Velocity at Altitude Calculator

✖Weight of Body is the force acting on the object due to gravity.ⓘ Weight of Body [W_body]			+10% -10%
✖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.ⓘ Density [ρ₀]			+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 an Altitude is the velocity of an aircraft at a given altitude (or density).ⓘ Velocity at Altitude [V_alt]

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Velocity at Altitude Solution

STEP 0: Pre-Calculation Summary

Formula Used

Velocity at an Altitude = sqrt(2*Weight of Body/(Density*Reference Area*Lift Coefficient))
V_alt = sqrt(2*W_body/(ρ₀*S*C_L))
This formula uses 1 Functions, 5 Variables

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 an Altitude - (Measured in Meter per Second) - Velocity at an Altitude is the velocity of an aircraft at a given altitude (or density).
Weight of Body - (Measured in Newton) - Weight of Body is the force acting on the object due to gravity.
Density - (Measured in Kilogram per Cubic Meter) - 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.
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
Density: 997 Kilogram per Cubic Meter --> 997 Kilogram per Cubic Meter 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

V_alt = sqrt(2*W_body/(ρ₀*S*C_L)) --> sqrt(2*750/(997*91.05*0.29))

Evaluating ... ...

V_alt = 0.238703659087935

STEP 3: Convert Result to Output's Unit

0.238703659087935 Meter per Second --> No Conversion Required

FINAL ANSWER

0.238703659087935 ≈ 0.238704 Meter per Second <-- Velocity at an Altitude

(Calculation completed in 00.006 seconds)

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Created by Vinay Mishra

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

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Verified by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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< Preliminary Aerodynamics Calculators

Power required at sea-level conditions

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

Power required at Altitude

LaTeX Go Power Required at Altitude = sqrt((2*Weight of Body^3*Drag Coefficient^2)/(Density*Reference Area*Lift Coefficient^3))

Velocity at Sea-Level given Lift Coefficient

LaTeX Go Velocity at Sea-Level = sqrt((2*Weight of Body)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient))

Velocity at Altitude

LaTeX Go Velocity at an Altitude = sqrt(2*Weight of Body/(Density*Reference Area*Lift Coefficient))

Velocity at Altitude Formula

LaTeX Go

Velocity at an Altitude = sqrt(2*Weight of Body/(Density*Reference Area*Lift Coefficient))
V_alt = sqrt(2*W_body/(ρ₀*S*C_L))

Do Airplanes Fly Faster at Higher Altitudes?

Each airplane has an optimal cruising altitude range that is the best tradeoff of speed and fuel efficiency.

How to Calculate Velocity at Altitude?

Velocity at Altitude calculator uses Velocity at an Altitude = sqrt(2*Weight of Body/(Density*Reference Area*Lift Coefficient)) to calculate the Velocity at an Altitude, Velocity at Altitude is a measure of the speed of an object at a specific height above the Earth's surface, taking into account the body's weight, air density, reference area, and lift coefficient, this formula allows for the calculation of velocity in aerodynamic systems, providing valuable insights for engineers and researchers in the fields of aerospace and aerodynamics. Velocity at an Altitude is denoted by V_alt symbol.

How to calculate Velocity at Altitude using this online calculator? To use this online calculator for Velocity at Altitude, enter Weight of Body (W_body), Density (ρ₀), Reference Area (S) & Lift Coefficient (C_L) and hit the calculate button. Here is how the Velocity at Altitude calculation can be explained with given input values -> 0.238704 = sqrt(2*750/(997*91.05*0.29)).

FAQ

What is Velocity at Altitude?

Velocity at Altitude is a measure of the speed of an object at a specific height above the Earth's surface, taking into account the body's weight, air density, reference area, and lift coefficient, this formula allows for the calculation of velocity in aerodynamic systems, providing valuable insights for engineers and researchers in the fields of aerospace and aerodynamics and is represented as V_alt = sqrt(2*W_body/(ρ₀*S*C_L)) or Velocity at an Altitude = sqrt(2*Weight of Body/(Density*Reference Area*Lift Coefficient)). Weight of Body is the force acting on the object due to gravity, 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 & 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 Altitude?

Velocity at Altitude is a measure of the speed of an object at a specific height above the Earth's surface, taking into account the body's weight, air density, reference area, and lift coefficient, this formula allows for the calculation of velocity in aerodynamic systems, providing valuable insights for engineers and researchers in the fields of aerospace and aerodynamics is calculated using Velocity at an Altitude = sqrt(2*Weight of Body/(Density*Reference Area*Lift Coefficient)). To calculate Velocity at Altitude, you need Weight of Body (W_body), Density (ρ₀), Reference Area (S) & Lift Coefficient (C_L). With our tool, you need to enter the respective value for Weight of Body, Density, 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.

How many ways are there to calculate Velocity at an Altitude?

In this formula, Velocity at an Altitude uses Weight of Body, Density, Reference Area & Lift Coefficient. We can use 1 other way(s) to calculate the same, which is/are as follows -

Velocity at an Altitude = Velocity at Sea-Level*sqrt([Std-Air-Density-Sea]/Density)

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