High Reynolds Number Tests of a C141A Aircraft Semispan Model to Investigate Shock-induced Separation |
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1.0 X/C Figure 16T TRANSITION FIXED 20 REYNOLDS NUMBER AEDC 16T TRANSITION aeroelastic aircraft airfoil ALPHA D+XO angle of attack boundary layer C-141 SEMI-SPAN MODEL CFF SMOOTH AEDC CFF TRANSITION FIXED CH141 SEMI-SPAN Compressible Flow Facility configuration correlation D+XO A ALPHA D+XO ALPHA 1234 DATE ALPHA degree angle Edge Pressure Recovery Effect on Shock Figure 12 FIXED CFF SMOOTH FLIGHT REFERENCE flight test FREE PAGE FIGURE high Reynolds number highest Reynolds number Location and Trailing Lockheed-Georgia Company low Reynolds numbers LSHT 10 DATE LSHT DATE Mach number MODEL ME 825 outboard stations Panel Model porosity pressure coefficient pressure distribution pylons and nacelles scale effects SEMI-SPAN MODEL 80 SEMI-SPAN MODEL M=-825 semispan test shock location Shock-Induced Separation SMOOTH AEDC 16T spanwise contamination spanwise station stagnation pressure station 389 station 637 SUPPORT TANG FAIRED trailing-edge pressure recovery trailing-edge separation TRANSITION FIXED CFF TRANSITION FIXED REFERENCE wing X/CSH