Static Longitudinal Aerodynamic Characteristics at Transonic Speeds and Angles of Attack Up to 99° of a Reentry Glider Having Folding Wing-tip Panels
Author: Walter B. Olstad
Publisher:
Published: 1961
Total Pages: 36
ISBN-13:
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Author: Walter B. Olstad
Publisher:
Published: 1961
Total Pages: 36
ISBN-13:
DOWNLOAD EBOOKAuthor: Walter B. Olstad
Publisher:
Published: 1961
Total Pages: 31
ISBN-13:
DOWNLOAD EBOOKAuthor:
Publisher:
Published: 1961
Total Pages: 36
ISBN-13:
DOWNLOAD EBOOKAuthor: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Publisher:
Published: 1968
Total Pages: 436
ISBN-13:
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Publisher:
Published: 1967
Total Pages: 670
ISBN-13:
DOWNLOAD EBOOKLists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher:
Published: 1968
Total Pages: 448
ISBN-13:
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Published: 1961
Total Pages: 40
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DOWNLOAD EBOOKAuthor: Kenneth W. Goodson
Publisher:
Published: 1961
Total Pages: 64
ISBN-13:
DOWNLOAD EBOOKAn investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The basic aspect-ratio-4.00 wing had a zero taper and an unswept 0.80 chord line. Several aspect-ratio modifications to the basic wing were made by clipping off portions of the wing tips. The complete model was tested with a chord-plane tail, a T-tail, and a biplane tail (combined T-tail and chord-plane tail). The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92. The data show that, when reduced to the same static margin, all the tail configurations tested on the model provided fairly good stability characteristics, the biplane tail giving the best overall characteristics as regards pitching-moment linearity. Changes in static margin at zero lift coefficient with Mach number were small for the model with these tails over the Mach number range investigated.
Author: Walter B. Olstad
Publisher:
Published: 1961
Total Pages: 34
ISBN-13:
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