双模态冲压发动机高超进气道的实验研究

推进技术 ›› 2001, Vol. 22 ›› Issue (6): 473-475.

双模态冲压发动机高超进气道的实验研究

杨进军,张堃元,徐辉,徐惊雷

南京航空航天大学能源与动力学院江苏南京210016;南京航空航天大学能源与动力学院江苏南京210016;南京航空航天大学能源与动力学院江苏南京210016;南京航空航天大学能源与动力学院江苏南京210016

发布日期:2021-08-15

Experiment study on supersonic inlet in dual-model scramjet

Coll.of Energy and power,Nanjing Univ.of Aeronautics and Astronautics,Nanjing 210016,China;Coll.of Energy and power,Nanjing Univ.of Aeronautics and Astronautics,Nanjing 210016,China;Coll.of Energy and power,Nanjing Univ.of Aeronautics and Astronautics,Nanjing 210016,China;Coll.of Energy and power,Nanjing Univ.of Aeronautics and Astronautics,Nanjing 210016,China

Published:2021-08-15

摘要/Abstract

摘要： 设计了侧压角为 6° ,后掠角 4 5° ,斜楔板压缩角分别为 4°和 8°的两套带隔离段的高超三维侧压式进气道 ,通过风洞实验研究了来流马赫数、出口反压、斜楔板压缩角以及隔离段等对进气道性能的影响。实验结果表明 ,在高来流马赫数及较小的斜楔板压缩角时 ,进气道的流量系数、总压恢复系数较高。总增压比在不同斜楔板压缩角时基本保持不变。

关键词: 高超声速进气道;侧压式进气道;进气道试验;进气道流量系数;进气道总压恢复系数

Abstract: Two types of three dimensional sidewall compression inlet models with 6° sidewall angle,45° swept angle and isolator were designed and experimentally investigated.The models were specially designed in 4° and 8° ramp angle.The Mach numbers of wind turnal were 5.3 and 3.85.The experimental results indicated that mass flow rate and total pressure recovery are higher in the condition of higher Mach number and lower ramp angle.Static pressure ratio in model remains constant in the condition of different ramp angles.

Key words: Hypersonic inlet;Sidewall compression inlet;Inlet lest;Flow coefficient of inlet;Total pressure recovery coefficient of inlet

杨进军,张堃元,徐辉,徐惊雷. 双模态冲压发动机高超进气道的实验研究[J]. 推进技术, 2001, 22(6): 473-475.