A simulation technique for jet temperature effects on nozzle-afterbody drag at transonic Mach numbers

The objective of this investigation was to implement and demonstrate the performance of a technique for correcting noezlelafterhody drag coefficient for jet temperature effects at transonic'freeStream Mach numbers. The technique corrects axisymmetric nozzle afterbody drag coefficient for jettemperature-related effects associated with inviscid jet plume shape and with jet mixing or entrainment. Data were utilized from experiments conducted in the AEDC I-ft and 16-ft transonic wind tunnels with two strut-mounted axisymmetric models incorporating a 15-deg afterbody hoattail angle. technique predicts jet temperature effects on afterbody drag coefficient (based on body diameter) within 50 drag counts at subsonic free-stream Mach numhers and 100 drag counts at supersonic free-stream Mach numbers. The correction