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Sri sivasubramaniyanadar college of engineering (ssn college of engineering), Chennai
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Mahatma Gandhi Institute of Technology (MGIT), Hyderabad
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The Modern Lift Equation Solution

STEP 0: Pre-Calculation Summary
Formula Used
Lift on airfoil = (Lift Coefficient* Air Density* Aircraft Gross Wing Area* Fluid Velocity)/2
L = (CL* ρ* S* uFluid)/2
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.
Air Density - Air Density is the density of wind or air in the atmosphere. (Measured in Gram per Meter³)
Aircraft Gross Wing Area - Aircraft Gross Wing Area calculated by looking at the wing from a top-down view and measuring the area of the wing. (Measured in Square Meter)
Fluid Velocity - Fluid velocity is the volume of fluid flowing in the given vessel per unit cross sectional area. (Measured in Meter per Second)
STEP 1: Convert Input(s) to Base Unit
Lift Coefficient: 5 --> No Conversion Required
Air Density: 1201 Gram per Meter³ --> 1.201 Kilogram per Meter³ (Check conversion here)
Aircraft Gross Wing Area: 4 Square Meter --> 4 Square Meter No Conversion Required
Fluid Velocity: 12 Meter per Second --> 12 Meter per Second No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
L = (CL* ρ* S* uFluid)/2 --> (5* 1.201* 4* 12)/2
Evaluating ... ...
L = 144.12
STEP 3: Convert Result to Output's Unit
144.12 Newton --> No Conversion Required
FINAL ANSWER
144.12 Newton <-- Lift on airfoil
(Calculation completed in 00.016 seconds)

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The Modern Lift Equation Formula

Lift on airfoil = (Lift Coefficient* Air Density* Aircraft Gross Wing Area* Fluid Velocity)/2
L = (CL* ρ* S* uFluid)/2

What is 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.

What is Wing Area?

The wing area is a projected area and is almost half of the total surface area. In aerodynamics, the surface area of a wing is calculated by looking at the wing from a top-down view and measuring the area of the wing. This surface area is also known as the planform area.

How to Calculate The Modern Lift Equation?

The Modern Lift Equation calculator uses Lift on airfoil = (Lift Coefficient* Air Density* Aircraft Gross Wing Area* Fluid Velocity)/2 to calculate the Lift on airfoil, The Modern Lift Equation states that lift L is equal to the lift coefficient times the air-density times half of the velocity squared times the wing area. Lift on airfoil is denoted by L symbol.

How to calculate The Modern Lift Equation using this online calculator? To use this online calculator for The Modern Lift Equation, enter Lift Coefficient (CL), Air Density (ρ), Aircraft Gross Wing Area (S) & Fluid Velocity (uFluid) and hit the calculate button. Here is how the The Modern Lift Equation calculation can be explained with given input values -> 144.12 = (5* 1.201* 4* 12)/2 .

FAQ

What is The Modern Lift Equation?
The Modern Lift Equation states that lift L is equal to the lift coefficient times the air-density times half of the velocity squared times the wing area and is represented as L = (CL* ρ* S* uFluid)/2 or Lift on airfoil = (Lift Coefficient* Air Density* Aircraft Gross Wing Area* Fluid Velocity)/2 . 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, Air Density is the density of wind or air in the atmosphere, Aircraft Gross Wing Area calculated by looking at the wing from a top-down view and measuring the area of the wing & Fluid velocity is the volume of fluid flowing in the given vessel per unit cross sectional area.
How to calculate The Modern Lift Equation?
The Modern Lift Equation states that lift L is equal to the lift coefficient times the air-density times half of the velocity squared times the wing area is calculated using Lift on airfoil = (Lift Coefficient* Air Density* Aircraft Gross Wing Area* Fluid Velocity)/2 . To calculate The Modern Lift Equation, you need Lift Coefficient (CL), Air Density (ρ), Aircraft Gross Wing Area (S) & Fluid Velocity (uFluid). With our tool, you need to enter the respective value for Lift Coefficient, Air Density, Aircraft Gross Wing Area & Fluid Velocity 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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