Download e-book for kindle: Concept to Reality: Contributions of the NASA Langley by Chambers J.R.

By Chambers J.R.

ISBN-10: 0756736870

ISBN-13: 9780756736873

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Read or Download Concept to Reality: Contributions of the NASA Langley Research Centerto U.S. Civil Aircraft of the 1990s PDF

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Extra info for Concept to Reality: Contributions of the NASA Langley Research Centerto U.S. Civil Aircraft of the 1990s

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Large commercial aircraft operate at cruise speeds high enough to require the radical area-ruled fuselage shapes necessary for a near-sonic transport. However, designers of large commercial transports have used the principles of area ruling to solve “local” flow problems and interference effects—especially nacelle integration issues for wingor fuselage-mounted engines. Following the early development of the area rule, Whitcomb continued his remarkably intuitive approach to transonic aerodynamics in efforts that 48 Concept to Reality AREA RULE Applications to Civil Aircraft showed how the principles involved in the area rule could be used to enhance the overall performance of transport aircraft, without the radical reshaping of the entire aircraft required for the near-sonic transport configurations.

Langley then turned its research emphasis to improving aerodynamic efficiency at lower cruise speeds by using the beneficial characteristics of the supercritical wing. The principles of the area rule, however, continued to be employed by designers for solutions to configuration integration issues. S. large commercial aircraft operate at cruise speeds high enough to require the radical area-ruled fuselage shapes necessary for a near-sonic transport. However, designers of large commercial transports have used the principles of area ruling to solve “local” flow problems and interference effects—especially nacelle integration issues for wingor fuselage-mounted engines.

Thus, to obtain the minimum shock wave drag, the overall distribution should be that of a smooth body with minimum drag. Whitcomb theorized that the most obvious way to achieve this distribution was to remove the equivalent Cross-sectional area for wing-body configuration and for wing cross-sectional area from that equivalent of revolution. Note bump in cross-sectional area of the fuselage cross-sectional area of body of revolution caused by addition of wing area. Concept to Reality 45 AREA RULE Background Richard T.

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Concept to Reality: Contributions of the NASA Langley Research Centerto U.S. Civil Aircraft of the 1990s by Chambers J.R.


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