Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Cold Flow Performance Of Several Variations Of A Ram Air Cooled Plug Nozzle For Supersonic Cruise Aircraft PDF full book. Access full book title Cold Flow Performance Of Several Variations Of A Ram Air Cooled Plug Nozzle For Supersonic Cruise Aircraft.
| Author | : Douglas E. Harrington |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1974 |
| Genre | : Jet nozzles |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 104 |
| Release | : 1980 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 116 |
| Release | : 1977 |
| Genre | : Astronautics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 948 |
| Release | : 1974 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 936 |
| Release | : 1973 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 2834 |
| Release | : 1975 |
| Genre | : Government publications |
| ISBN | : |
| Author | : United States. Superintendent of Documents |
| Publisher | : |
| Total Pages | : 1408 |
| Release | : 1976 |
| Genre | : United States |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 68 |
| Release | : 1975 |
| Genre | : Aeronautics |
| ISBN | : |
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
| Author | : Oak Ridge National Laboratory |
| Publisher | : |
| Total Pages | : 1458 |
| Release | : 1976 |
| Genre | : Fuel |
| ISBN | : |
| Author | : Stanley M. Nosek |
| Publisher | : |
| Total Pages | : 29 |
| Release | : 1976 |
| Genre | : Airplanes |
| ISBN | : |
Plug nozzle film cooling data were obtained downstream of a slot located at 42 percent of the total plug length on a J-85 engine. Film cooling reduced the aft end wall temperature as much as 150 K, reduced total pressure loss in the upstream convection cooling passages by 50 percent, and reduced estimated compressor bleed flow requirement by 14 percent compared to an all convectively cooled nozzle. Shock waves along the plug surface strongly influenced temperature distributions on both convection and film cooled portions. The effect was most severe at nozzle pressure ratios below 10 where adverse pressure gradients were most severe.
