Lift Coefficient for given Turn Rate Calculator

✖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 [ω]			+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%
✖Load Factor is the ratio of the aerodynamic force on the aircraft to the gross weight of the aircraft.ⓘ Load Factor [n]			+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 for given Turn Rate [C_L]

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Lift Coefficient for given Turn Rate Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift Coefficient = 2*Aircraft Weight*(Turn Rate^2)/([g]^2*Freestream Density*Load Factor*Reference Area)
C_L = 2*W*(ω^2)/([g]^2*ρ_∞*n*S)
This formula uses 1 Constants, 6 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.
Turn Rate - (Measured in Radian per Second) - Turn Rate is the rate at which an aircraft executes a turn expressed in degrees per second.
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.
Load Factor - Load Factor is the ratio of the aerodynamic force on the aircraft to the gross weight of the aircraft.
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.

STEP 1: Convert Input(s) to Base Unit

Aircraft Weight: 1800 Newton --> 1800 Newton No Conversion Required
Turn Rate: 1.144 Degree per Second --> 0.0199665666428114 Radian per Second (Check conversion here)
Freestream Density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Load Factor: 1.2 --> No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_L = 2*W*(ω^2)/([g]^2*ρ_∞*n*S) --> 2*1800*(0.0199665666428114^2)/([g]^2*1.225*1.2*5.08)

Evaluating ... ...

C_L = 0.00199842054871387

STEP 3: Convert Result to Output's Unit

0.00199842054871387 --> No Conversion Required

FINAL ANSWER

0.00199842054871387 ≈ 0.001998 <-- Lift Coefficient

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

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

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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])

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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

Lift Coefficient for given Turn Rate Formula

LaTeX Go

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

What is adverse yaw?

Adverse yaw is the natural and undesirable tendency for an aircraft to yaw in the opposite direction of a roll. It is caused by the difference in lift and drag of each wing.

How to Calculate Lift Coefficient for given Turn Rate?

Lift Coefficient for given Turn Rate calculator uses Lift Coefficient = 2*Aircraft Weight*(Turn Rate^2)/([g]^2*Freestream Density*Load Factor*Reference Area) to calculate the Lift Coefficient, Lift Coefficient for given Turn Rate formula is defined as a measure of the aerodynamic efficiency of an aircraft during a turn, reflecting the relationship between weight, turn rate, and the aircraft's lift characteristics in high load factor maneuvers. Lift Coefficient is denoted by C_L symbol.

How to calculate Lift Coefficient for given Turn Rate using this online calculator? To use this online calculator for Lift Coefficient for given Turn Rate, enter Aircraft Weight (W), Turn Rate (ω), Freestream Density (ρ_∞), Load Factor (n) & Reference Area (S) and hit the calculate button. Here is how the Lift Coefficient for given Turn Rate calculation can be explained with given input values -> 0.001998 = 2*1800*(0.0199665666428114^2)/([g]^2*1.225*1.2*5.08).

FAQ

What is Lift Coefficient for given Turn Rate?

Lift Coefficient for given Turn Rate formula is defined as a measure of the aerodynamic efficiency of an aircraft during a turn, reflecting the relationship between weight, turn rate, and the aircraft's lift characteristics in high load factor maneuvers and is represented as C_L = 2*W*(ω^2)/([g]^2*ρ_∞*n*S) or Lift Coefficient = 2*Aircraft Weight*(Turn Rate^2)/([g]^2*Freestream Density*Load Factor*Reference Area). Aircraft Weight is the total aircraft weight at any moment during the flight or ground operation, Turn Rate is the rate at which an aircraft executes a turn expressed in degrees per second, Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, Load Factor is the ratio of the aerodynamic force on the aircraft to the gross weight of the aircraft & 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.

How to calculate Lift Coefficient for given Turn Rate?

Lift Coefficient for given Turn Rate formula is defined as a measure of the aerodynamic efficiency of an aircraft during a turn, reflecting the relationship between weight, turn rate, and the aircraft's lift characteristics in high load factor maneuvers is calculated using Lift Coefficient = 2*Aircraft Weight*(Turn Rate^2)/([g]^2*Freestream Density*Load Factor*Reference Area). To calculate Lift Coefficient for given Turn Rate, you need Aircraft Weight (W), Turn Rate (ω), Freestream Density (ρ_∞), Load Factor (n) & Reference Area (S). With our tool, you need to enter the respective value for Aircraft Weight, Turn Rate, Freestream Density, Load Factor & Reference Area 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, Turn Rate, Freestream Density, Load Factor & Reference Area. We can use 2 other way(s) to calculate the same, which is/are as follows -

Lift Coefficient = Aircraft Weight/(0.5*Freestream Density*Reference Area*[g]*Turn Radius)
Lift Coefficient = 2*Wing Loading/(Freestream Density*Turn Radius*[g])

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