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addition aerodynamic Aeronautics and Space aircraft alloy angle approach approximately base baseline calculated Center characteristics coefficient combustor completed Concluded configuration Continued corrected determined diaphragm distribution edge effect efficiency energy engine error evaluation exit Figure flame flaps flight flow Form frequency fuel function increased indicated inflow inlet input ı ı ı length liquid located longitudinal Mach number measured NASA National Aeronautics noise Note nozzle obtained opening operating pattern percent performance pitch plug nozzle position presented pressure produced proposal PUBLICATIONS range ratio recorded reduction reference Reynolds number shown in figure shows sidewalls sound Space Administration stabilizer station suppressing surface tank TECHNICAL temperature thrust Transcript Type values velocity wing wire
Page 9 - Braslow, Albert L.; and Knox, Eugene C.: Simplified Method for Determination of Critical Height of Distributed Roughness Particles for Boundary -Layer Transition at Mach Numbers From 0 to 5.
Page 3 - Security Classif. (of this report) Unclassified 20. Security Classif. (of this pagel Unclassified 21. No. of Pages 115 22. Price" A 06 ' For sale by the National Technical Information Service.
Page 18 - A Preliminary Theoretical Study of the Expansion Tube, a New Device for Producing High-Enthalpy Short-Duration Hypersonic Gas Flows, NASA TR R-133 (1962) 54 VORREITER, JW and SHEPARD, Ch.
Page 49 - Calculation of the Absorbed Dose and Dose Equivalent From Neutrons and Protons in the Energy Range From 3.5 GeV to 1.0 TeV.
Page 53 - For sale by the National Technical Information Service. Springfield, Virginia 22161 1 Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA CR-2885 4. Title and Subtitle 5. Report Date "Computers for Real Time Market Survey" Flight Simulation: A July 1977 6.