关键词: 超音速进气道;腹部进气道;风洞试验;迎角;性能

Abstract: The experimental result of aft bypass supersonic inlet model in wind tunnel test is presented in this paper. And inlet performance, specially at high angle of attack and yaw is discussed in detail.There are two models for wind tunnel test. Model A is twin half-cone inlets aft-installed under fuselage. Model B is four symmetrical inlets insta-lled around fuselage. The inlets with single cone and mixed external/internal compression were tested at flight Mach number 2.0-2.5, at which conical shock wave enters inlet’s entrance) attack angle ranging from - 14° to 13° and yaw angle ranging from 0° to 15°.Experimental results show that both models can operate stably at high angles of attack and yaw. The total pressure measurement under the mixing condition at dump chamber entrance is feasible and the pressure recovery measured is satisfactory.

Key words: Supersonic inlet;Ventral inlet;wind-tunnel test;Angle of attack;Performance