| Customization: | Available |
|---|---|
| Transport Package: | Box |
| Origin: | China |
Suppliers with verified business licenses
Audited Supplier Audited by an independent third-party inspection agency
| Propeller Wind Tunnel Icing Wind Tunnel Vertical Wind Tunnel Supersonic Wind Tunnel Transonic Wind Tunnel Hypersonic Wind Tunnel |
The air propeller is a tool that converts the power of the aero engine into the propulsion of the aircraft. The development of the propeller has experienced a process from rise to decline and rise again. Calculation of propeller performance and wind tunnel experiments are the basis for propeller design and application.
The most important content of the icing wind tunnel test is to determine the critical ice type and the range of the icing area required for the anti-icing design of the aircraft. In the dynamic test, it is also necessary to determine whether the surface needs anti-icing (de-icing) according to the influence of icing on the performance of the aircraft; for the determined anti-icing area, the effectiveness of anti-icing and de-icing should be grasped according to the icing conditions. Therefore, it is very beneficial to carry out in-depth research on new concepts and new technologies.
Rapid adjustment of wind speed in test section
A supersonic wind tunnel refers to a wind tunnel where the Mach number M of the airflow in the experimental section of the wind tunnel is between 1.4 and 5.
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.
A hypersonic wind tunnel means that the Mach number in the experimental section ranges from about 5 to 14, and the airflow temperature is high enough to prevent liquefaction in the experimental section when the airflow isentropically expanded to the above Mach number, but there is no wind high enough to produce real gas effects. Hole.
){kind=link}