Fluorescence Visualization of Hypersonic Flow over Rapid Prototype Wind-Tunnel Models

摘要: Reentry models for use in hypersonic wind tunnel tests were fabricated using a stereolithography apparatus. These produced one day or less, which is significant time savings compared to the manufacture of ceramic metal models. The tested NASA Langley Research Center 31-Inch Mach 10 Air Tunnel. Most did not survive repeated tunnel, and several failure modes identified. Planar laser-induced fluorescence (PLIF) nitric oxide (NO) was used visualize flowfields wakes these Pure NO either seeded through tubes plumbed into model via tube attached strut holding model, provided localized addition s wake porous cylinder end tube. Models included 2-inch diameter Inflatable Vehicle Experiment (IRVE) 5-inch Crew Exploration (CEV) Various configurations studied including different sting placements relative models, orientations attachment angles, seeding methods. angle attack also varied location laser sheet scanned provide three-dimensional flowfield information. Virtual Diagnostics Interface technology, developed at Langley, data sets post processing. calibration "dotcards" investigated correct camera perspective lens distortions PLIF images. Lessons learned recommendations future experiments are discussed.