Experimental and Theoretical Studies of Interference Effects on the Damping in Roll of the Bell X-1A Research Airplane at Supersonic Speeds (including Canopy Shape Effects) PDF Download

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Experimental and Theoretical Studies of Interference Effects on the Damping in Roll of the Bell X-1A Research Airplane at Supersonic Speeds (including Canopy Shape Effects)

Experimental and Theoretical Studies of Interference Effects on the Damping in Roll of the Bell X-1A Research Airplane at Supersonic Speeds (including Canopy Shape Effects) PDF Author: Russell W. McDearmon
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 35

Book Description
Component interference studies have been made in an attempt to explain the unexpected large loss in damping in roll which occurred in wind-tunnel tests at zero angle of attack for the Bell X-1A research airplane near a Mach number of 2.22 in the investigation of NACA Research Memorandum LL5I19. The present studies include theoretical calculations of the effect of the body flow field on the wing damping in roll and measurements at test Mach numbers 1.62, 1.94, 2.22, 2.41, and 2.62 of the contributions of the individual components to the damping in roll. In addition, the effects of various modifications to the dorsal and ventral fins are determined experimentally for the complete airplane configuration.

Experimental and Theoretical Studies of Interference Effects on the Damping in Roll of the Bell X-1A Research Airplane at Supersonic Speeds (including Canopy Shape Effects)

Experimental and Theoretical Studies of Interference Effects on the Damping in Roll of the Bell X-1A Research Airplane at Supersonic Speeds (including Canopy Shape Effects) PDF Author: Russell W. McDearmon
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 35

Book Description
Component interference studies have been made in an attempt to explain the unexpected large loss in damping in roll which occurred in wind-tunnel tests at zero angle of attack for the Bell X-1A research airplane near a Mach number of 2.22 in the investigation of NACA Research Memorandum LL5I19. The present studies include theoretical calculations of the effect of the body flow field on the wing damping in roll and measurements at test Mach numbers 1.62, 1.94, 2.22, 2.41, and 2.62 of the contributions of the individual components to the damping in roll. In addition, the effects of various modifications to the dorsal and ventral fins are determined experimentally for the complete airplane configuration.

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