Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 200+ more calculators!
Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has verified this Calculator and 100+ more calculators!

11 Other formulas that you can solve using the same Inputs

Propeller Efficiency for given Endurance of Propeller-Driven Airplane
Propeller efficiency=Endurance of aircraft/((1/Specific Fuel Consumption)*((lift coefficient^1.5)/Drag Coefficient)*(sqrt(2*Freestream density*Reference Area))*(((1/Gross Weight)^(1/2))-((1/Weight without fuel)^(1/2)))) GO
Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane
Specific Fuel Consumption=(Propeller efficiency/Endurance of aircraft)*((lift coefficient^1.5)/Drag Coefficient)*(sqrt(2*Freestream density*Reference Area))*(((1/Gross Weight)^(1/2))-((1/Weight without fuel)^(1/2))) GO
Endurance of Propeller-Driven Airplane
Endurance of aircraft=(Propeller efficiency/Specific Fuel Consumption)*((lift coefficient^1.5)/Drag Coefficient)*(sqrt(2*Freestream density*Reference Area))*(((1/Gross Weight)^(1/2))-((1/Weight without fuel)^(1/2))) GO
Thrust-Specific Fuel Consumption for given Range of Jet Airplane
Thrust-Specific Fuel Consumption=(sqrt(8/(Freestream density*Reference Area)))*(1/(Range of aircraft*Drag Coefficient))*(sqrt(lift coefficient))*((sqrt(Gross Weight))-(sqrt(Weight without fuel))) GO
Range of Jet Airplane
Range of aircraft=(sqrt(8/(Freestream density*Reference Area)))*(1/(Thrust-Specific Fuel Consumption*Drag Coefficient))*(sqrt(lift coefficient))*((sqrt(Gross Weight))-(sqrt(Weight without fuel))) GO
Drag during ground effect
Drag Force=(Parasite Drag coefficient+(((lift coefficient^2)*Ground effect factor)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)))*(0.5*Freestream density*(Velocity^2)*Reference Area) GO
Pressure for the cylindrical blast wave
Pressure=Boltzmann constant 1*Freestream density*((Energy/Freestream density)^(1/2))/(Time) GO
formula For creation pressure for the planar blast wave
Pressure=[BoltZ]*Freestream density*((Energy/Freestream density)^(2/3))*(Time)^(-2/3) GO
Energy for the blast wave
Energy=(0.5)*Freestream density*(Freestream Velocity^2)*Drag Coefficient*Area GO
Radial coordinate for the planar blast wave,
Radial coordinate=((Energy/Freestream density)^(1/3))*(Time^(2/3)) GO
Radial coordinate of cylindrical blast wave
Radial coordinate=((Energy/Freestream density)^(1/4))*(Time^(1/2)) 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 rate
lift coefficient=2*Weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area) 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 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
Lift coefficient for a rotating cylinder with tangential speed
lift coefficient=(2*pi*Tangential Velocity)/Freestream Velocity 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 wing loading and turn radius Formula

lift coefficient=2*Wing Loading/(Freestream density*Turn Radius*[g])
C<sub>L</sub>=2*W<sub>S</sub>/(ρ<sub>∞</sub>*R*[g])
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
Load factor for a given turn rate for a high-performance fighter aircraft GO
Radius of turn for a given lift coefficient GO
Turn rate for a given lift coefficient GO
Lift Coefficient for a given turn rate GO
Radius of turn for a given wing loading GO
Wing loading for a given turn radius GO
Turn rate for a given wing loading GO

What is the significance of wing loading?

The faster an aircraft flies, the more lift is produced by each unit of wing area, so a smaller wing can carry the same weight in level flight, operating at a higher wing loading.

How to Calculate Lift Coefficient for a given wing loading and turn radius?

Lift Coefficient for a given wing loading and turn radius calculator uses lift coefficient=2*Wing Loading/(Freestream density*Turn Radius*[g]) to calculate the lift coefficient, The Lift Coefficient for a given wing loading and turn radius depends upon the altitude, turn radius and wing loading of the aircraft. lift coefficient and is denoted by CL symbol.

How to calculate Lift Coefficient for a given wing loading and turn radius using this online calculator? To use this online calculator for Lift Coefficient for a given wing loading and turn radius, enter Wing Loading (WS), Freestream density ) and Turn Radius (R) and hit the calculate button. Here is how the Lift Coefficient for a given wing loading and turn radius calculation can be explained with given input values -> 0.002775 = 2*5/(1.225*300*[g]).

FAQ

What is Lift Coefficient for a given wing loading and turn radius?
The Lift Coefficient for a given wing loading and turn radius depends upon the altitude, turn radius and wing loading of the aircraft and is represented as CL=2*WS/(ρ*R*[g]) or lift coefficient=2*Wing Loading/(Freestream density*Turn Radius*[g]). Wing Loading is the loaded weight of the aircraft divided by the area of the wing, Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude and Turn Radius is the radius of the flight path causing the airplane to turn in a circular path.
How to calculate Lift Coefficient for a given wing loading and turn radius?
The Lift Coefficient for a given wing loading and turn radius depends upon the altitude, turn radius and wing loading of the aircraft is calculated using lift coefficient=2*Wing Loading/(Freestream density*Turn Radius*[g]). To calculate Lift Coefficient for a given wing loading and turn radius, you need Wing Loading (WS), Freestream density ) and Turn Radius (R). With our tool, you need to enter the respective value for Wing Loading, Freestream density and 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 Wing Loading, Freestream density and Turn Radius. 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*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area)
  • 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)
  • lift coefficient=(2*pi*Tangential Velocity)/Freestream Velocity
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