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Supersonic wind tunnel

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Asupersonic 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.

Restrictions for supersonic tunnel operation[edit]

Minimum required pressure ratio[edit]

Optimistic estimate: Pressure ratio ${\displaystyle \leq }$ the total pressure ratio over normal shock at M in test section:

${\displaystyle {\frac {P_{t}}{P_{amb}}}\leq \left({\frac {P_{t_{1}}}{P_{t_{2}}}}\right)_{M_{1}=M_{m}}}$

Examples:

Temperature effects: condensation[edit]

Temperature in the test section:

${\displaystyle {\frac {T_{m}}{T_{t}}}=\left(1+{\frac {\gamma -1}{2}}M_{m}^{2}\right)^{-1}}$

with ${\displaystyle T_{t}}$ = 330 K: ${\displaystyle T_{m}}$ = 70 K at ${\displaystyle M_{m}}$ = 4

The velocity range is limited by reservoir temperature

Power requirements[edit]

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[edit]

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

See also[edit]

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

External links[edit]

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