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]

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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)

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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

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< Hypersonic Flow Parameters Calculators

Coefficient of Pressure with Similarity Parameters

LaTeX 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))

Deflection Angle

LaTeX Go Deflection Angle = 2/(Specific Heat Ratio-1)*(1/Mach Number ahead of Shock-1/Mach Number Behind Shock)

Coefficient of Drag

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

Axial Force Coefficient

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

Lift Coefficient Formula

LaTeX Go

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, Lift Coefficient formula is defined as a dimensionless quantity that represents the lift force per unit area exerted on an object in a hypersonic flow, providing a measure of the aerodynamic efficiency of an aircraft or spacecraft during high-speed flight. 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?

Lift Coefficient formula is defined as a dimensionless quantity that represents the lift force per unit area exerted on an object in a hypersonic flow, providing a measure of the aerodynamic efficiency of an aircraft or spacecraft during high-speed flight 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?

Lift Coefficient formula is defined as a dimensionless quantity that represents the lift force per unit area exerted on an object in a hypersonic flow, providing a measure of the aerodynamic efficiency of an aircraft or spacecraft during high-speed flight 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.

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