2 edition of **More tests with a variable ramp intake having a design mach number of 2.2** found in the catalog.

More tests with a variable ramp intake having a design mach number of 2.2

M. C. Neale

- 77 Want to read
- 11 Currently reading

Published
**1967**
by H.M.S.O. in London
.

Written in English

- Airplanes -- Jet propulsion -- Air intakes.

**Edition Notes**

Statement | by M. C. Neale and P. S. Lamb. |

Series | Aeronautical Research Council. Current papers,, no. 938, Current papers (Aeronautical Research Council (Great Britain)) ;, no. 938. |

Contributions | Lamb, P. S., joint author. |

Classifications | |
---|---|

LC Classifications | L507 .G77 no. 938 |

The Physical Object | |

Pagination | 16 p. |

Number of Pages | 16 |

ID Numbers | |

Open Library | OL5588308M |

LC Control Number | 67108722 |

OCLC/WorldCa | 6163430 |

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More tests mlth a variable ramp intake having a design Mach number of - by - M. Neale and P. Lamb SUMMARY Results are repvted of tests on a two-dimensional combined external/internal compressIon Intake having a design Mach number of File Size: 2MB.

Tests with a variable ramp intake having combined external/internal compression, and a design Mach number of - by - M. Neale and P. Lamb August, Results are reported of tests on a two-dimensional combined external/internal compression intake having a.

" Some Test with Variable Ramp Intake Having Combined External/Internal Compression, and a Design Mach Number of" Aeronautical Research Council. A variable-sweep wing, colloquially known as a "swing wing", is an airplane wing, or set of wings, that may be swept back and then returned to its original straight position during allows the aircraft's shape to be modified in flight, and is therefore an example of a variable-geometry aircraft.

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The Rolls-Royce/SNECMA Olympus (which powered the Concorde) used a complex intake-ramp system to improve the engine's efficiency and prevent an engine shutdown or failure during supersonic flight. 45, ft at a freestream Mach number ofand with an over-wing Mach number of Two similar inlet designs were tested experimentally in the 8.

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A rectangular stream-tube stream-traced Busemann intake, shown in Fig. 27, for a design Mach number was tested in Mach and Mach wind tunnels to investigate the overall performance. To obtain off-design performance data the model shape was based on Mach Busemann flow and the leading edge was truncated at a surface angle of 6 Cited by: 1.

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