Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has created this Calculator and 300+ more calculators!
Rushi Shah
K J Somaiya College of Engineering (K J Somaiya), Mumbai
Rushi Shah has verified this Calculator and 100+ more calculators!

11 Other formulas that you can solve using the same Inputs

Diagonal of a Rectangle when breadth and area are given
Diagonal=sqrt(((Area)^2/(Breadth)^2)+(Breadth)^2) GO
Diagonal of a Rectangle when length and area are given
Diagonal=sqrt(((Area)^2/(Length)^2)+(Length)^2) GO
Side of a Kite when other side and area are given
Side A=(Area*cosec(Angle Between Sides))/Side B GO
Perimeter of rectangle when area and rectangle length are given
Perimeter=(2*Area+2*(Length)^2)/Length GO
Buoyant Force
Buoyant Force=Pressure*Area GO
Perimeter of a square when area is given
Perimeter=4*sqrt(Area) GO
Diagonal of a Square when area is given
Diagonal=sqrt(2*Area) GO
Length of rectangle when area and breadth are given
Length=Area/Breadth GO
Breadth of rectangle when area and length are given
Breadth=Area/Length GO
Pressure when force and area are given
Pressure=Force/Area GO
Stress
Stress=Force/Area 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 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 Formula

lift coefficient=Lift force/(Dynamic Pressure*Area)
C<sub>L</sub>=L/(P<sub>dynamic*A)
More formulas
Mach number GO
Dynamic pressure GO
Lift Force GO
Coefficient of drag GO
Drag force GO
Dynamic pressure based on coefficient of lift GO
Normal Force Coefficient GO
Deflection angle GO
Moment coefficient GO
Shear-stress distribution. GO
Axial force coefficient GO
Fourier’s law of heat conduction GO
Hypersonic similarity parameter GO
Coefficient of pressure with similarity parameters GO
Pressure ratio for high Mach number GO
Mach ratio at high mach number GO
Pressure ratio having high mach number with similarity constant GO
Newtonian sine-squared law for pressure coefficient GO
Supersonic expression for pressure coefficient on a surface with local deflection angle θ GO

What is a lift coefficient?

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

How to Calculate lift coefficient?

lift coefficient calculator uses lift coefficient=Lift force/(Dynamic Pressure*Area) to calculate the lift coefficient, The lift coefficient formula is defined as the ratio of lift force action the body to the product of dynamic pressure of fluid and reference area. lift coefficient and is denoted by CL symbol.

How to calculate lift coefficient using this online calculator? To use this online calculator for lift coefficient, enter Lift force (L), Dynamic Pressure (Pdynamic) and Area (A) and hit the calculate button. Here is how the lift coefficient calculation can be explained with given input values -> 0.02 = 10/(10*50).

FAQ

What is lift coefficient?
The lift coefficient formula is defined as the ratio of lift force action the body to the product of dynamic pressure of fluid and reference area and is represented as CL=L/(Pdynamic*A) or lift coefficient=Lift force/(Dynamic Pressure*Area). The lift force, lifting force or simply lift is the sum of all the forces on a body that force it to move perpendicular to the direction of flow, Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid and The area is the amount of two-dimensional space taken up by an object.
How to calculate lift coefficient?
The lift coefficient formula is defined as the ratio of lift force action the body to the product of dynamic pressure of fluid and reference area is calculated using lift coefficient=Lift force/(Dynamic Pressure*Area). To calculate lift coefficient, you need Lift force (L), Dynamic Pressure (Pdynamic) and Area (A). With our tool, you need to enter the respective value for Lift force, Dynamic Pressure and 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 Lift force, Dynamic Pressure and Area. We can use 11 other way(s) to calculate the same, which is/are as follows -
  • 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*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)
Share Image
Let Others Know
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!