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`V = sqrt((M*g)/(½*A*ρ*CL) )`

Enter a value for all fields

The **Velocity Needed for Takeoff **calculator computes the velocity required to create more lift than the weight of an aircraft or watercraft using a wing (e.g. hydrofoil).

**INSTRUCTIONS**: Choose units and enter the following:

- (
**C**) Lift coefficient of the wings._{L} - (
**A**) Surface area of the wings. - (
**ρ**) Density of the fluid (air 1.2754 kg/m^{3}at STP or water 998.2071 kg/m^{3}at STP) - (
**M**) Mass of the craft.

**Takeoff Speed (V):** The calculator returns the required velocity (speed) in meters per second. However, this can be automatically converted to compatible units (e.g. miles per hour) via the pull-down menu.

Lift force is created by the flow of a fluid or gas over a wing. Lift force is a function of the wing characteristics and the velocity of the flow over the wing. As the velocity increases, so does the lifting force. At some point, when the velocity is increased, the lift force matches the downward force of gravity on the mass of the vehicle. That velocity is estimated in this formula. The **Velocity for Lift to overcome Weight** formula computes the speed needed to achieve the lifting force on the surface area of a wing that is greater than the vehicle's weight. The formula for the velocity to match force of lift to weight is:

`V = sqrt((M*g)/(½*A*rho*CL) )`

where:

- V is the velocity (see note)
- M is the Mass of vehicle
- g is the acceleration due to gravity
- A is the wing surface area
- ρ is the density of fluid
- CL is the lift coefficient

Flight can be achieved with the force of lift is greater than the weight.

**Note**: the wind velocity is not necessarily equal to the speed of the vehicle (e.g. aircraft on the runway). For aircraft, tail and head winds contribute to the total wind speed flowing over the wings. For precisely this reason, aircraft carriers turn into the wind to add both the ship's velocity and the speed of the wind to velocity of the aircraft being launched.

Bernoulli's principle is based on the conservation of energy, which dictates that in a steady flow of a fluid (lacking any substantial turbulence) the sum of all mechanical energy along a line of flow, a streamline, is the same at all points on that flow path. This , in turn means the sum of the potential and kinetic energy must remain constant and so with increased velocity of the flow, there is an decrease in static pressure.

From this same Bernoulli's principle we can derive the equation to calculate the lift force on a wing surface (airfoil). When the air flowing past the top surface of an aircraft wing moves faster than the air flowing past the bottom surface, Bernoulli's principle defines a difference in pressure on the two surfaces of the wing, with the lower pressure being on the upper surface where the faster flow exists.

The difference in pressure sums to a net upwards lifting force, as calculated in this equation..

The **density of air**, ρ (Greek: rho) (air density), is the mass per unit volume of Earth's atmosphere. Air density, like air pressure, decreases with increasing altitude. It also changes with variation in temperature or humidity. At sea level and at 15 °C, air has a density of approximately 1.225 kg/m^{3} (0.001225 g/cm^{3}, 0.0023769 slug/ft^{3}, 0.0765 lbm/ft^{3}) according to ISA (International Standard Atmosphere).

- At IUPAC standard temperature and pressure (0 °C and 100 kPa), dry air has a density of 1.2754 kg/m
^{3}. - At 20 °C and 101.325 kPa, dry air has a density of 1.2041 kg/m
^{3}. - At 70 °F and 14.696 psi, dry air has a density of 0.074887lb
_{m}/ft^{3}.

- Correction Angle
- Compute the Ground Speed
- Compute the distances between coordinates
- Compute the time to travel between coordinates
- Force of Drag
- Force of Lift
- Lift Coefficient
- vector (3D)
- Speed Needed for Takeoff
- Physics 105
- Glide Ratio
- Wing Surface Area
- Velocity of Air over the Wing

- Wikipedia - http://en.wikipedia.org/wiki/Density_of_air