Maximum Lift coefficient for given stall velocity Calculator

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✖Weight Newton is a vector quantity and defined as the product of mass and acceleration acting on that mass.ⓘ Weight Newton [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%
✖Stall Velocity is defined as the velocity of an airplane in steady flight at its maximum lift coefficient.ⓘ Stall Velocity [V_stall]			+10% -10%

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

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Formula

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Maximum Lift coefficient for given stall velocity

Formula

`"C"_{"L,max"} = 2*"W"/("ρ"_{"∞"}*"S"*("V"_{"stall"}^2))`

Example

`"0.000885"=2*"60.34N"/("1.225kg/m³"*"5.08m²"*(("148m/s")^2))`

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Maximum Lift coefficient for given stall velocity Solution

STEP 0: Pre-Calculation Summary

Formula Used

Maximum Lift Coefficient = 2*Weight Newton/(Freestream density*Reference Area*(Stall Velocity^2))
C_L,max = 2*W/(ρ_∞*S*(V_stall^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 Newton - (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.
Stall Velocity - (Measured in Meter per Second) - Stall Velocity is defined as the velocity of an airplane in steady flight at its maximum lift coefficient.

STEP 1: Convert Input(s) to Base Unit

Weight Newton: 60.34 Newton --> 60.34 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
Stall Velocity: 148 Meter per Second --> 148 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_L,max = 2*W/(ρ_∞*S*(V_stall^2)) --> 2*60.34/(1.225*5.08*(148^2))

Evaluating ... ...

C_L,max = 0.000885344043462792

STEP 3: Convert Result to Output's Unit

0.000885344043462792 --> No Conversion Required

FINAL ANSWER

0.000885344043462792 ≈ 0.000885 <-- Maximum Lift Coefficient

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

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

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< 15 Take-Off Calculators

Take Off Ground Run

Go Takeoff Ground Run = Weight Of Aircraft/(2*[g])*int((2*Velocity of Aircraft)/(Thrust Force-Drag Force-Reference Of Rolling Resistance Coefficient*(Weight Of Aircraft-Lift Force)),x,0,Aircraft Lift Off Speed)

Drag during ground effect

Go Drag Force = (Parasite Drag coefficient+(((Lift Coefficient^2)*Ground effect factor)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)))*(0.5*Freestream density*(Flight Velocity^2)*Reference Area)

Thrust for given liftoff distance

Go Thrust of an aircraft = 1.44*(Weight Newton^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Liftoff Distance)

Liftoff distance

Go Liftoff Distance = 1.44*(Weight Newton^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Thrust of an aircraft)

Liftoff velocity for given weight

Go Liftoff velocity = 1.2*(sqrt((2*Weight Newton)/(Freestream density*Reference Area*Maximum Lift Coefficient)))

Stall velocity for given weight

Go Stall Velocity = sqrt((2*Weight Newton)/(Freestream density*Reference Area*Maximum Lift Coefficient))

Maximum Lift coefficient for given liftoff velocity

Go Maximum Lift Coefficient = 2.88*Weight Newton/(Freestream density*Reference Area*(Liftoff velocity^2))

Ground effect factor

Go Ground effect factor = ((16*Height from Ground/Wingspan)^2)/(1+((16*Height from Ground/Wingspan)^2))

Maximum Lift coefficient for given stall velocity

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

Coefficient of rolling friction during ground roll

Go Coefficient of Rolling Friction = Rolling Resistance/(Weight Newton-Lift Force)

Lift acting on aircraft during ground roll

Go Lift Force = Weight Newton-(Rolling Resistance/Coefficient of Rolling Friction)

Weight of aircraft during ground roll

Go Weight Newton = (Rolling Resistance/Coefficient of Rolling Friction)+Lift Force

Resistance force during ground roll

Go Rolling Resistance = Coefficient of Rolling Friction*(Weight Newton-Lift Force)

Liftoff velocity for given stall velocity

Go Liftoff velocity = 1.2*Stall Velocity

Stall velocity for given liftoff velocity

Go Stall Velocity = Liftoff velocity/1.2

Maximum Lift coefficient for given stall velocity Formula

Maximum Lift Coefficient = 2*Weight Newton/(Freestream density*Reference Area*(Stall Velocity^2))
C_L,max = 2*W/(ρ_∞*S*(V_stall^2))

Does air density affect lift?

Lift and drag depend linearly on the density of the fluid. Halving the density halves the lift, halving the density halves the drag.

How to Calculate Maximum Lift coefficient for given stall velocity?

Maximum Lift coefficient for given stall velocity calculator uses Maximum Lift Coefficient = 2*Weight Newton/(Freestream density*Reference Area*(Stall Velocity^2)) to calculate the Maximum Lift Coefficient, The Maximum Lift coefficient for given stall velocity of an aircraft depends upon the instantaneous weight and altitude of the aircraft,To find the maximum lift coefficient for a given stall velocity, we need to consider the aerodynamic relationship between lift, velocity, and the wing's characteristics. Maximum Lift Coefficient is denoted by C_L,max symbol.

How to calculate Maximum Lift coefficient for given stall velocity using this online calculator? To use this online calculator for Maximum Lift coefficient for given stall velocity, enter Weight Newton (W), Freestream density (ρ_∞), Reference Area (S) & Stall Velocity (V_stall) and hit the calculate button. Here is how the Maximum Lift coefficient for given stall velocity calculation can be explained with given input values -> 0.003229 = 2*60.34/(1.225*5.08*(stall_velocity^2)).

FAQ

What is Maximum Lift coefficient for given stall velocity?

The Maximum Lift coefficient for given stall velocity of an aircraft depends upon the instantaneous weight and altitude of the aircraft,To find the maximum lift coefficient for a given stall velocity, we need to consider the aerodynamic relationship between lift, velocity, and the wing's characteristics and is represented as C_L,max = 2*W/(ρ_∞*S*(V_stall^2)) or Maximum Lift Coefficient = 2*Weight Newton/(Freestream density*Reference Area*(Stall 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 & Stall Velocity is defined as the velocity of an airplane in steady flight at its maximum lift coefficient.

How to calculate Maximum Lift coefficient for given stall velocity?

The Maximum Lift coefficient for given stall velocity of an aircraft depends upon the instantaneous weight and altitude of the aircraft,To find the maximum lift coefficient for a given stall velocity, we need to consider the aerodynamic relationship between lift, velocity, and the wing's characteristics is calculated using Maximum Lift Coefficient = 2*Weight Newton/(Freestream density*Reference Area*(Stall Velocity^2)). To calculate Maximum Lift coefficient for given stall velocity, you need Weight Newton (W), Freestream density (ρ_∞), Reference Area (S) & Stall Velocity (V_stall). With our tool, you need to enter the respective value for Weight Newton, Freestream density, Reference Area & Stall 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 Newton, Freestream density, Reference Area & Stall Velocity. We can use 1 other way(s) to calculate the same, which is/are as follows -

Maximum Lift Coefficient = 2.88*Weight Newton/(Freestream density*Reference Area*(Liftoff velocity^2))

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