## Credits

Mahatma Gandhi Institute of Technology (MGIT), Hyderabad
Kaki Varun Krishna has created this Calculator and 25+ more calculators!
Shri Govindram Seksaria Institute of Technology and Science (SGSITS ), Indore
Saurabh Patil has verified this Calculator and 25+ more calculators!

## 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))
Vmin = sqrt((W/S)*(2/(ρ))*(1/CL))
This formula uses 1 Functions, 4 Variables
Functions Used
sqrt - Squre root function, sqrt(Number)
Variables Used
Aircraft weight - Aircraft weight is the total aircraft weight at any moment during the flight or ground operation. (Measured in Newton)
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)
Air Density - Air Density denoted ρ, is the mass per unit volume of Earth's atmosphere. (Measured in Kilogram per Meter³)
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: 1000 Newton --> 1000 Newton No Conversion Required
Aircraft Gross Wing Area: 4 Square Meter --> 4 Square Meter No Conversion Required
Air Density: 1.293 Kilogram per Meter³ --> 1.293 Kilogram per Meter³ No Conversion Required
Lift Coefficient: 5 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Vmin = sqrt((W/S)*(2/(ρ))*(1/CL)) --> sqrt((1000/4)*(2/(1.293))*(1/5))
Evaluating ... ...
Vmin = 8.79428908411436
STEP 3: Convert Result to Output's Unit
8.79428908411436 Meter per Second --> No Conversion Required
8.79428908411436 Meter per Second <-- Minimum Flight Velocity
(Calculation completed in 00.016 seconds)

## < 10+ Flight Envelope Calculators

Lift Coefficient for given turn rate
Lift Coefficient = 2*Weight of body*(Turn Rate^2)/(([g]^2)*Freestream density*Load factor*Reference Area) Go
Velocity for given turn rate for high load factor
Velocity = [g]*Load factor/Turn Rate Go
Turn rate for high load factor
Turn Rate = [g]*Load factor/Velocity Go

### Minimum Flight Velocity Formula

Minimum Flight Velocity = sqrt((Aircraft weight/Aircraft Gross Wing Area)*(2/(Air Density))*(1/Lift Coefficient))
Vmin = sqrt((W/S)*(2/(ρ))*(1/CL))

## 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 Vmin 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 (S), Air Density (ρ) & Lift Coefficient (CL) and hit the calculate button. Here is how the Minimum Flight Velocity calculation can be explained with given input values -> 8.794289 = sqrt((1000/4)*(2/(1.293))*(1/5)).

### 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 Vmin = sqrt((W/S)*(2/(ρ))*(1/CL)) 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 (S), Air Density (ρ) & Lift Coefficient (CL). 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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