Velocity at Sea-level given Lift Coefficient Calculator

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Introduction and Governing Equations

Aircraft Design

Aircraft Performance

Static Stability and Control

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Preliminary Aerodynamics

Aircraft Dynamics Nomenclature

Atmosphere and Gas Properties

Lift and Drag Polar

✖Weight of body is the force acting on the object due to gravity.ⓘ Weight of body [W_body]			+10% -10%
✖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.ⓘ Reference Area [S]			+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%

✖Velocity at sea-level is the distance traveled per unit time by aircraft at the sea-level condition.ⓘ Velocity at Sea-level given Lift Coefficient [V₀]

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Formula

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Velocity at Sea-level given Lift Coefficient

Formula

`"V"_{"0"} = sqrt((2*"W"_{"body"})/("[Std-Air-Density-Sea]"*"S"*"C"_{"L"}))`

Example

`"6.798776m/s"=sqrt((2*"750N")/("[Std-Air-Density-Sea]"*"91.05m²"*"0.29"))`

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Velocity at Sea-level given Lift Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Velocity at sea-level = sqrt((2*Weight of body)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient))
V₀ = sqrt((2*W_body)/([Std-Air-Density-Sea]*S*C_L))
This formula uses 1 Constants, 1 Functions, 4 Variables

Constants Used

[Std-Air-Density-Sea] - Standard air density at sea-level conditions Value Taken As 1.229

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

Velocity at sea-level - (Measured in Meter per Second) - Velocity at sea-level is the distance traveled per unit time by aircraft at the sea-level condition.
Weight of body - (Measured in Newton) - Weight of body is the force acting on the object due to gravity.
Reference Area - (Measured in Square Meter) - 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.
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

Weight of body: 750 Newton --> 750 Newton No Conversion Required
Reference Area: 91.05 Square Meter --> 91.05 Square Meter No Conversion Required
Lift Coefficient: 0.29 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

V₀ = sqrt((2*W_body)/([Std-Air-Density-Sea]*S*C_L)) --> sqrt((2*750)/([Std-Air-Density-Sea]*91.05*0.29))

Evaluating ... ...

V₀ = 6.79877570892459

STEP 3: Convert Result to Output's Unit

6.79877570892459 Meter per Second --> No Conversion Required

FINAL ANSWER

6.79877570892459 ≈ 6.798776 Meter per Second <-- Velocity at sea-level

(Calculation completed in 00.004 seconds)

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Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

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< 17 Preliminary Aerodynamics Calculators

Power required at sea-level conditions

Go Power required at sea-level = sqrt((2*Weight of body^3*Drag Coefficient^2)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient^3))

Mach Number-2

Go Mach number 2 = sqrt(((((Heat Capacity Ratio-1)*Mach Number^(2)+2))/(2*Heat Capacity Ratio*Mach Number^(2)-(Heat Capacity Ratio-1))))

Power required at Altitude

Go Power required at an altitude = sqrt((2*Weight of body^3*Drag Coefficient^2)/(Density*Reference Area*Lift Coefficient^3))

Velocity at Sea-level given Lift Coefficient

Go Velocity at sea-level = sqrt((2*Weight of body)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient))

Dynamic pressure given gas constant

Go Dynamic Pressure = 1/2*Ambient air density*Mach Number^2*Specific Heat of Air*Gas Constant*Temperature

Velocity at Altitude

Go Velocity at an altitude = sqrt(2*Weight of body/(Density*Reference Area*Lift Coefficient))

Power required at Altitude given Power at sea-level

Go Power required at an altitude = Power required at sea-level*sqrt([Std-Air-Density-Sea]/Density)

Velocity at Altitude given Velocity at Sea-Level

Go Velocity at an altitude = Velocity at sea-level*sqrt([Std-Air-Density-Sea]/Density)

Dynamic pressure given induced drag

Go Dynamic Pressure = Lift Force^2/(pi*Induced Drag*Lateral plane span^2)

Dynamic pressure given mach number

Go Dynamic Pressure = 1/2*Ambient air density*(Mach Number*Sonic speed)^2

Dynamic pressure given normal pressure

Go Dynamic Pressure = 1/2*Specific Heat of Air*Pressure*Mach Number^2

Flight speed given dynamic pressure

Go Flight speed = sqrt((2*Dynamic Pressure)/Ambient air density)

Dynamic pressure aircraft

Go Dynamic Pressure = 1/2*Ambient air density*Flight speed^2

Dynamic pressure given lift coefficient

Go Dynamic Pressure = Lift Force/Lift Coefficient

Dynamic pressure given drag coefficient

Go Dynamic Pressure = Drag Force/Drag Coefficient

Aerodynamic force

Go Aerodynamic Force = Drag Force+Lift Force

Mach number of moving object

Go Mach Number = Velocity/Speed of Sound

Velocity at Sea-level given Lift Coefficient Formula

Velocity at sea-level = sqrt((2*Weight of body)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient))
V₀ = sqrt((2*W_body)/([Std-Air-Density-Sea]*S*C_L))

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 given Lift Coefficient?

Velocity at Sea-level given Lift Coefficient calculator uses Velocity at sea-level = sqrt((2*Weight of body)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient)) to calculate the Velocity at sea-level, Velocity At Sea-level given Lift Coefficient formula evaluates the flight velocity at sea level conditions given the lift coefficient and the weight. Velocity at sea-level is denoted by V₀ symbol.

How to calculate Velocity at Sea-level given Lift Coefficient using this online calculator? To use this online calculator for Velocity at Sea-level given Lift Coefficient, enter Weight of body (W_body), Reference Area (S) & Lift Coefficient (C_L) and hit the calculate button. Here is how the Velocity at Sea-level given Lift Coefficient calculation can be explained with given input values -> 6.798776 = sqrt((2*750)/([Std-Air-Density-Sea]*91.05*0.29)).

FAQ

What is Velocity at Sea-level given Lift Coefficient?

Velocity At Sea-level given Lift Coefficient formula evaluates the flight velocity at sea level conditions given the lift coefficient and the weight and is represented as V₀ = sqrt((2*W_body)/([Std-Air-Density-Sea]*S*C_L)) or Velocity at sea-level = sqrt((2*Weight of body)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient)). Weight of body is the force acting on the object due to gravity, 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 & 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 Velocity at Sea-level given Lift Coefficient?

Velocity At Sea-level given Lift Coefficient formula evaluates the flight velocity at sea level conditions given the lift coefficient and the weight is calculated using Velocity at sea-level = sqrt((2*Weight of body)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient)). To calculate Velocity at Sea-level given Lift Coefficient, you need Weight of body (W_body), Reference Area (S) & Lift Coefficient (C_L). With our tool, you need to enter the respective value for Weight of body, Reference Area & 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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