Russian Research on Experimental Hydrogen-Fueled Dual-Mode Scramjet: Conception and Preflight Tests

Abstract

The experience of model dual-modescramjet (DMSCRAM) creation and the main results of ground and pre ight tests are analyzed in this paper beginning from the conception choice, goals, and working program implemented for about 15 years, preceding to the rst ight test of hypersonic ight laboratory. Design schemes for plane and axisymmetrical engine concept are examined. The description of experimental test facilities, test instrumentation, and methods of readings treatment used in ground-test procedure of DMSCRAM are given. The test results of ground model engine at Mach-number range M = 3.5-6.5 and ground test-results for ight type engine at M = 5 were cited and con rmed the durability and readiness of developed DMSCRAM for ight tests. Nomenclature= cross-section area G = mass fuel, air rate g = relative fuel consumption I = ow impulse M = Mach number P Q = heat release parameter Q comb = heat resulted in fuel combustion Q W = summary heat ux into the duct walls q w = speci c heat ux into the wall q 1 = freestream dynamic pressure R = thrust Re = Reynolds number T = temperature X = drag force ® = angle, heat-transfer coef cient = fuel/air equivalence ratio ± ® = heat-transfer nonuniformity coef cient, ± ®;cool D .® max ® min /=® averagé = combustion ef ciency » 6 = nozzle impulse loss coef cient, » 6 D .1 I real =I ideal / ¾ = total pressure recovery coef cient ' = inlet capture ratio Subscripts at = angle of attack c, comb = combustor cool = cooling system, coolant rz = recirculation zone t = total parameters th = inlet throat w = wall 6 = summary value I, II, III, = rows of fuel injectors IV, and V 1 = freestream parameters Presented as Paper 98-1586 at