Stall velocity for given weight 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%
✖Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attack.ⓘ Maximum Lift Coefficient [C_L,max]			+10% -10%

✖Stall Velocity is defined as the velocity of an airplane in steady flight at its maximum lift coefficient.ⓘ Stall velocity for given weight [V_stall]

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Formula

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Stall velocity for given weight

Formula

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

Example

`"148.2249m/s"=sqrt((2*"60.5N")/("1.225kg/m³"*"5.08m²"*"0.000885"))`

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Stall velocity for given weight Solution

STEP 0: Pre-Calculation Summary

Formula Used

Stall Velocity = sqrt((2*Weight)/(Freestream Density*Reference Area*Maximum Lift Coefficient))
V_stall = sqrt((2*W)/(ρ_∞*S*C_L,max))
This formula uses 1 Functions, 5 Variables

Functions Used

sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)

Variables Used

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.
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.
Maximum Lift Coefficient - Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attack.

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
Maximum Lift Coefficient: 0.000885 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

V_stall = sqrt((2*W)/(ρ_∞*S*C_L,max)) --> sqrt((2*60.5)/(1.225*5.08*0.000885))

Evaluating ... ...

V_stall = 148.224894299244

STEP 3: Convert Result to Output's Unit

148.224894299244 Meter per Second --> No Conversion Required

FINAL ANSWER

148.224894299244 ≈ 148.2249 Meter per Second <-- Stall Velocity

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Aircraft Performance » Take-off and Landing » Aerospace » Take-Off » Stall velocity for given weight

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Created by Vinay Mishra

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

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Indian Institute of Technology (IIT), Bombay

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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 = (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 Aircraft Thrust = 1.44*(Weight^2)/([g]*Freestream Density*Reference Area*Maximum Lift Coefficient*Liftoff Distance)

Liftoff distance

Go Liftoff Distance = 1.44*(Weight^2)/([g]*Freestream Density*Reference Area*Maximum Lift Coefficient*Aircraft Thrust)

Liftoff velocity for given weight

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

Stall velocity for given weight

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

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 liftoff velocity

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

Maximum Lift coefficient for given stall velocity

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

Coefficient of rolling friction during ground roll

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

Lift acting on aircraft during ground roll

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

Weight of aircraft during ground roll

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

Resistance force during ground roll

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

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

Stall velocity for given weight Formula

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

Why does stall speed increase in a turn?

When you turn, you need to increase your total lift to maintain altitude. You increase your total lift by increasing your angle of attack, which means you're closer to stall than you were in wings-level flight. And, your stall speed increases in proportion to the square root of your load factor.

How to Calculate Stall velocity for given weight?

Stall velocity for given weight calculator uses Stall Velocity = sqrt((2*Weight)/(Freestream Density*Reference Area*Maximum Lift Coefficient)) to calculate the Stall Velocity, Stall Velocity for Given Weight is a measure of the airspeed at which an aircraft wing stalls, calculated as a function of weight, free stream density, reference area, and maximum lift coefficient, providing a critical velocity threshold for safe flight operations. Stall Velocity is denoted by V_stall symbol.

How to calculate Stall velocity for given weight using this online calculator? To use this online calculator for Stall velocity for given weight, enter Weight (W), Freestream Density (ρ_∞), Reference Area (S) & Maximum Lift Coefficient (C_L,max) and hit the calculate button. Here is how the Stall velocity for given weight calculation can be explained with given input values -> 3.432818 = sqrt((2*60.5)/(1.225*5.08*0.000885)).

FAQ

What is Stall velocity for given weight?

Stall Velocity for Given Weight is a measure of the airspeed at which an aircraft wing stalls, calculated as a function of weight, free stream density, reference area, and maximum lift coefficient, providing a critical velocity threshold for safe flight operations and is represented as V_stall = sqrt((2*W)/(ρ_∞*S*C_L,max)) or Stall Velocity = sqrt((2*Weight)/(Freestream Density*Reference Area*Maximum Lift Coefficient)). 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 & Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attack.

How to calculate Stall velocity for given weight?

Stall Velocity for Given Weight is a measure of the airspeed at which an aircraft wing stalls, calculated as a function of weight, free stream density, reference area, and maximum lift coefficient, providing a critical velocity threshold for safe flight operations is calculated using Stall Velocity = sqrt((2*Weight)/(Freestream Density*Reference Area*Maximum Lift Coefficient)). To calculate Stall velocity for given weight, you need Weight (W), Freestream Density (ρ_∞), Reference Area (S) & Maximum Lift Coefficient (C_L,max). With our tool, you need to enter the respective value for Weight, Freestream Density, Reference Area & Maximum Lift Coefficient 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 Stall Velocity?

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

Stall Velocity = Liftoff velocity/1.2

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