Minimum Flight Velocity Calculator

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High Load Factor Maneuver

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✖Aircraft weight is the total aircraft weight at any moment during the flight or ground operation.ⓘ Aircraft weight [W]			+10% -10%
✖Aircraft Gross Wing Area calculated by looking at the wing from a top-down view and measuring the area of the wing.ⓘ Aircraft Gross Wing Area [5]			+10% -10%
✖Air Density denoted ρ, is the mass per unit volume of Earth's atmosphere.ⓘ Air Density [ρ]			+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]			+10% -10%

✖Minimum Flight Velocity is the velocity of the aircraft such that air passes over the wings fast enough for the aircraft to sustain constant altitude.ⓘ Minimum Flight Velocity [V_min]

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Formula

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Minimum Flight Velocity

Formula

`"V"_{"min"} = sqrt(("W"/"5")*(2/("ρ"))*(1/"C"_{"L"}))`

Example

`"589.9388m/s"=sqrt(("1800N"/"4m²")*(2/("1.293kg/m³"))*(1/"0.002"))`

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Minimum Flight Velocity Solution

STEP 0: Pre-Calculation Summary

Formula Used

Minimum Flight Velocity = sqrt((Aircraft weight/Aircraft Gross Wing Area)*(2/(Air Density))*(1/Lift Coefficient))
V_min = sqrt((W/5)*(2/(ρ))*(1/C_L))
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

Minimum Flight Velocity - (Measured in Meter per Second) - Minimum Flight Velocity is the velocity of the aircraft such that air passes over the wings fast enough for the aircraft to sustain constant altitude.
Aircraft weight - (Measured in Newton) - Aircraft weight is the total aircraft weight at any moment during the flight or ground operation.
Aircraft Gross Wing Area - (Measured in Square Meter) - Aircraft Gross Wing Area calculated by looking at the wing from a top-down view and measuring the area of the wing.
Air Density - (Measured in Kilogram per Cubic Meter) - Air Density denoted ρ, is the mass per unit volume of Earth's atmosphere.
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.

STEP 1: Convert Input(s) to Base Unit

Aircraft weight: 1800 Newton --> 1800 Newton No Conversion Required
Aircraft Gross Wing Area: 4 Square Meter --> 4 Square Meter No Conversion Required
Air Density: 1.293 Kilogram per Cubic Meter --> 1.293 Kilogram per Cubic Meter No Conversion Required
Lift Coefficient: 0.002 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

V_min = sqrt((W/5)*(2/(ρ))*(1/C_L)) --> sqrt((1800/4)*(2/(1.293))*(1/0.002))

Evaluating ... ...

V_min = 589.938846175922

STEP 3: Convert Result to Output's Unit

589.938846175922 Meter per Second --> No Conversion Required

FINAL ANSWER

589.938846175922 ≈ 589.9388 Meter per Second <-- Minimum Flight Velocity

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Aircraft Performance » Maneuvering Flight » High Load Factor Maneuver » Minimum Flight Velocity

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Created by Kaki Varun Krishna

Mahatma Gandhi Institute of Technology (MGIT), Hyderabad

Kaki Varun Krishna has created this Calculator and 25+ more calculators!

Verified by Saurabh Patil

Shri Govindram Seksaria Institute of Technology and Science (SGSITS ), Indore

Saurabh Patil has verified this Calculator and 25+ more calculators!

< 25 High Load Factor Maneuver Calculators

Turn rate for given lift coefficient

Go Turn Rate = [g]*(sqrt((Reference Area*Freestream density*Lift Coefficient*Load factor)/(2*Aircraft weight)))

Turn rate for given wing loading

Go Turn Rate = [g]*(sqrt(Freestream density*Lift Coefficient*Load factor/(2*Wing Loading)))

Lift Coefficient for given turn rate

Go Lift Coefficient = 2*Aircraft weight*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area)

Lift Coefficient for given Turn Radius

Go Lift Coefficient = Aircraft weight/(0.5*Freestream density*Reference Area*[g]*Turn Radius)

Radius of turn for given lift coefficient

Go Turn Radius = 2*Aircraft weight/(Freestream density*Reference Area*[g]*Lift Coefficient)

Wing loading for given turn rate

Go Wing Loading = ([g]^2)*Freestream density*Lift Coefficient*Load factor/(2*(Turn Rate^2))

Lift Coefficient for given wing loading and turn radius

Go Lift Coefficient = 2*Wing Loading/(Freestream density*Turn Radius*[g])

Radius of turn for given wing loading

Go Turn Radius = 2*Wing Loading/(Freestream density*Lift Coefficient*[g])

Wing loading for given turn radius

Go Wing Loading = (Turn Radius*Freestream density*Lift Coefficient*[g])/2

Velocity for given pull-up maneuver radius

Go Velocity = sqrt(Turn Radius*[g]*(Load factor-1))

Velocity given Pull-down Maneuver Radius

Go Velocity = sqrt(Turn Radius*[g]*(Load factor+1))

Velocity given Turn Radius for High Load Factor

Go Velocity = sqrt(Turn Radius*Load factor*[g])

Change in Angle of Attack due to Upward Gust

Go Change in Angle of Attack = tan(Gust Velocity/Flight Velocity)

Load Factor given Pull-down Maneuver Radius

Go Load factor = ((Velocity^2)/(Turn Radius*[g]))-1

Load Factor given Pull-UP Maneuver Radius

Go Load factor = 1+((Velocity^2)/(Turn Radius*[g]))

Pull-down maneuver radius

Go Turn Radius = (Velocity^2)/([g]*(Load factor+1))

Pull-up maneuver radius

Go Turn Radius = (Velocity^2)/([g]*(Load factor-1))

Load factor for given turn radius for high-performance fighter aircraft

Go Load factor = (Velocity^2)/([g]*Turn Radius)

Turn radius for high load factor

Go Turn Radius = (Velocity^2)/([g]*Load factor)

Velocity for given pull-up maneuver rate

Go Velocity = [g]*(Load factor-1)/Turn Rate

Load Factor given Pull-Up Maneuver Rate

Go Load factor = 1+(Velocity*Turn Rate/[g])

Pull-down maneuver rate

Go Turn Rate = [g]*(1+Load factor)/Velocity

Pull-up maneuver rate

Go Turn Rate = [g]*(Load factor-1)/Velocity

Load factor for given turn rate for high-performance fighter aircraft

Go Load factor = Velocity*Turn Rate/[g]

Turn rate for high load factor

Go Turn Rate = [g]*Load factor/Velocity

Minimum Flight Velocity Formula

Minimum Flight Velocity = sqrt((Aircraft weight/Aircraft Gross Wing Area)*(2/(Air Density))*(1/Lift Coefficient))
V_min = sqrt((W/5)*(2/(ρ))*(1/C_L))

What is the stall velocity for small aircrafts?

For small planes and unmanned drones the stall velocity or minimum flight velocity can be less than 50km/h (31mph).

What is stall velocity dependent on and what indicators are used to predict them?

The stall velocity is dependent on the airplane's weight, altitude, Wing span, coefficient of lift, Density, Airspeed Indicators are used to predict stall conditions in airplanes

How to Calculate Minimum Flight Velocity?

Minimum Flight Velocity calculator uses Minimum Flight Velocity = sqrt((Aircraft weight/Aircraft Gross Wing Area)*(2/(Air Density))*(1/Lift Coefficient)) to calculate the Minimum Flight Velocity, Minimum Flight Velocity, in terms of aerodynamics, also called as 'stall speed', is the velocity of the aircraft such that air passes over the wings fast enough for the aircraft to sustain constant altitude. Minimum Flight Velocity is denoted by V_min symbol.

How to calculate Minimum Flight Velocity using this online calculator? To use this online calculator for Minimum Flight Velocity, enter Aircraft weight (W), Aircraft Gross Wing Area (5), Air Density (ρ) & Lift Coefficient (C_L) and hit the calculate button. Here is how the Minimum Flight Velocity calculation can be explained with given input values -> 58.99388 = sqrt((Weight_of_aircraft_/4)*(2/(1.293))*(1/0.002)).

FAQ

What is Minimum Flight Velocity?

Minimum Flight Velocity, in terms of aerodynamics, also called as 'stall speed', is the velocity of the aircraft such that air passes over the wings fast enough for the aircraft to sustain constant altitude and is represented as V_min = sqrt((W/5)*(2/(ρ))*(1/C_L)) or Minimum Flight Velocity = sqrt((Aircraft weight/Aircraft Gross Wing Area)*(2/(Air Density))*(1/Lift Coefficient)). Aircraft weight is the total aircraft weight at any moment during the flight or ground operation, Aircraft Gross Wing Area calculated by looking at the wing from a top-down view and measuring the area of the wing, Air Density denoted ρ, is the mass per unit volume of Earth's atmosphere & 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.

How to calculate Minimum Flight Velocity?

Minimum Flight Velocity, in terms of aerodynamics, also called as 'stall speed', is the velocity of the aircraft such that air passes over the wings fast enough for the aircraft to sustain constant altitude is calculated using Minimum Flight Velocity = sqrt((Aircraft weight/Aircraft Gross Wing Area)*(2/(Air Density))*(1/Lift Coefficient)). To calculate Minimum Flight Velocity, you need Aircraft weight (W), Aircraft Gross Wing Area (5), Air Density (ρ) & Lift Coefficient (C_L). With our tool, you need to enter the respective value for Aircraft weight, Aircraft Gross Wing Area, Air Density & Lift Coefficient 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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