国防科技大学学报
國防科技大學學報
국방과기대학학보
JOURNAL OF NATIONAL UNIVERSITY OF DEFENSE TECHNOLOGY
2009年
6期
57-61
,共5页
高超声速%风洞%风洞调试%流场校测
高超聲速%風洞%風洞調試%流場校測
고초성속%풍동%풍동조시%류장교측
hypersonic%wind tunnels%test of wind tunnel%calibration of flow field
介绍了新近建成的马赫数为2.5～7.0的Φ200mm 高超声速风洞(Φ200 Hypersonic Wind Tunnel,HWT-200)调试情况及空风洞流场校测结果.调试校测结果表明,风洞的总温、总压、运行时间等参数完全达到了设计要求,顺利实现了宽马赫数范围下的超声速/高超声速运行;本风洞有较大的实验段流场均匀区,各流场的马赫数均方根偏差全部达到GJB(1179-91)的合格指标,一部分达到了先进指标.风洞运行时间不少于20s,是一座参数范围较宽、运行成本较低、维护方便、可用于空气动力学教学试验和基础性科学研究的设备.
介紹瞭新近建成的馬赫數為2.5～7.0的Φ200mm 高超聲速風洞(Φ200 Hypersonic Wind Tunnel,HWT-200)調試情況及空風洞流場校測結果.調試校測結果錶明,風洞的總溫、總壓、運行時間等參數完全達到瞭設計要求,順利實現瞭寬馬赫數範圍下的超聲速/高超聲速運行;本風洞有較大的實驗段流場均勻區,各流場的馬赫數均方根偏差全部達到GJB(1179-91)的閤格指標,一部分達到瞭先進指標.風洞運行時間不少于20s,是一座參數範圍較寬、運行成本較低、維護方便、可用于空氣動力學教學試驗和基礎性科學研究的設備.
개소료신근건성적마혁수위2.5～7.0적Φ200mm 고초성속풍동(Φ200 Hypersonic Wind Tunnel,HWT-200)조시정황급공풍동류장교측결과.조시교측결과표명,풍동적총온、총압、운행시간등삼수완전체도료설계요구,순리실현료관마혁수범위하적초성속/고초성속운행;본풍동유교대적실험단류장균균구,각류장적마혁수균방근편차전부체도GJB(1179-91)적합격지표,일부분체도료선진지표.풍동운행시간불소우20s,시일좌삼수범위교관、운행성본교저、유호방편、가용우공기동역학교학시험화기출성과학연구적설비.
The newly finished Φ200 hypersonic wind tunnel(Mach numbers2.5 to 7) has been tested and calibrated. The results of calibration indicating total temperature, total pressure, operating time of HWT-200 have accorded with the purpose of design. HWT-200 can run within large Mach number span at supersonic/hypersonic flow. The rms of Mach numbers (σ_M) at all test sections Math numbers from 2.5 to 7.0 reaches the requirement of GJB1179-91. A large, uniform region of flow was documented. Operational time of HWT-200 is no less than 20s. So, HWT-200 is a facilitv Which can be used for teaching of aerodynamic experiments and elementariy scientific researches.
