The specific thrust level and variation rule of solid fuel scramjet combustor were researched both by numerical and experimental methods. A methane-burning vitiated air heater was designed and made to simulate flight environment of Mach 6 at 25km altitude. Based on the two dimensional flow field structures, a new quasi-one dimensional numerical method was established. The typical unsteady matter of solid fuel scramjet combustion and flow was transformed into a steady calculation of every moment in this method. And it can be used to simulate the parametric changing process of combustor quickly. Self-ignition and fuel regression rate characteristics in current experiment were consistent with results from previous works. And the agreement between the numerical and experimental results was generally good too. The specific thrust can reach the level of (600 ～~ 800) N/kg•s in the designed flight environment. It was found that the specific thrust decrease with the total pressure loss increase during the working process.
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