Experimental Investigation Of A Mach 5 Isentropic Spike Inlet At And Below Design Speed
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Author | : Leonard E. Stitt |
Publisher | : |
Total Pages | : 22 |
Release | : 1959 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Download Experimental Investigation of a Mach 5 Isentropic Spike Inlet at and Below Design Speed Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 1074 |
Release | : 1965 |
Genre | : Aeronautics |
ISBN | : |
Download Scientific and Technical Aerospace Reports Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 590 |
Release | : 1967 |
Genre | : Airplanes |
ISBN | : |
Download Conference on Hypersonic Aircraft Technology Book in PDF, Epub and Kindle
Author | : Earl C. Watson |
Publisher | : |
Total Pages | : 34 |
Release | : 1960 |
Genre | : Boundary layer control |
ISBN | : |
Download An Experimental Investigation at Mach Numbers from 2.1 to 3.0 of Circular Internal-compression Inlets Having Translatable Centerbodies and Provisions for Boundary-layer Removal Book in PDF, Epub and Kindle
Author | : United States. National Aeronautics and Space Administration Scientific and Technical Information Division |
Publisher | : |
Total Pages | : 1440 |
Release | : 1966 |
Genre | : Aeronautics |
ISBN | : |
Download NASA Scientific and Technical Reports Book in PDF, Epub and Kindle
Author | : Marvin G. Torrence |
Publisher | : |
Total Pages | : 66 |
Release | : 1975 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Download Experimental Investigation of a Mach 6 Fixed-geometry Inlet Featuring a Swept External-internal Compression Flow Field Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 56 |
Release | : 1961 |
Genre | : |
ISBN | : |
Download Investigation of the Compression Field and the Flow Distribution in the Throat of a Two Dimensional, Internal Compression, Mach Number 6.9 Inlet Book in PDF, Epub and Kindle
Author | : United States. National Aeronautics and Space Administration. Scientific and Technical Information Division |
Publisher | : |
Total Pages | : 1680 |
Release | : 1965 |
Genre | : Aeronautics |
ISBN | : |
Download A Selected Listing of NASA Scientific and Technical Reports for ... Book in PDF, Epub and Kindle
Author | : Paulo G. P. Toro |
Publisher | : |
Total Pages | : |
Release | : 1999 |
Genre | : |
ISBN | : |
Download Experimental Pressure Investigation of a "directed-energy Air Spike" Inlet at Mach 10 Book in PDF, Epub and Kindle
Author | : Joseph F. Wasserbauer |
Publisher | : |
Total Pages | : 50 |
Release | : 1996 |
Genre | : |
ISBN | : |
Download Experimental Investigation of the Performance of a Mach-2.7 Two-dimensional Bifurcated Duct Inlet with 30 Percent Internal Contraction Book in PDF, Epub and Kindle
An experimental study was conducted to determine the performance of a two-dimensional, mixed-compression bifurcated duct inlet system designed for a free-stream Mach number of 2.7. Thirty percent of the supersonic area contraction occurred internally. A movable ramp was used to vary the contraction ratio for off-design operation. Boundary layer bleed regions were located on the cowl, centerbody, and sidewall surfaces. There were also provisions for vortex generators on the cowl and centerbody of the subsonic diffuser. Data were obtained over the Mach number range of 2.0 to 2.8 and at angles of yaw from 0 deg. to the maximum value prior to inlet un-start. The test at Mach 2.8 was to obtain data for an over- speed condition. The Reynolds number varied from 2.5 to 2.3 million/ft for Mach numbers above 2.5. At Mach numbers of 2.5 and lower, the Reynolds number was set at 2.5 million/ft. Bleed patterns, vortex generator patterns, and ramp position were varied, and three inlet configurations were selected for more extensive study. Two of these configurations had self-starting capability. The self-starting configuration that was developed produced 89 percent total pressure recovery at the compressor face station with 6.8 percent total bleed. The compressor face distortion was about 16 percent. Vortex generators were extremely effective in re-distributing flow but were not as effective in reducing distortion. Excellent flow symmetry was achieved between the separated halves of the inlet, and twin-duct instability was not observed. The ramp tip shock was steeper than expected. This caused the cowl lip shock to be reflected from the ramp instead of being cancelled at the shoulder. However, peak recovery at the throat was still obtained with the ramp near the design position.