Wind Tunnel

Transonic Wind Tunnel

The Mach number range of the transonic wind tunnel test is roughly 0.8~1.4, and the upper limit of the Mach number is mainly limited by the power. The power consumed by the transonic wind tunnel is enormous and increases rapidly with the increase of Mach number. When the Mach number reaches about 1.4, the flow around the model (such as an airfoil) has completely or basically become a supersonic flow, and the change of aerodynamic characteristics with the Mach number has become stable. In the transonic range, the flow is more complicated. There are both subsonic and supersonic regions in the flow field, and it is often unstable. The aerodynamic force and torque change drastically with the change of Mach number. The so-called sound barrier problem that has arisen in the history of aircraft development is related to the complexity of this flow. The main speed range of modern fighter jets for air combat is the transonic range of high subsonic speed and low supersonic speed, and the flight speed of large and medium-sized passenger aircraft is also in the high subsonic speed or transonic speed range. Although the speed of supersonic aircraft and higher-speed rockets, missiles and other aircraft has long been greater than or far greater than the speed of sound, they must still pass through the transonic range during the acceleration process. Therefore, the transonic performance of all these vehicles is still a problem that must be studied and solved.

Transonic wind tunnel Design and development
Transonic wind tunnel facility
Transonic wind tunnel experiment and test
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