Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
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Sai Venkata Phanindra Chary Arendra
Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad
Sai Venkata Phanindra Chary Arendra has verified this Calculator and 100+ more calculators!

11 Other formulas that you can solve using the same Inputs

Pressure coefficient combined with blast wave for the shuttle at angle of attack
Pressure coefficient=(0.0137/(Distance from X-axis/Length of the shuttle))+2*(sin(Angle of attack))^2 GO
Velocity of airfoil for circulation developed on the airfoil
velocity of airfoil=Circulation/(pi*Chord Length*sin(Angle of attack)) GO
Chord length for circulation developed on the airfoil
Chord Length=Circulation/(pi*velocity of airfoil*sin(Angle of attack)) GO
Circulation developed on the airfoil
Circulation=pi*velocity of airfoil*Chord Length*sin(Angle of attack) GO
Coefficient of lift equation with coefficient of normal force
lift coefficient=coefficient of force*cos(Angle of attack) GO
Coefficient of drag equation with coefficient of normal force
Drag Coefficient=coefficient of force*sin(Angle of attack) GO
Lift coefficient for symmetrical airfoil by Thin airfoil theory
Lift coefficient for 2D body=2*pi*Angle of attack GO
Coefficient of drag equation with angle of attack
Drag Coefficient=2*(sin(Angle of attack))^3 GO
Coefficient of lift for an airfoil
lift coefficient=2*pi*sin(Angle of attack) GO
Lift force with angle of attack
Lift force=Drag Force*cot(Angle of attack) GO
Drag force with angle of attack
Drag Force=Lift force/cot(Angle of attack) 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 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
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

Coefficient of lift equation with angle of attack Formula

lift coefficient=2*((sin(Angle of attack))^2)*cos(Angle of attack)
C<sub>L</sub>=2*((sin(α))^2)*cos(α)
More formulas
Mass flux incident on a surface area GO
Time rate of change of momentum of the mass flux GO
Force F exerted on the surface GO
Coefficient of lift equation with coefficient of normal force GO
Coefficient of drag equation with coefficient of normal force GO
Coefficient of drag equation with angle of attack GO
Lift force with angle of attack GO
Drag force with angle of attack GO
Modified Newtonian Law GO
Maximum Pressure coefficient GO
exact normal shock-wave maximum coefficient of pressure GO
Pressure coefficient for slender 2-D bodies GO
Pressure coefficient for slender bodies of revolution GO

What is angle of attack?

In fluid dynamics, angle of attack is the angle between a reference line on a body and the vector representing the relative motion between the body and the fluid through which it is moving.

How to Calculate Coefficient of lift equation with angle of attack?

Coefficient of lift equation with angle of attack calculator uses lift coefficient=2*((sin(Angle of attack))^2)*cos(Angle of attack) to calculate the lift coefficient, The Coefficient of lift equation with angle of attack formula is defined as the double the product of square of sine angle of attack and cosine of angle of attack. lift coefficient and is denoted by CL symbol.

How to calculate Coefficient of lift equation with angle of attack using this online calculator? To use this online calculator for Coefficient of lift equation with angle of attack, enter Angle of attack (α) and hit the calculate button. Here is how the Coefficient of lift equation with angle of attack calculation can be explained with given input values -> 0.059391 = 2*((sin(10))^2)*cos(10).

FAQ

What is Coefficient of lift equation with angle of attack?
The Coefficient of lift equation with angle of attack formula is defined as the double the product of square of sine angle of attack and cosine of angle of attack and is represented as CL=2*((sin(α))^2)*cos(α) or lift coefficient=2*((sin(Angle of attack))^2)*cos(Angle of attack). Angle of attack is the angle between a reference line on a body and the vector representing the relative motion between the body and the fluid through which it is moving. .
How to calculate Coefficient of lift equation with angle of attack?
The Coefficient of lift equation with angle of attack formula is defined as the double the product of square of sine angle of attack and cosine of angle of attack is calculated using lift coefficient=2*((sin(Angle of attack))^2)*cos(Angle of attack). To calculate Coefficient of lift equation with angle of attack, you need Angle of attack (α). With our tool, you need to enter the respective value for Angle of attack 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 Angle of attack. 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*Weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area)
  • 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)
  • lift coefficient=(2*pi*Tangential Velocity)/Freestream Velocity
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