Results Of Full Scale Wind Tunnel Tests On The H 126 Jet Flap Aircraft
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Results of Full scale Wind Tunnel Tests on the H 126 Jet Flap Aircraft
Author | : Anthony M. Cook,Dale G. Jones |
Publsiher | : Unknown |
Total Pages | : 66 |
Release | : 1969 |
Genre | : Jet flaps (Airplanes) |
ISBN | : UIUC:30112106595819 |
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Low Speed Wind Tunnel Tests on a One seventh Scale Model of the H 126 Jet Flap Aircraft
Author | : Anonim |
Publsiher | : Unknown |
Total Pages | : 94 |
Release | : 1975 |
Genre | : Electronic Book |
ISBN | : NASA:31769000531106 |
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NASA Technical Note
Author | : Anonim |
Publsiher | : Unknown |
Total Pages | : 410 |
Release | : 1973 |
Genre | : Electronic Book |
ISBN | : MINN:319510008464540 |
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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.
Technical Information Indexes
Author | : Anonim |
Publsiher | : Unknown |
Total Pages | : 126 |
Release | : 1975 |
Genre | : Aeronautics, Military |
ISBN | : UIUC:30112104133027 |
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T I S C A Technical Information Indexes
Author | : United States. Naval Air Systems Command |
Publsiher | : Unknown |
Total Pages | : 122 |
Release | : 1975 |
Genre | : Aeronautics, Military |
ISBN | : CORNELL:31924071765667 |
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Scientific and Technical Aerospace Reports
Author | : Anonim |
Publsiher | : Unknown |
Total Pages | : 952 |
Release | : 1987 |
Genre | : Aeronautics |
ISBN | : UIUC:30112075701505 |
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NASA s Contributions to Aeronautics Flight environment operations flight testing and research
Author | : Anonim |
Publsiher | : Unknown |
Total Pages | : 1064 |
Release | : 2010 |
Genre | : Aeronautics |
ISBN | : UCSD:31822036341212 |
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Two-volume collection of case studies on aspects of NACA-NASA research by noted engineers, airmen, historians, museum curators, journalists, and independent scholars. Explores various aspects of how NACA-NASA research took aeronautics from the subsonic to the hypersonic era.-publisher description.