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angle approximately attached BETAM blade body calculated cells Center characteristics coefficient collector communications components compressor configuration Continued cooling coordinate corrected cost cycles design speed determined direction distribution edge effect efficiency elevon end plate engine equation field Figure flight flow fuel function heat INCIDENCE increased inlet LOSS MACH MACH NO MERID mass maximum measured meters module NASA º º obtained operating oxidation PEAK Percent of design performance position presented pressure pressure ratio propulsion radiation range ratio reading recirculation reference region Report Research rotor separator shown in figure shows slots solar array Space spacecraft SPAN speckle stability stage static stator surface TABLE temperature thermal thruster TOT PROF tube unit values weight wing
Page 1 - No. 12. Sponsoring Agency Name and Address 13. Type of Report and Period Covered 15.
Page 14 - AMES RESEARCH STAFF : Equations, Tables, and Charts for Compressible Flow. NACA Rep. 1135, 1953.
Page 2 - Orifice weight flow, total pressures, static pressures, and temperatures were all corrected to sea-level conditions based on the rotor-inlet conditions. RESULTS AND DISCUSSION The results of this investigation are presented in the...
Page 1 - For sale by the National Technical Infoimation Service, Springfield, Virginia 22161 1 Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA TM X-3465 4.