Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
Maiarutselvan V has verified this Calculator and 200+ more calculators!

11 Other formulas that you can solve using the same Inputs

Stanton Number (using basic fluid properties)
Stanton Number=External convection heat transfer coefficient/(Specific Heat Capacity*Fluid Velocity*Density) GO
Reynolds Number for Non-Circular Tubes
Reynolds Number=Density*Fluid Velocity*Characteristic Length/Dynamic viscosity GO
Thermal Diffusivity
Thermal Diffusivity=Thermal Conductivity/(Density*Specific Heat Capacity) GO
Reynolds Number for Circular Tubes
Reynolds Number=Density*Fluid Velocity*Diameter /Dynamic viscosity GO
Inertial Force Per Unit Area
Inertial Force per unit area=(Fluid Velocity^2)*Density GO
Pressure when density and height are given
Pressure=Density*Acceleration Due To Gravity*Height GO
Turbulence
Turbulence=Density*Dynamic viscosity*Fluid Velocity GO
Molar Volume
Molar Volume=(Atomic Weight*Molar Mass)/Density GO
Momentum Diffusivity
Momentum diffusivity=Dynamic viscosity/Density GO
Number of atomic sites
Number of atomic sites=Density/Atomic Mass GO
Relative Density
Relative Density=Density/Water Density GO

1 Other formulas that calculate the same Output

Power required at an altitude for given power required at sea-level condition
Power required at an altitude=Power required at sea-level*sqrt([Std-Air-Density-Sea]/Density) GO

Power required at an altitude Formula

Power required at an altitude=sqrt(2*(Weight^3)*(Drag Coefficient^2)/(Density*Reference Area*(lift coefficient^3)))
P<sub>R,alt</sub>=sqrt(2*(W^3)*(C<sub>D</sub>^2)/(ρ*S*(C<sub>L</sub>^3)))
More formulas
Velocity at sea-level condition GO
Power required at sea-level condition GO
Velocity at an altitude GO
Velocity at an altitude for given velocity at sea-level condition GO
Power required at an altitude for given power required at sea-level condition GO

How fast can you go in a commercial airliner?

For civil aircraft, there is an airspeed limit of Mach 1 which is 667 knots or around 767 miles per hour.

How to Calculate Power required at an altitude?

Power required at an altitude calculator uses Power required at an altitude=sqrt(2*(Weight^3)*(Drag Coefficient^2)/(Density*Reference Area*(lift coefficient^3))) to calculate the Power required at an altitude, The Power required at an altitude for an aircraft is a function of the weight, reference area, aerodynamic coefficients of the aircraft, and the density of air at that altitude. Power required at an altitude and is denoted by PR,alt symbol.

How to calculate Power required at an altitude using this online calculator? To use this online calculator for Power required at an altitude, enter Weight (W), Drag Coefficient (CD), Density (ρ), Reference Area (S) and lift coefficient (CL) and hit the calculate button. Here is how the Power required at an altitude calculation can be explained with given input values -> 63.34064 = sqrt(2*(100^3)*(100^2)/(997*5*(10^3))).

FAQ

What is Power required at an altitude?
The Power required at an altitude for an aircraft is a function of the weight, reference area, aerodynamic coefficients of the aircraft, and the density of air at that altitude and is represented as PR,alt=sqrt(2*(W^3)*(CD^2)/(ρ*S*(CL^3))) or Power required at an altitude=sqrt(2*(Weight^3)*(Drag Coefficient^2)/(Density*Reference Area*(lift coefficient^3))). Weight is a vector quantity and defined as the product of mass and acceleration acting on that mass, Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water, The density of a material shows the denseness of that material in a specific given area. This is taken as mass per unit volume of a given object. , 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 and The lift coefficient (CL) 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 Power required at an altitude?
The Power required at an altitude for an aircraft is a function of the weight, reference area, aerodynamic coefficients of the aircraft, and the density of air at that altitude is calculated using Power required at an altitude=sqrt(2*(Weight^3)*(Drag Coefficient^2)/(Density*Reference Area*(lift coefficient^3))). To calculate Power required at an altitude, you need Weight (W), Drag Coefficient (CD), Density (ρ), Reference Area (S) and lift coefficient (CL). With our tool, you need to enter the respective value for Weight, Drag Coefficient, Density, Reference Area and 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 Power required at an altitude?
In this formula, Power required at an altitude uses Weight, Drag Coefficient, Density, Reference Area and lift coefficient. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Power required at an altitude=Power required at sea-level*sqrt([Std-Air-Density-Sea]/Density)
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