J. Marroquin

• Results of A M = 5.3 heat transfer test of the integrated vehicle using phase-change paint techniques on the 0.0175-scale model 56-OTS in the NASA/AMES Research Center 3.5-foot hypersonic wind tunnel (IH-42)
• Results of aeroheating DFI and ET design-data test on a 0.0175-scale model 60-OTS conducted in the Von Karman gas dynamics facility (VKF) 40-inch supersonic and the 50-inch hypersonic wind tunnels A&C (IH-97A/B/C)
• Results of the AFRSI rewaterproofing systems screening test in the NASA/AMES Research Center (ARC) 2x2-foot transonic wind tunnel (OS-310)
• Results of wind tunnel tests of an ASRM configured 0.03 scale space shuttle integrated vehicle model (47-OTS) in the AEDC 16-foot transonic wind tunnel (IA613A)