The use of shear-stress-sensitive (SSS) liquid crystals (LCs) has been evaluated as a boundary-layer transition detection technique for hypersonic flows. Experiments were conducted at Mach 8 in the Sandia National Laboratories Hypersonic Wind lunnel using a flat-plate model at near-0-deg angle of attack over the freestream unit-Reynolds-number range (1.2-5.8) x!0 6 /ft. Standard 35-mm color photography and Super VHS color video were used to record LC color changes due to varying surface shear stress during the transition process for a range of commercial SSS liquid crystals. Visual transition data were compared with an established method using calorimetric surface heat-transfer measurements to evaluate the LC technique. It is concluded that the use of SSS LCs can be an inexpensive, safe, and easy-to-use boundary-layer transition detection method for hypersonic flows. However, a valid interpretation of the visual records requires careful attention to illumination intensity levels and uniformity and to lighting and viewing angles, some prior understanding of the general character of the flow, and the selection of the appropriate liquid crystal for the particular flow conditions. Nomenclature M = Mach number P = pressure, psia q = heat transfer rate, Btu/ft 2 • s Re = unit Reynolds number, ft" 1 T -temperature, °R t = time, s X = distance from leading edge, in. a = angle of attack, deg r = shear stress, lbf/ft 2 Subscripts c = calculated cw = cold wall i = initial conditions, t = 0 m = measured r = recovery 0 = stagnation conditions oo = freestream conditions