Lift Coefficient for a given turn rate Calculator

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Physics	Flight Stability and Control ↺
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✖Weight is a vector quantity and defined as the product of mass and acceleration acting on that massⓘ 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 (CL) 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 a given turn rate [C_L]

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Vinay Mishra

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

Vinay Mishra has created this Calculator and 300+ more calculators!

Shikha Maurya

Indian Institute of Technology (IIT), Bombay

Shikha Maurya has verified this Calculator and 100+ more calculators!

< 11 Other formulas that you can solve using the same Inputs

Minimum Thrust required for given weight

Thrust of an aircraft=(Dynamic Pressure*Reference Area*Zero-lift drag coefficient)+((Weight^2)/(Dynamic Pressure*Reference Area*pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO

Lift coefficient for given minimum required thrust

lift coefficient=sqrt(pi*Oswald efficiency factor*Aspect Ratio of a wing*((Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Zero-lift drag coefficient)) GO

Zero-lift drag coefficient for given required thrust

Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Coefficient of drag due to lift GO

Power required for given aerodynamic coefficients

Power=Weight*Freestream Velocity*Drag Coefficient/lift coefficient GO

Coefficient of Drag for given thrust and weight

Drag Coefficient=Thrust of an aircraft*lift coefficient/Weight GO

Coefficient of Lift for given thrust and weight

lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft GO

Thrust for given coefficients of lift and drag

Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient GO

Lift for an unaccelerated flight

Lift force=Weight-(Thrust of an aircraft*sin(Thrust angle)) GO

Thrust angle for an unaccelerated flight for given lift

Thrust angle=asin((Weight-Lift force)/Thrust of an aircraft) GO

Thrust required for given Lift-to-drag ratio

Thrust of an aircraft=Weight/Lift-to-drag ratio GO

Lift-to-drag ratio for given required thrust

Lift-to-drag ratio=Weight/Thrust of an aircraft GO

< 11 Other formulas that calculate the same Output

Lift coefficient for given minimum required thrust

lift coefficient=sqrt(pi*Oswald efficiency factor*Aspect Ratio of a wing*((Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Zero-lift drag coefficient)) GO

Total Lift Coefficient of wing-tail combination

lift coefficient=Wing Lift Coefficient+(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area) GO

Lift Coefficient for a given turn radius

lift coefficient=2*Weight/(Freestream density*Reference Area*[g]*Turn Radius) GO

lift coefficient for lift force in a body moving on a fluid

lift coefficient=Lift force/(Reference Area*0.5*Density*(Velocity^2)) GO

Lift Coefficient for a given wing loading and turn radius

lift coefficient=2*Wing Loading/(Freestream density*Turn Radius*[g]) GO

Lift coefficient for a rotating cylinder with circulation

lift coefficient=Circulation/(Cylinder Radius*Freestream Velocity) GO

Coefficient of lift equation with angle of attack

lift coefficient=2*((sin(Angle of attack))^2)*cos(Angle of attack) GO

Coefficient of Lift for given thrust and weight

lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft GO

Coefficient of lift equation with coefficient of normal force

lift coefficient=coefficient of force*cos(Angle of attack) GO

Coefficient of Lift for given thrust-to-weight ratio

lift coefficient=Drag Coefficient/Thrust-to-weight ratio GO

lift coefficient

lift coefficient=Lift force/(Dynamic Pressure*Area) GO

Lift Coefficient for a given turn rate Formula

lift coefficient=2*Weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area)
C<sub>L</sub>=2*W*(ω^2)/(([g]^2)*ρ<sub>∞</sub>*n*S)

More formulas

Turn radius for a high load factor GO

Velocity for a given turn radius for a high load factor GO

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

Turn rate for a high load factor GO

Velocity for a given turn rate for a high load factor GO

Load factor for a given turn rate for a high-performance fighter aircraft GO

Radius of turn for a given lift coefficient GO

Lift Coefficient for a given turn radius GO

Turn rate for a given lift coefficient GO

Radius of turn for a given wing loading GO

Lift Coefficient for a given wing loading and turn radius GO

Wing loading for a given turn radius GO

Turn rate for a given wing loading GO

Wing loading for a given turn rate GO

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 a given turn rate?

Lift Coefficient for a given turn rate calculator uses lift coefficient=2*Weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area) to calculate the lift coefficient, The Lift Coefficient for a given turn rate of an aircraft depends on its weight, altitude and load factor. lift coefficient and is denoted by C_L symbol.

How to calculate Lift Coefficient for a given turn rate using this online calculator? To use this online calculator for Lift Coefficient for a given turn rate, enter Weight (W), Turn Rate (ω), Freestream density (ρ_∞), Load factor (n) and Reference Area (S) and hit the calculate button. Here is how the Lift Coefficient for a given turn rate calculation can be explained with given input values -> 0.000776 = 2*100*(0.05235987755982^2)/(([g]^2)*1.225*1.2*5).

FAQ

What is Lift Coefficient for a given turn rate?

The Lift Coefficient for a given turn rate of an aircraft depends on its weight, altitude and load factor and is represented as C_L=2*W*(ω^2)/(([g]^2)*ρ_∞*n*S) or lift coefficient=2*Weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area). Weight is a vector quantity and defined as the product of mass and acceleration acting on that mass, 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 and 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 a given turn rate?

The Lift Coefficient for a given turn rate of an aircraft depends on its weight, altitude and load factor is calculated using lift coefficient=2*Weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area). To calculate Lift Coefficient for a given turn rate, you need Weight (W), Turn Rate (ω), Freestream density (ρ_∞), Load factor (n) and Reference Area (S). With our tool, you need to enter the respective value for Weight, Turn Rate, Freestream density, Load factor and 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 Weight, Turn Rate, Freestream density, Load factor and Reference Area. We can use 11 other way(s) to calculate the same, which is/are as follows -

lift coefficient=Lift force/(Dynamic Pressure*Area)
lift coefficient=Drag Coefficient/Thrust-to-weight ratio
lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft
lift coefficient=sqrt(pi*Oswald efficiency factor*Aspect Ratio of a wing*((Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Zero-lift drag coefficient))
lift coefficient=coefficient of force*cos(Angle of attack)
lift coefficient=2*((sin(Angle of attack))^2)*cos(Angle of attack)
lift coefficient=2*Weight/(Freestream density*Reference Area*[g]*Turn Radius)
lift coefficient=2*Wing Loading/(Freestream density*Turn Radius*[g])
lift coefficient=Wing Lift Coefficient+(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area)
lift coefficient=Lift force/(Reference Area*0.5*Density*(Velocity^2))
lift coefficient=Circulation/(Cylinder Radius*Freestream Velocity)

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