A comparison of experimental and computational results for 5 and 10 degree cones at high Mach numbersExperiments were performed on 5 and 10 deg slender cones at a velocity of approximately 5 km/sec in the NASA-Ames ballistic ranges. The flowfields for the cones were computed using ideal-gas and chemical nonequilibrium-air parabolized Navier-Stokes codes. Experimentally determined drag coefficients and shock shapes are compared with the results of the computer codes. Both the flight-data analysis methods and the computational codes are examined to achieve the most meaningful comparison. Under the conditions of the experiments, skin-friction drag makes up approximately 50 percent of the total drag for the 5 deg cone and 30 percent of the total drag for the 10 deg cone. Computed drag coefficients of the 10 deg cone agree well with the experimental values; predictions fall below the experimental values for the 5 deg cone.
Document ID
19880060763
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Strawa, A. W. (NASA Ames Research Center Moffett Field, CA, United States)
Prabhu, D. K. (NASA Ames Research Center Moffett Field, CA, United States)