Analysis of wind-tunnel boundary-layer transition experiments on axisymmetric bodies at transonic speeds using compressible boundary-layer stability theoryThe design of laminar flow fuselages and advanced swept wings at high-subsonic compressible speeds can benefit from a correlation of compressible transition experiments with the e exp n transition-prediction method. A computational analysis has been conducted to investigate the detailed transition measurements obtained by Boltz et al. (1956, 1960) for two bodies-of-revolution. Nonadiabatic wall conditions were included in the analysis when wall-temperature measurements were available.
Document ID
19880034781
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Vijgen, P. M. H. W. (High Technology Corp. Hampton, VA, United States)
Dodbele, S. S. (Vigyan Research Associates, Inc. Hampton, VA, United States)
Pfenninger, W. (Analytical Services and Materials, Inc. Hampton, VA, United States)
Holmes, B. J. (NASA Langley Research Center Hampton, VA, United States)