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

Pressure difference measured by manometer in the low-speed wind tunnel
Pressure differ between reservoir & test section=Weight per unit volume of manometer fluid*Difference in height of manometric fluid GO

Pressure difference in the low-speed wind tunnel for given test section velocity Formula

Pressure differ between reservoir & test section=0.5*Density*((Velocity at point 2)^2)*(1-(1/Contraction ratio)^2)
P<sub>1</sub>-P<sub>2</sub>=0.5*ρ*((V<sub>2</sub>)^2)*(1-(1/A<sub>1</sub>/A <sub>2</sub>)^2)
More formulas
Pressure at a downstream point on streamline by Bernoulli's equation GO
Pressure at an upstream point on streamline by Bernoulli's equation GO
Airspeed measurement by venturi GO
Test section velocity in low-speed wind tunnel GO
Pressure difference measured by manometer in the low-speed wind tunnel GO
Test section velocity for low sped wind tunnel in terms of height difference of manometric fluid GO
Height difference of manometric fluid for given pressure difference GO
Dynamic pressure in incompressible flow GO
Total pressure in incompressible flow GO
Static pressure in incompressible flow GO
Airspeed measurement by Pitot tube for low-speed incompressible flow GO
Pressure coefficient in terms of velocity ratio for inncompressible flow GO
Pressure Coefficient GO
Surface pressure on the body in terms of Pressure coefficient GO
Velocity potential for uniform incompressible flow GO
Velocity at a point on airfoil for given pressure coefficient and free-stream velocity GO
Stream function for uniform incompressible flow GO
Velocity potential for uniform incompressible flow in polar coordinates GO
Stream function for uniform incompressible flow in polar coordinates GO
Source Strength for 2-D incompressible source flow GO
Radial velocity for 2-D incompressible source flow GO
Velocity potential for 2-D source flow GO
Stream function for 2-D incompressible source flow GO
Stream function for semi-infinite body GO
Stagnation streamline equation for flow over semi-infinite body GO
Stream function for flow over Rankine oval GO
Stream function for 2-D Doublet flow GO
Velocity potential for 2-D doublet flow GO
Stream function for non-lifting flow over a circular cylinder GO
Tangential velocity for non-lifting flow over circular cylinder GO
Radial velocity for non-lifting flow over circular cylinder GO
Radius of cylinder for non-lifting flow GO
Surface pressure coefficient for non-lifting flow over circular cylinder GO
Stream function for 2-D Vortex flow GO
Velocity potential for 2-D Vortex flow GO
Tangential velocity for 2-D Vortex flow GO
Stream function for lifting flow over a circular cylinder GO
Radial velocity for lifting flow over circular cylinder GO
Tangential velocity for lifting flow over circular cylinder GO
Surface pressure coefficient for lifting flow over circular cylinder GO
Location of stagnation point outside the cylinder for lifting flow GO
2-D Lift coefficient for cylinder GO
Lift per unit span by Kutta-Joukowski theorem GO
Circulation by Kutta-Joukowski theorem GO
Freestream velocity by Kutta-Joukowski theorem GO
Freestream density by Kutta-Joukowski theorem GO

What is open and closed circuit wind tunnel?

In the open-circuit wind tunnel, where the air is drawn in the front directly from the atmosphere and exhausted out the back, again directly to the atmosphere. The wind tunnel may be a closed circuit, where the air from the exhaust is returned directly to the front of the tunnel via a closed duct forming a loop.

How to Calculate Pressure difference in the low-speed wind tunnel for given test section velocity ?

Pressure difference in the low-speed wind tunnel for given test section velocity calculator uses Pressure differ between reservoir & test section=0.5*Density*((Velocity at point 2)^2)*(1-(1/Contraction ratio)^2) to calculate the Pressure differ between reservoir & test section, Pressure difference in the low-speed wind tunnel for given test section velocity and area ratio is a function of contraction ratio, the density of the fluid in the wind tunnel and test section velocity. . Pressure differ between reservoir & test section and is denoted by P1-P2 symbol.

How to calculate Pressure difference in the low-speed wind tunnel for given test section velocity using this online calculator? To use this online calculator for Pressure difference in the low-speed wind tunnel for given test section velocity , enter Density (ρ), Velocity at point 2 (V2) and Contraction ratio (A1/A 2) and hit the calculate button. Here is how the Pressure difference in the low-speed wind tunnel for given test section velocity calculation can be explained with given input values -> 1.254E+6 = 0.5*997*((57.91)^2)*(1-(1/2)^2).

FAQ

What is Pressure difference in the low-speed wind tunnel for given test section velocity ?
Pressure difference in the low-speed wind tunnel for given test section velocity and area ratio is a function of contraction ratio, the density of the fluid in the wind tunnel and test section velocity. and is represented as P1-P2=0.5*ρ*((V2)^2)*(1-(1/A1/A 2)^2) or Pressure differ between reservoir & test section=0.5*Density*((Velocity at point 2)^2)*(1-(1/Contraction ratio)^2). 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. , velocity at point 2 is the velocity of fluid passing through point 2 in a flow and 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 Pressure difference in the low-speed wind tunnel for given test section velocity ?
Pressure difference in the low-speed wind tunnel for given test section velocity and area ratio is a function of contraction ratio, the density of the fluid in the wind tunnel and test section velocity. is calculated using Pressure differ between reservoir & test section=0.5*Density*((Velocity at point 2)^2)*(1-(1/Contraction ratio)^2). To calculate Pressure difference in the low-speed wind tunnel for given test section velocity , you need Density (ρ), Velocity at point 2 (V2) and Contraction ratio (A1/A 2). With our tool, you need to enter the respective value for Density, Velocity at point 2 and Contraction ratio 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 Pressure differ between reservoir & test section?
In this formula, Pressure differ between reservoir & test section uses Density, Velocity at point 2 and Contraction ratio. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Pressure differ between reservoir & test section=Weight per unit volume of manometer fluid*Difference in height of manometric fluid
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