Wind tunnel AT - 303 is designed for the study of fundamental
and applied problems related to provision of a long-time flight of promising
scramjet-powered hypersonic flying vehicles in the Earth atmosphere. The
obtained experimental data are used to study complicated gas- and
thermal-dynamic processes appearing at such aircraft flight, and also to check
the calculated models, to define their accuracy and reliability.
- full-scale simulation of the Reynolds numbers in the hypersonic
range of velocities due to high pressure of the test gas in the settling
- long - run duration (40 - 500 ms at constant pressure)
sufficient for obtaining a steady flow;
- very pure flow free of working gas dissociation, and also
chemical and mechanical admixtures.
|General view of hypersonic wind tunnel
The basis of the wind tunnel AT-303 is the test gas source*. In the
initial position a valve in the settling chamber 4 is closed, and the pistons in
the section of high pressure 3 are in the extreme position. Through a special
Cowper-type heater 7, the settling chamber is filled with the test gas with
pressure up to 200 atm and temperature up to 1000 К. When the driver gas with
pressure up to 200 atm is supplied from receivers 1 to the pistons of hydraulic
pressure multipliers 2, the pressure in the liquid increases up to 1500 atm and
affects the pistons in the section of high pressure. The pistons begin to move,
compressing adiabatically the test gas in the settling chamber up to pressure
3000 atm and temperature 2500 К. The velocity of piston motion is controlled by
liquid flow through the throttling device 5. The next device activates the
fast-acting valve in the settling chamber which opens the exit for the test gas
to the nozzle.
*Test gas source - Patent of the Russian Federation No. 2166186.
Sketch of hypersonic wind tunnel
Principle scheme of the gas
Technical parameters wind tunnel AT -
|Nozzle diameter D, mm
|Settling chamber volume, dm3
|Stagnation pressure Po, atm
|Stagnation temperature Тo, К
|Mach number M
|Reynolds number Reo
|Run duration t, s
||0,04 - 0,2
||0,04 - 0,2|
||Air, nitrogen, CO., etc.
||Air, nitrogen, CO., etc.|
More characteristics of wind tunnel AT
|Control system of the wind tunnel. Multi-channel
data acquisition system|
|Visualization of the flow around a rake of
- Development and performance of aerodynamic test programs in the
range of Mach numbers from 8 up to 20 at high Reynolds values
- Simulation of ramjet under conditions of pure air flow.
- Aerodynamic tests using any gases and mixtures for creation of
- Development and application of untypical methods of gasdynamic
investigations and measurements.
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS
Institutskaya str., 4/1, Novosibirsk 630090, Russia
Tel: (383) 330-34-30; fax: (383) 330-72-68, e-mail:email@example.com
Shipluk Alexandr Nikolaevich, tel: (383) 330-18-95