Abstract
주동체, 쌍동 부스터 및 핀으로 구성된 로켓의 기본적 공력 특성을 파악하기 위한 고속 풍동시험을 국방과학연구소의 삼중음속풍동에서 마하수 0.4~4.0에 대해 수행하였다. 시험 형상은 3단형 과학로켓 초기 설계 형상의 6 % 축소 모형으로 주동체 단독, 주동체/핀, 주동체/부스터 및 주동체/부스터/핀 등의 형상과 주동체 길이, 부스터 간격 및 뱅크각 효과에 대해 시험하였다. The high speed wind tunnel test for the study of the basic aerodynamic characteristics of the rocket with twin strap-on boosters was performed using ADD trisonic wind tunnel on the Mach number range of 0.4~4.0. The 6 % scale model of the early design version of Korean sounding rocket was tested. The tested configurations were core only, core/fins, core/boosters and core/boosters/fins. The effects of core length, gap between core and booster, and bank angle were investigated.
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