Maximum Lift coefficient for given liftoff velocity Calculator

✖Weight Newton is a vector quantity and defined as the product of mass and acceleration acting on that mass.ⓘ Weight [W]			+10% -10%
✖Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.ⓘ Freestream Density [ρ_∞]			+10% -10%
✖The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+10% -10%
✖Liftoff velocity is defined as the velocity of the aircraft at which it first becomes airborne.ⓘ Liftoff velocity [V_LO]			+10% -10%

✖Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attack.ⓘ Maximum Lift coefficient for given liftoff velocity [C_L,max]

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Maximum Lift coefficient for given liftoff velocity Solution

STEP 0: Pre-Calculation Summary

Formula Used

Maximum Lift Coefficient = 2.88*Weight/(Freestream Density*Reference Area*(Liftoff velocity^2))
C_L,max = 2.88*W/(ρ_∞*S*(V_LO^2))
This formula uses 5 Variables

Variables Used

Maximum Lift Coefficient - Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attack.
Weight - (Measured in Newton) - Weight Newton is a vector quantity and defined as the product of mass and acceleration acting on that mass.
Freestream Density - (Measured in Kilogram per Cubic Meter) - Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
Liftoff velocity - (Measured in Meter per Second) - Liftoff velocity is defined as the velocity of the aircraft at which it first becomes airborne.

STEP 1: Convert Input(s) to Base Unit

Weight: 60.5 Newton --> 60.5 Newton No Conversion Required
Freestream Density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Liftoff velocity: 177.6 Meter per Second --> 177.6 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_L,max = 2.88*W/(ρ_∞*S*(V_LO^2)) --> 2.88*60.5/(1.225*5.08*(177.6^2))

Evaluating ... ...

C_L,max = 0.000887691657764317

STEP 3: Convert Result to Output's Unit

0.000887691657764317 --> No Conversion Required

FINAL ANSWER

0.000887691657764317 ≈ 0.000888 <-- Maximum Lift Coefficient

(Calculation completed in 00.004 seconds)

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Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

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Maximum Lift coefficient for given liftoff velocity Formula

LaTeX Go

Maximum Lift Coefficient = 2.88*Weight/(Freestream Density*Reference Area*(Liftoff velocity^2))
C_L,max = 2.88*W/(ρ_∞*S*(V_LO^2))

What is a high density altitude?

A “high” density altitude means that air density is reduced, which has an adverse impact on aircraft performance.

How to Calculate Maximum Lift coefficient for given liftoff velocity?

Maximum Lift coefficient for given liftoff velocity calculator uses Maximum Lift Coefficient = 2.88*Weight/(Freestream Density*Reference Area*(Liftoff velocity^2)) to calculate the Maximum Lift Coefficient, Maximum Lift Coefficient for Given Liftoff Velocity is a measure that represents the maximum lift force an aircraft can generate at a given liftoff velocity, influenced by its weight, free stream density, reference area, and velocity, providing a critical design parameter for aircraft performance optimization. Maximum Lift Coefficient is denoted by C_L,max symbol.

How to calculate Maximum Lift coefficient for given liftoff velocity using this online calculator? To use this online calculator for Maximum Lift coefficient for given liftoff velocity, enter Weight (W), Freestream Density (ρ_∞), Reference Area (S) & Liftoff velocity (V_LO) and hit the calculate button. Here is how the Maximum Lift coefficient for given liftoff velocity calculation can be explained with given input values -> 0.000888 = 2.88*60.5/(1.225*5.08*(177.6^2)).

FAQ

What is Maximum Lift coefficient for given liftoff velocity?

Maximum Lift Coefficient for Given Liftoff Velocity is a measure that represents the maximum lift force an aircraft can generate at a given liftoff velocity, influenced by its weight, free stream density, reference area, and velocity, providing a critical design parameter for aircraft performance optimization and is represented as C_L,max = 2.88*W/(ρ_∞*S*(V_LO^2)) or Maximum Lift Coefficient = 2.88*Weight/(Freestream Density*Reference Area*(Liftoff velocity^2)). Weight Newton is a vector quantity and defined as the product of mass and acceleration acting on that mass, Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area & Liftoff velocity is defined as the velocity of the aircraft at which it first becomes airborne.

How to calculate Maximum Lift coefficient for given liftoff velocity?

Maximum Lift Coefficient for Given Liftoff Velocity is a measure that represents the maximum lift force an aircraft can generate at a given liftoff velocity, influenced by its weight, free stream density, reference area, and velocity, providing a critical design parameter for aircraft performance optimization is calculated using Maximum Lift Coefficient = 2.88*Weight/(Freestream Density*Reference Area*(Liftoff velocity^2)). To calculate Maximum Lift coefficient for given liftoff velocity, you need Weight (W), Freestream Density (ρ_∞), Reference Area (S) & Liftoff velocity (V_LO). With our tool, you need to enter the respective value for Weight, Freestream Density, Reference Area & Liftoff velocity 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 Maximum Lift Coefficient?

In this formula, Maximum Lift Coefficient uses Weight, Freestream Density, Reference Area & Liftoff velocity. We can use 1 other way(s) to calculate the same, which is/are as follows -

Maximum Lift Coefficient = 2*Weight/(Freestream Density*Reference Area*(Stall Velocity^2))

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