Development of AFE aerobrake aerothermodynamic data bookThe computation method developed for the NASA Aeroassist Flight Experiment (AFE) data book generates a design reference for the AFE's aerothermodynamic environment using an optimized technology for a 4100-lb vehicle. This environment is defined by convective, radiative, and total heating rates, radiation equilibrium temperatures, and local surface pressures along the AFE pitch-plane and associated off-pitch planes. The Boundary Layer Integral Matrix Procedure is the major program code used in this analysis; a partially catalytic wall was assumed on the basis of measured recombination rates.
Document ID
19890055877
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ting, Paul C. (Lockheed Engineering and Sciences Co. Houston, TX, United States)
Rochelle, W. C. (Lockheed Engineering and Sciences Co. Houston, TX, United States)
Mueller, S. R. (Lockheed Engineering and Sciences Co. Houston, TX, United States)
Colovin, J. E. (Lockheed Engineering and Sciences Co. Houston, TX, United States)
Scott, C. D. (Lockheed Engineering and Sciences Co. Houston, TX, United States)
Curry, D. M. (NASA Johnson Space Center Houston, TX, United States)