Lift Coefficient Calculator

✖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.ⓘ Lift Force [F_L]			+10% -10%
✖Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.ⓘ Dynamic Pressure [q]			+10% -10%
✖Area for flow decreases velocity increases and vice versa. For subsonic flows, M < 1, the behavior resembles that for incompressible flows.ⓘ Area for Flow [A]			+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 [C_L]

⎘ Copy

👎

Formula

✖

Lift Coefficient

Formula

`"C"_{"L"} = "F"_{"L"}/("q"*"A")`

Example

`"0.021"="10.5N"/("10Pa"*"50m²")`

Calculator

LaTeX

Reset

👍

Download Hypersonic Flow Formula PDF

Lift Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift Coefficient = Lift Force/(Dynamic Pressure*Area for Flow)
C_L = F_L/(q*A)
This formula uses 4 Variables

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.
Lift Force - (Measured in Newton) - 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 - (Measured in Pascal) - Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.
Area for Flow - (Measured in Square Meter) - Area for flow decreases velocity increases and vice versa. For subsonic flows, M < 1, the behavior resembles that for incompressible flows.

STEP 1: Convert Input(s) to Base Unit

Lift Force: 10.5 Newton --> 10.5 Newton No Conversion Required
Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
Area for Flow: 50 Square Meter --> 50 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_L = F_L/(q*A) --> 10.5/(10*50)

Evaluating ... ...

C_L = 0.021

STEP 3: Convert Result to Output's Unit

0.021 --> No Conversion Required

FINAL ANSWER

0.021 <-- Lift Coefficient

(Calculation completed in 00.004 seconds)

You are here -

Home » Engineering » Mechanical » Fluid Mechanics » Hypersonic Flow » Hypersonic Flow Parameters » Lift Coefficient

Credits

Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has created this Calculator and 300+ more calculators!

Verified by Rushi Shah

K J Somaiya College of Engineering (K J Somaiya), Mumbai

Rushi Shah has verified this Calculator and 200+ more calculators!

< 20 Hypersonic Flow Parameters Calculators

Coefficient of Pressure with Similarity Parameters

Go Pressure Coefficient = 2*Flow Deflection angle^2*((Specific Heat Ratio+1)/4+sqrt(((Specific Heat Ratio+1)/4)^2+1/Hypersonic Similarity Parameter^2))

Pressure Ratio having High Mach Number with Similarity Constant

Go Pressure Ratio = (1-((Specific Heat Ratio-1)/2)*Hypersonic Similarity Parameter)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))

Mach Number with Fluids

Go Mach Number = Fluid Velocity/(sqrt(Specific Heat Ratio*Universal Gas Constant*Final Temperature))

Pressure Ratio for High Mach Number

Go Pressure Ratio = (Mach Number ahead of shock/Mach Number behind shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))

Moment Coefficient

Go Moment Coefficient = Moment/(Dynamic Pressure*Area for Flow*Chord Length)

Deflection Angle

Go Deflection Angle = 2/(Specific Heat Ratio-1)*(1/Mach Number ahead of shock-1/Mach Number behind shock)

Normal Force Coefficient

Go Coefficient of Force = Normal Force/(Dynamic Pressure*Area for Flow)

Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle

Go Pressure Coefficient = (2*Deflection Angle)/(sqrt(Mach Number^2-1))

Dynamic Pressure given Coefficient of Lift

Go Dynamic Pressure = Lift Force/(Lift Coefficient*Area for Flow)

Coefficient of Drag

Go Drag Coefficient = Drag Force/(Dynamic Pressure*Area for Flow)

Dynamic Pressure

Go Dynamic Pressure = Drag Force/(Drag Coefficient*Area for Flow)

Lift Coefficient

Go Lift Coefficient = Lift Force/(Dynamic Pressure*Area for Flow)

Axial Force Coefficient

Go Coefficient of Force = Force/(Dynamic Pressure*Area for Flow)

Drag Force

Go Drag Force = Drag Coefficient*Dynamic Pressure*Area for Flow

Lift Force

Go Lift Force = Lift Coefficient*Dynamic Pressure*Area for Flow

Mach Ratio at High Mach Number

Go Mach Ratio = 1-Hypersonic Similarity Parameter*((Specific Heat Ratio-1)/2)

Hypersonic Similarity Parameter

Go Hypersonic Similarity Parameter = Mach Number*Flow Deflection angle

Shear-Stress Distribution

Go Shear Stress = Viscosity Coefficient*Velocity Gradient

Fourier's Law of Heat Conduction

Go Heat Flux = Thermal Conductivity*Temperature Gradient

Newtonian Sine Squared Law for Pressure Coefficient

Go Pressure Coefficient = 2*sin(Deflection Angle)^2

Lift Coefficient Formula

Lift Coefficient = Lift Force/(Dynamic Pressure*Area for Flow)
C_L = F_L/(q*A)

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 for Flow) 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 is denoted by C_L symbol.

How to calculate Lift Coefficient using this online calculator? To use this online calculator for Lift Coefficient, enter Lift Force (F_L), Dynamic Pressure (q) & Area for Flow (A) and hit the calculate button. Here is how the Lift Coefficient calculation can be explained with given input values -> 0.021 = 10.5/(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 C_L = F_L/(q*A) or Lift Coefficient = Lift Force/(Dynamic Pressure*Area for Flow). 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 & Area for flow decreases velocity increases and vice versa. For subsonic flows, M < 1, the behavior resembles that for incompressible flows.

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 for Flow). To calculate Lift Coefficient, you need Lift Force (F_L), Dynamic Pressure (q) & Area for Flow (A). With our tool, you need to enter the respective value for Lift Force, Dynamic Pressure & Area for Flow and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

Home

FREE PDFs

🔍 Search