F-105F Transonic Buffet Study and Effect of Maneuvering Flaps
Report Number: AFFDL TR 69-37
Author(s): Margolin, Milton, Chung, Jung G.
Corporate Author(s): Fairchild Hiller Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1969-07
Pages: 232
Contract: F33657-68-C-1057
DoD Project: None Given
Identifier: AD0693650
Abstract:
A flight test investigation was made using a Republic F-105F aircraft to obtain data related to high subsonic-transonic buffet and the effects of utilizing a maneuvering flap. Flight tests were made at nominal altitudes of 25,000 feet and 35,00 feet. At each altitude, data was collected at three Mach numbers from level flight to maximum usable lift. A related investigation was made using a 1/22-scale model of the F-105F aircraft in the NASA Langley High-Speed Wind Tunnel. The wind tunnel tests were made at three Mach numbers (0.80, 0.85 and 0.90) and data was obtained from zero angle-of-attack to the strain gage balance limits. Flight test results compare readily to wind tunnel data. The boundary layer profiles between flight test and wind tunnel are quite similar. The angles of attack at buffet onset are also comparable. Selection of the leading edge flap and trailing edge flap deflection may be made on the basis of the greatest normal force coefficient at buffet onset, but the final criterion will be level of buffet intensity apparent to the pilot. This level may be varied with the leading edge flap deflection.
Provenance: AFRL/VACA
Author(s): Margolin, Milton, Chung, Jung G.
Corporate Author(s): Fairchild Hiller Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1969-07
Pages: 232
Contract: F33657-68-C-1057
DoD Project: None Given
Identifier: AD0693650
Abstract:
A flight test investigation was made using a Republic F-105F aircraft to obtain data related to high subsonic-transonic buffet and the effects of utilizing a maneuvering flap. Flight tests were made at nominal altitudes of 25,000 feet and 35,00 feet. At each altitude, data was collected at three Mach numbers from level flight to maximum usable lift. A related investigation was made using a 1/22-scale model of the F-105F aircraft in the NASA Langley High-Speed Wind Tunnel. The wind tunnel tests were made at three Mach numbers (0.80, 0.85 and 0.90) and data was obtained from zero angle-of-attack to the strain gage balance limits. Flight test results compare readily to wind tunnel data. The boundary layer profiles between flight test and wind tunnel are quite similar. The angles of attack at buffet onset are also comparable. Selection of the leading edge flap and trailing edge flap deflection may be made on the basis of the greatest normal force coefficient at buffet onset, but the final criterion will be level of buffet intensity apparent to the pilot. This level may be varied with the leading edge flap deflection.
Provenance: AFRL/VACA