Wind Tunnel Flow Field Visualizations of the Space Launch System Vehicle Ascent

Garbeff, Theodore J, II ; Baerny, Jennifer K ; Ross, James C

关键词: INFRARED IMAGERY;    SHADOWGRAPH PHOTOGRAPHY;    SPACECRAFT LAUNCHING;    SPACE LAUNCH SYSTEM (SLS);    PRESSURE SENSITIVE PAINTS;    FLOW VISUALIZATION;    WIND TUNNEL TESTS;   

RP-ID  :  ARC-E-DAA-TN63676

学科分类：航空航天科学

美国|英语

来源: NASA Technical Reports Server

【 摘 要 】

A series of wind tunnel tests were conducted to characterize the force-and-moment, and aeroacoustic environment of several configurations of the Space Launch System during ascent. The tests were conducted in the 11-by-11 foot transonic and 9-by-7 foot supersonic test sections at NASA Ames research center. Throughout these experiments data was collected from several types of instrumentation including: multicomponent force-and-moment strain gage balances, dynamic and steady-state pressure sensors, unsteady and steady pressure-sensitive paint, time-resolved shadowgraph and infrared imaging. The following details results and analysis from the time-resolved shadowgraph and infrared imaging data systems. The time-resolved shadowgraph and infrared imaging provided a qualitative measurement of the near-field turbulent fluctuations. These results helped provide context to the relative magnitude and frequency content of the fluid-structure-interaction driving the surface pressure phenomena characterized by the discrete pressure transducers and unsteady pressure sensitive paint.