Supersonic wind tunnel

This article is missing information about Explanation of the mathematics of throat area and pressure ratios determining Mach number, explanation of the meaning of the symbols in "minimum required pressure ratio", and the promised examples. Please expand the article to include this information. Further details may exist on the talk page. (October 2014)

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Engineers check an aircraft model before a test run in the Supersonic Wind Tunnel at Lewis Flight Propulsion Laboratory. Schlieren photography is often used to capture images of gas flow and shock waves in supersonic wind tunnels. Here, Mach 4 flow over a pitot probe is observed by schlieren optics in the Penn State Supersonic Wind Tunnel. The flow direction is left-to-right.

A supersonic wind tunnel is a wind tunnel that produces supersonic speeds (1.2<M<5) The Mach number and flow are determined by the nozzle geometry. The Reynolds number is varied by changing the density level (pressure in the settling chamber). Therefore, a high pressure ratio is required (for a supersonic regime at M=4, this ratio is of the order of 10). Apart from that, condensation of moisture or even gas liquefaction can occur if the static temperature becomes cold enough. This means that a supersonic wind tunnel usually needs a drying or a pre-heating facility. A supersonic wind tunnel has a large power demand, so most are designed for intermittent instead of continuous operation.

The first supersonic wind tunnel (with a cross section of 2 cm) was built in National Physical Laboratory in England, and started working in 1922.

## Contents

* 1 Restrictions for supersonic tunnel operation
* 1.1 Minimum required pressure ratio
* 1.2 Temperature effects: condensation
* 2 Power requirements
* 3 Further reading
* 4 See also
* 5 External links

## Restrictions for supersonic tunnel operation

### Minimum required pressure ratio

Optimistic estimate: Pressure ratio ≤ the total pressure ratio over normal shock at M in test section:

PtPamb≤(Pt1Pt2)M1=Mm

Examples:

### Temperature effects: condensation

Temperature in the test section:

TmTt=(1+γ−12Mm2)−1

with Tt = 330 K: Tm = 70 K at Mm = 4

The velocity range is limited by reservoir temperature

## Power requirements

The power required to run a supersonic wind tunnel is enormous, of the order of 50 MW per square meter of test section cross-sectional area. For this reason most wind tunnels operate intermittently using energy stored in high-pressure tanks. These wind tunnels are also called intermittent supersonic blowdown wind tunnels (of which a schematic preview is given below). Another way of achieving the huge power output is with the use of a vacuum storage tank. These tunnels are called indraft supersonic wind tunnels, and are seldom used because they are restricted to low Reynolds numbers. Some large countries have built major supersonic tunnels that run continuously; one is shown in the photo. Other problems operating a supersonic wind tunnel include:

* starting and unstart of the test section (related to maintaining at least a minimum pressure ratio)
* adequate supply of dry air
* wall interference effects due to shock wave reflection and (sometimes) blockage
* high-quality instruments capable of rapid measurements due to short run times in intermittent tunnels

Tunnels such as a Ludwieg tube have short test times (usually less than one second), relatively high Reynolds number, and low power requirements.

## Further reading

* Pope, A.; Goin, K. (1978). High-speed Wind Tunnel Testing. Krieger. ISBN 0-88275-727-X.

## See also

* Low speed wind tunnel
* High speed wind tunnel
* Hypersonic wind tunnel
* Ludwieg tube
* Shock tube

## External links

* Supersonic wind tunnel test demonstration (Mach 2.5) with flat plate and wedge creating an oblique shock(Video)

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