

An aeroplane has three axes of rotation: Pitch, Yaw and Roll. Coordinated flight requires the pilot to use pitch, roll and yaw control simultaneously.

How to Calculate Turn Rate for given Lift Coefficient?

Turn Rate for given Lift Coefficient calculator uses Turn Rate = [g]*(sqrt((Reference Area*Freestream Density*Lift Coefficient*Load Factor)/(2*Aircraft Weight))) to calculate the Turn Rate, Turn Rate for given Lift Coefficient formula is defined as a measure of the aircraft's ability to change direction during flight, influenced by lift, weight, and aerodynamic properties, crucial for assessing maneuverability in high load factor conditions. Turn Rate is denoted by ω symbol.

How to calculate Turn Rate for given Lift Coefficient using this online calculator? To use this online calculator for Turn Rate for given Lift Coefficient, enter Reference Area (S), Freestream Density (ρ_∞), Lift Coefficient (C_L), Load Factor (n) & Aircraft Weight (W) and hit the calculate button. Here is how the Turn Rate for given Lift Coefficient calculation can be explained with given input values -> 65.57227 = [g]*(sqrt((5.08*1.225*0.002*1.2)/(2*1800))).

FAQ

What is Turn Rate for given Lift Coefficient?

Turn Rate for given Lift Coefficient formula is defined as a measure of the aircraft's ability to change direction during flight, influenced by lift, weight, and aerodynamic properties, crucial for assessing maneuverability in high load factor conditions and is represented as ω = [g]*(sqrt((S*ρ_∞*C_L*n)/(2*W))) or Turn Rate = [g]*(sqrt((Reference Area*Freestream Density*Lift Coefficient*Load Factor)/(2*Aircraft Weight))). 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, 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, Load Factor is the ratio of the aerodynamic force on the aircraft to the gross weight of the aircraft & Aircraft Weight is the total aircraft weight at any moment during the flight or ground operation.

How to calculate Turn Rate for given Lift Coefficient?

Turn Rate for given Lift Coefficient formula is defined as a measure of the aircraft's ability to change direction during flight, influenced by lift, weight, and aerodynamic properties, crucial for assessing maneuverability in high load factor conditions is calculated using Turn Rate = [g]*(sqrt((Reference Area*Freestream Density*Lift Coefficient*Load Factor)/(2*Aircraft Weight))). To calculate Turn Rate for given Lift Coefficient, you need Reference Area (S), Freestream Density (ρ_∞), Lift Coefficient (C_L), Load Factor (n) & Aircraft Weight (W). With our tool, you need to enter the respective value for Reference Area, Freestream Density, Lift Coefficient, Load Factor & Aircraft Weight 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 Rate?

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

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

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