HCF of two numbers

Wind Tunnel Test Section Velocity Calculator

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Aerodynamic Measurements and Wind Tunnel Testing Bernoulli's Equation and Pressure Concepts

✖Pressure at Point 1 is the pressure on streamline at a given point in the flow.ⓘ Pressure at Point 1 [P₁]			+10% -10%
✖Pressure at Point 2 is the pressure on streamline at a given point in the flow.ⓘ Pressure at Point 2 [P₂]			+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%
✖Contraction ratio is the ratio of inlet area or reservoir area to the test section area or throat area of a duct.ⓘ Contraction Ratio [A_lift]			+10% -10%

✖velocity at Point 2 is the velocity of fluid passing through point 2 in a flow.ⓘ Wind Tunnel Test Section Velocity [V₂]

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Wind Tunnel Test Section Velocity Solution

STEP 0: Pre-Calculation Summary

Formula Used

Velocity at Point 2 = sqrt((2*(Pressure at Point 1-Pressure at Point 2))/(Density*(1-1/Contraction Ratio^2)))
V₂ = sqrt((2*(P₁-P₂))/(ρ₀*(1-1/A_lift^2)))
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 Point 2 - (Measured in Meter per Second) - velocity at Point 2 is the velocity of fluid passing through point 2 in a flow.
Pressure at Point 1 - (Measured in Pascal) - Pressure at Point 1 is the pressure on streamline at a given point in the flow.
Pressure at Point 2 - (Measured in Pascal) - Pressure at Point 2 is the pressure on streamline at a given point in the flow.
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.
Contraction Ratio - Contraction ratio is the ratio of inlet area or reservoir area to the test section area or throat area of a duct.

STEP 1: Convert Input(s) to Base Unit

Pressure at Point 1: 9800 Pascal --> 9800 Pascal No Conversion Required
Pressure at Point 2: 9630.609 Pascal --> 9630.609 Pascal No Conversion Required
Density: 997 Kilogram per Cubic Meter --> 997 Kilogram per Cubic Meter No Conversion Required
Contraction Ratio: 2.1 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

V₂ = sqrt((2*(P₁-P₂))/(ρ₀*(1-1/A_lift^2))) --> sqrt((2*(9800-9630.609))/(997*(1-1/2.1^2)))

Evaluating ... ...

V₂ = 0.662910182337578

STEP 3: Convert Result to Output's Unit

0.662910182337578 Meter per Second --> No Conversion Required

FINAL ANSWER

0.662910182337578 ≈ 0.66291 Meter per Second <-- Velocity at Point 2

(Calculation completed in 00.020 seconds)

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Indian Institute of Technology (IIT), Bombay

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< Aerodynamic Measurements and Wind Tunnel Testing Calculators

Wind Tunnel Test Section Velocity

LaTeX Go Velocity at Point 2 = sqrt((2*(Pressure at Point 1-Pressure at Point 2))/(Density*(1-1/Contraction Ratio^2)))

Airspeed Measurement by Venturi

LaTeX Go Velocity at Point 1 = sqrt((2*(Pressure at Point 1-Pressure at Point 2))/(Density*(Contraction Ratio^2-1)))

Wind Tunnel Pressure Difference with Test Speed

LaTeX Go Pressure Difference = 0.5*Air Density*Velocity at Point 2^2*(1-1/Contraction Ratio^2)

Wind Tunnel Pressure Difference by Manometer

LaTeX Go Pressure Difference = Specific Weight of Manometric Fluid*Height Difference of Manometric Fluid

Wind Tunnel Test Section Velocity Formula

LaTeX Go

Velocity at Point 2 = sqrt((2*(Pressure at Point 1-Pressure at Point 2))/(Density*(1-1/Contraction Ratio^2)))
V₂ = sqrt((2*(P₁-P₂))/(ρ₀*(1-1/A_lift^2)))

What are wind tunnels?

In the most basic sense, they are ground-based experimental facilities designed to produce flows of air (sometimes other gases), which simulate the natural flows occurring outside the laboratory. For aerospace engineering applications, wind tunnels are designed to simulate flows encountered in the flight of airplanes, missiles, or space vehicles. They are classified on the basis of flight Mach number from low speed subsonic to hypersonic.

Which parameter governs the test section velocity of low speed wind tunnel?

For a given wind tunnel design area ratio is a fixed quantity hence the test section velocity of the low-speed wind tunnel is governed by the pressure difference between inlet and test section.

How to Calculate Wind Tunnel Test Section Velocity?

Wind Tunnel Test Section Velocity calculator uses Velocity at Point 2 = sqrt((2*(Pressure at Point 1-Pressure at Point 2))/(Density*(1-1/Contraction Ratio^2))) to calculate the Velocity at Point 2, Wind Tunnel Test Section Velocity formula is defined as a method to determine the velocity of airflow in a wind tunnel test section, which is essential for analyzing aerodynamic properties and performance of models under controlled conditions. Velocity at Point 2 is denoted by V₂ symbol.

How to calculate Wind Tunnel Test Section Velocity using this online calculator? To use this online calculator for Wind Tunnel Test Section Velocity, enter Pressure at Point 1 (P₁), Pressure at Point 2 (P₂), Density (ρ₀) & Contraction Ratio (A_lift) and hit the calculate button. Here is how the Wind Tunnel Test Section Velocity calculation can be explained with given input values -> 0.66291 = sqrt((2*(9800-9630.609))/(997*(1-1/2.1^2))).

FAQ

What is Wind Tunnel Test Section Velocity?

Wind Tunnel Test Section Velocity formula is defined as a method to determine the velocity of airflow in a wind tunnel test section, which is essential for analyzing aerodynamic properties and performance of models under controlled conditions and is represented as V₂ = sqrt((2*(P₁-P₂))/(ρ₀*(1-1/A_lift^2))) or Velocity at Point 2 = sqrt((2*(Pressure at Point 1-Pressure at Point 2))/(Density*(1-1/Contraction Ratio^2))). Pressure at Point 1 is the pressure on streamline at a given point in the flow, Pressure at Point 2 is the pressure on streamline at a given point in the flow, 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 & Contraction ratio is the ratio of inlet area or reservoir area to the test section area or throat area of a duct.

How to calculate Wind Tunnel Test Section Velocity?

Wind Tunnel Test Section Velocity formula is defined as a method to determine the velocity of airflow in a wind tunnel test section, which is essential for analyzing aerodynamic properties and performance of models under controlled conditions is calculated using Velocity at Point 2 = sqrt((2*(Pressure at Point 1-Pressure at Point 2))/(Density*(1-1/Contraction Ratio^2))). To calculate Wind Tunnel Test Section Velocity, you need Pressure at Point 1 (P₁), Pressure at Point 2 (P₂), Density (ρ₀) & Contraction Ratio (A_lift). With our tool, you need to enter the respective value for Pressure at Point 1, Pressure at Point 2, Density & Contraction Ratio 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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