Boundary-layer and aeroheating characteristics of several X-33 configuratio
ns have been experimentally examined in the NASA Langley Research Center 20
-Inch Mach 6 Air Tunnel. Global surface heat transfer distributions, surfac
e streamline patterns, and shock shapes were measured on 0.013-scale models
at Mach 6 in air. Parametric variations include angles of attack of 20, 30
, and 40 deg; Reynolds numbers based on model length of 9 x 10(5) to 6.6 x
10(6); and body-flap deflections of 0, 10, and 20 deg. The effects of discr
ete and distributed (in the form of wavy wall bowed panels) roughness on bo
undary-layer transition, which included trip height, size, location, and di
stribution, both on and off the windward centerline, were investigated. The
discrete roughness results on centerline were used to provide a transition
correlation for the X-33 flight vehicle that was applicable across the ran
ge of reentry angles of attack. The attachment line discrete roughness resu
lts were shown to be consistent with the centerline results because no incr
eased sensitivity to roughness along the attachment line was identified. Th
e effect of bowed panels was qualitatively shown to be less effective than
the discrete trips; however, the distributed nature of the bowed panels aff
ected a larger percent of the aft-body windward surface than a single discr
ete trip.