This paper discusses experimental research on the aerodynamic characteristics of base bleeding with combustion of fuel-rich solid fuel in flows at subsonic, transonic, and supersonic speeds. The effects of ejection parameter, freestream Mach number, geometry parameter of jet hole, rotary speed of model, and combustion temperature at jet hole on the base drag reduction rate for the model are investigated. The results show significant differences of drag reduction characteristics between base combustion of fuel-rich solid fuel and base bleeding of cold or hot gas. Nomenclature C Db = base-drag coefficient without base combustion (or base-bleed) C Dbj = base-drag coefficient with base combustion (or base-bleed) &C Db = (C Db = base-drag reduction rate due to base -C Dbj )/C Db combustion (or base-bleed) D b = base diameter DJ = jet hole diameter / = m/pVS b = ejection parameter Mso = Mach number of freestream m = mass burning rate of fuel-rich solid fuel P b = base pressure of model P^ = static pressure of freestream R = mean linear burning rate with rotation -0 = mean linear burning rate with zero rotary speed S b = base area of model T b= combustion temperature at jet hole T 0 = total temperature of freestream t = combustion time V = velocity of freestream p = density of freestream -(dC Db /dI) I=0 = drag reduction efficiency of base combustion (or base bleed)
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