Measurements of Fluctuating Pressures in 8- by 6-foot Supersonic Wind Tunnel for Mach Number Range of 0.56 to 2.07National Aeronautics and Space Administration, 1970 - 30 pages |
Other editions - View all
Common terms and phrases
0-percent porosity 1-percent-porosity test section 2.2 Mach number 3.1 percent 6-foot supersonic wind 800-hertz peak AC Pp-p Air flow amplitudes to rms App-p average rms pressure balance chamber bellmouth compressor Cprms displays of fluctuating disturbance at 500 dynamic pressure Effect of Mach Fluctuating peak-to-peak pressure fluctuating pressure coefficients Fluctuating pressure data fluctuating pressure peak-to-peak Fluctuating rms pressure hertz Instantaneous rms pressure MACH NUMBER RANGE maximum nonporous test section number on fluctuating PBal/Po peak-to-peak pressure coefficient percent 6.2 percent of dynamic porosity of 3.1 porous region porous test section Power spectral density presented in figure pressure disturbances Pressure Fluctuations pressure peak-to-peak amplitudes pressure perturbations pressure transducer pressures for transducer Ratio of fluctuating results were similar Reynolds number rms amplitudes rms pressure coefficient Root-mean-square amplitudes Schlieren shown in figure Spectral displays subsonic Mach numbers supersonic Mach numbers supersonic wind tunnel test sec test section porosity test section wall Transducer K4 Transonic