Static performance of a fixed-geometry exhaust nozzle incorporating porous cavities for shock-boundary layer interaction control / / Scott C. Asbury and Craig A. Hunter |
Autore | Asbury Scott C. |
Pubbl/distr/stampa | Hampton, Virginia : , : National Aeronautics and Space Administration, Langley Research Center, , August 1999 |
Descrizione fisica | 1 online resource (134 pages) : illustrations |
Collana | NASA/TM |
Soggetto topico |
Exhaust nozzles
Porosity Hole geometry (mechanics) Cavities Thrust vector control |
Formato | Materiale a stampa |
Livello bibliografico | Monografia |
Lingua di pubblicazione | eng |
Record Nr. | UNINA-9910706145403321 |
Asbury Scott C. | ||
Hampton, Virginia : , : National Aeronautics and Space Administration, Langley Research Center, , August 1999 | ||
Materiale a stampa | ||
Lo trovi qui: Univ. Federico II | ||
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Static performance of six innovative thrust reverser concepts for subsonic transport applications : summary of the NASA Langley Innovative Thrust Reverser Test Program / / Scott C. Asbury and Jeffrey A. Yetter |
Autore | Asbury Scott C. |
Pubbl/distr/stampa | Hampton, Virginia : , : National Aeronautics and Space Administration, Langley Research Center, , July 2000 |
Descrizione fisica | 1 online resource (30 pages, 334 unnumbered pages) : color illustrations |
Collana | NASA/TM |
Soggetto topico |
Airplanes - Brakes
Airplanes - Design and construction Airplanes - Motors - Thrust Airplanes - Turbofan engines Jet planes - Thrust reversers - Testing Thrust reversal Turbofans Aeronautical engineering Aircraft design Performance tests |
Formato | Materiale a stampa |
Livello bibliografico | Monografia |
Lingua di pubblicazione | eng |
Altri titoli varianti | Static performance of six innovative thrust reverser concepts for subsonic transport applications |
Record Nr. | UNINA-9910707886903321 |
Asbury Scott C. | ||
Hampton, Virginia : , : National Aeronautics and Space Administration, Langley Research Center, , July 2000 | ||
Materiale a stampa | ||
Lo trovi qui: Univ. Federico II | ||
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