Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Shikha Maurya
Indian Institute of Technology (IIT), Bombay
Shikha Maurya has verified this Calculator and 100+ more calculators!

11 Other formulas that you can solve using the same Inputs

Drag Coefficient for given zero-lift drag coefficient
Drag Coefficient=Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Drag Coefficient for given parasite drag coefficient
Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Coefficient of Drag due to lift
Coefficient of drag due to lift=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing) GO
Thrust for given coefficients of lift and drag
Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient GO
Lift for an unaccelerated flight
Lift force=Weight-(Thrust of an aircraft*sin(Thrust angle)) GO
Thrust angle for an unaccelerated flight for given lift
Thrust angle=asin((Weight-Lift force)/Thrust of an aircraft) GO
Thrust-to-weight ratio
Thrust-to-weight ratio=Drag Coefficient/lift coefficient GO
Dynamic pressure based on coefficient of lift
Dynamic Pressure=Lift force/(lift coefficient*Area) GO
Lift for a level, unaccelerated flight at negligible thrust angle
Lift force=Dynamic Pressure*Area*lift coefficient GO
Lift Force
Lift force=lift coefficient*Dynamic Pressure*Area GO
Weight of aircraft for a level, unaccelerated flight at negligible thrust angle
Weight=Dynamic Pressure*Area*lift coefficient GO

Velocity at sea-level condition Formula

Velocity at sea-level=sqrt(2*Weight/([Std-Air-Density-Sea]*Reference Area*lift coefficient))
V<sub>0</sub>=sqrt(2*W/([Std-Air-Density-Sea]*S*C<sub>L</sub>))
More formulas
Power required at sea-level condition GO
Velocity at an altitude GO
Power required 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

What are Standard sea-level conditions?

Standard sea-level conditions (SSL), also known as sea-level standard (SLS), defines a set of atmospheric conditions for physical calculations.

How to Calculate Velocity at sea-level condition?

Velocity at sea-level condition calculator uses Velocity at sea-level=sqrt(2*Weight/([Std-Air-Density-Sea]*Reference Area*lift coefficient)) to calculate the Velocity at sea-level, The Velocity at sea-level condition for an aircraft is a function of weight, reference area, and lift-coefficient of aircraft. Velocity at sea-level and is denoted by V0 symbol.

How to calculate Velocity at sea-level condition using this online calculator? To use this online calculator for Velocity at sea-level condition, enter Weight (W), Reference Area (S) and lift coefficient (CL) and hit the calculate button. Here is how the Velocity at sea-level condition calculation can be explained with given input values -> 1.804073 = sqrt(2*100/([Std-Air-Density-Sea]*5*10)).

FAQ

What is Velocity at sea-level condition?
The Velocity at sea-level condition for an aircraft is a function of weight, reference area, and lift-coefficient of aircraft and is represented as V0=sqrt(2*W/([Std-Air-Density-Sea]*S*CL)) or Velocity at sea-level=sqrt(2*Weight/([Std-Air-Density-Sea]*Reference Area*lift coefficient)). Weight is a vector quantity and defined as the product of mass and acceleration acting on that mass, 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 Velocity at sea-level condition?
The Velocity at sea-level condition for an aircraft is a function of weight, reference area, and lift-coefficient of aircraft is calculated using Velocity at sea-level=sqrt(2*Weight/([Std-Air-Density-Sea]*Reference Area*lift coefficient)). To calculate Velocity at sea-level condition, you need Weight (W), Reference Area (S) and lift coefficient (CL). With our tool, you need to enter the respective value for Weight, 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.
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