Results from an investigation of the effects of underexpanded engine exhaust flow on the aerodynamic performance and stability of a cruise airplane at Mach 6 are presented. The influence of wing reflex angle and nozzle geometry on exhaust flow interference effects was investigated on a flat-plate model. The experiments were conducted at a free-stream Reynolds number of 17.05 X 10 (to the 6 power) based on the length of the airplane model over a model angle-of-attack range of 0(degrees) to 10(degrees) and at nozzle static-pressure ratios from 1 to approximately 4.

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Some fundamental aspects of a regeneratively cooled, upper stage rocket plane with external-burning thrust augmentation are investigated analytically. Cases considered are only the ejected coolant is burned externally and all of the thrust required for sustained cruise is provided by external burning. One conclusion is that external-burning configurations offer an apparent advantage over internal propulsion systems in that the total vehicle cooling requirement for high-speed operation is much less for the external- burning regeneratively cooled configuration. Also, the fuel required for propulsion by an external-burning configuration greatly exceeds the fuel required for cooling.