Flight Tests Of A Leading Edge Area Suction On A Fighter Type Airplane With A 35 Degree Sweptback Wing
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Flight Tests of a Leading edge Area Suction on a Fighter type Airplane with a 35 Degree Sweptback Wing
Author | : Richard S. Bray,Robert C. Innis |
Publsiher | : Unknown |
Total Pages | : 34 |
Release | : 1955 |
Genre | : Aeronautics |
ISBN | : UOM:39015086432781 |
Download Flight Tests of a Leading edge Area Suction on a Fighter type Airplane with a 35 Degree Sweptback Wing Book in PDF, Epub and Kindle
Tests have been made to determine the flight characteristics of an F-86F airplane equipped with a leading-edge area-suction boundary-layer-control system, and to investigate the possible operational limitations imposed on a fighter-type airplane by such an installation. The results of the flight tests are compared with those of full-scale wind-tunnel tests of a similar installation on a model incorporating F-86 wing panels. The basic porous-area distribution tested extended the full length of the wing leading edge. Suction power was provided by a modified turbosupercharger which was driven by air bled from the compressor of the airplane's jet engine.
IRE Transactions on Human Factors in Electronics
Author | : Institute of Radio Engineers. Professional Group on Human Factors in Electronics |
Publsiher | : Unknown |
Total Pages | : 730 |
Release | : 1960 |
Genre | : Electronic apparatus and appliances |
ISBN | : UOM:39015011851519 |
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Index to NASA Technical Publications
Author | : United States. National Aeronautics and Space Administration |
Publsiher | : Unknown |
Total Pages | : 135 |
Release | : 1960-07 |
Genre | : Electronic Book |
ISBN | : STANFORD:36105024165701 |
Download Index to NASA Technical Publications Book in PDF, Epub and Kindle
The Engineer
Author | : Anonim |
Publsiher | : Unknown |
Total Pages | : 1192 |
Release | : 1951 |
Genre | : Engineering |
ISBN | : MINN:31951000651382W |
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Congressional Record
Author | : United States. Congress |
Publsiher | : Unknown |
Total Pages | : 888 |
Release | : 2024 |
Genre | : Law |
ISBN | : STANFORD:36105009911525 |
Download Congressional Record Book in PDF, Epub and Kindle
The Congressional Record is the official record of the proceedings and debates of the United States Congress. It is published daily when Congress is in session. The Congressional Record began publication in 1873. Debates for sessions prior to 1873 are recorded in The Debates and Proceedings in the Congress of the United States (1789-1824), the Register of Debates in Congress (1824-1837), and the Congressional Globe (1833-1873)
Scientific and Technical Aerospace Reports
Author | : Anonim |
Publsiher | : Unknown |
Total Pages | : 992 |
Release | : 1974 |
Genre | : Aeronautics |
ISBN | : OSU:32435027927771 |
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Full scale Wind tunnel Tests of a Small Unpowered Jet Aircraft with a T Tail
Author | : Paul T. Soderman,Thomas N. Aiken |
Publsiher | : Unknown |
Total Pages | : 108 |
Release | : 1971 |
Genre | : Airplanes |
ISBN | : UIUC:30112106692574 |
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The aerodynamic characteristics of a full scale executive type jet transport aircraft with a T-tail were investigated in a 40 x 80 ft (12.2 by 24.4 meter) wind tunnel (subsonic). Static, longitudinal, and lateral stability, and control characteristics were determined at angles of attack from -2 deg to 42 deg. The aircraft wing had 13 deg of sweep and an aspect ratio of 5.02. The aircraft was tested power off with various wing leading- and trailing-edge high lift devices. The basic configuration was tested with and without such components as engine nacelles, wing tip tanks, and empannage. Hinge-moment data were obtained and downwash angles in the horizontal-tail plane location were calculated. The data were obtained at Reynolds numbers of 4.1 million and 8.7 million based on mean aerodynamic chord. The model had static longitudinal stability through initial stall. Severe tail buffet occurred near the angle of attack for maximum lift. Above initial stall the aircraft had pronounced pitch-up, characteristic of T-tail configurations. A stable trim point was possible at angles of attack between 30 deg and 40 deg (depending on c.g. location and flap setting). Hinge-moment data showed no regions with adverse effects on stick force. Comparisons of wind-tunnel data and flight-test are presented.