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Design Guide for Pitch-Up Evaluation and Investigation at High Subsonic Speeds of Possible Limitations Due to Wing-Aspect-Ratio VariationsA design guide is suggested as a basis for indicating combinations of airplane design variables for which the possibilities of pitch-up are minimized for tail-behind-wing and tailless airplane configurations. The guide specifies wing plan forms that would be expected to show increased tail-off stability with increasing lift and plan forms that show decreased tail-off stability with increasing lift. Boundaries indicating tail-behind-wing positions that should be considered along with given tail-off characteristics also are suggested. An investigation of one possible limitation of the guide with respect to the effects of wing-aspect-ratio variations on the contribution to stability of a high tail has been made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.60 to 0.92. The measured pitching-moment characteristics were found to be consistent with those of the design guide through the lift range for aspect ratios from 3.0 to 2.0. However, a configuration with an aspect ratio of 1.55 failed t o provide the predicted pitch-up warning characterized by sharply increasing stability at the high lifts following the initial stall before pitching up. Thus, it appears that the design guide presented herein might not be applicable when the wing aspect ratios lower than about 2.0.
Document ID
19630003100
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Spreemann, Kenneth P. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 1, 2013
Publication Date
August 1, 1959
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-26
Accession Number
63N12976
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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