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Wind-Tunnel Investigation of the Stability of the Jettisonable Nose Section of the X-3 Airplane
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Author and Affiliation:
Scher, Stanley H.(National Advisory Committee for Aeronautics. Langley Aeronautical Lab., Langley Field, VA, United States)
Abstract: Because previous work has indicated that jettisonable nose sections of airplanes may be inherently unstable, and thus may cause dangerous centripetal accelerations on a pilot after jettisoning during high-speed flight, an investigation has been conducted in the Langley 20-foot free-spinning tunnel to determine the behavior in descent of a model of the jettisonable nose section of the Douglas X-3 airplane. The effects of varying the center-of-gravity position, of attaching fins of various sizes, and of installing a stabilizing parachute were investigated. In the investigation the model descended with its front and trimmed 36 deg above the horizontal and rotated about a vertical wind axis while rolling about its longitudinal body axis. The nose section was made to descend in a stable front-down attitude when stabilizing fins were installed in conjunction with movement of the center of gravity forward or when a stable parachute was attached to the model.
Publication Date: Dec 08, 1946
Document ID:
(Acquired Jan 11, 2005)
Subject Category: AERODYNAMICS
Report/Patent Number: NACA-RM-L8K18a
Document Type: Technical Report
Financial Sponsor: National Advisory Committee for Aeronautics; Washington, DC, United States
Organization Source: National Advisory Committee for Aeronautics. Langley Aeronautical Lab.; Langley Field, VA, United States
Description: 19p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
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