Accession Number : ADP000223

Title :   Review of Shock Tube and Shock Tunnel Advancements at NAL,

Corporate Author : NATIONAL AEROSPACE LAB TOKYO (JAPAN)

Personal Author(s) : Soga,K. ; Wada,I.

Report Date : JUL 1981

Pagination or Media Count : 11

Abstract : Since it was organized in 1960, the Shock Tube Research Group of NAL has studied the various aerodynamic problems of hypersonic flight at high altitudes using a reflected shock tunnel, electrically heated shock tubes and a gun tunnel. These studies are reviewed briefly in this paper. In order to construct and operate a large-scale shock tunnel used for project works, a new operational method of short-duration wind tunnels using a large-orifice plate and high speed valves is proposed in this paper. The practicability of this method has been studied using the gun tunnel, and the results of these experiments are shown in this paper. The exclusion of the piston and the use of high speed valves to replace the diaphragms not only enable us to eliminate dust in the flow but also to reduce the tunnel reset time. (Author)

Descriptors :   *Shock tubes, *Shock tunnels, *Hypersonic flight, Wind tunnel tests, Hypersonic wind tunnels, State of the art, Japan

Distribution Statement : APPROVED FOR PUBLIC RELEASE