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Accession Number:
AD0102027
Title:
WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC SPEEDS OF JET, SPOILER, AND AILERON CONTROLS ON A 1/16-SCALE MODEL OF THE DOUGLAS D-558-II RESEARCH AIRPLANE
Corporate Author:
NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA
Report Date:
1956-07-27
Abstract:
An investigation was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.60 to 0.96 to determine the characteristics of a wing trailing-edge jet control on a 116-scale model of the Douglas D-558-II research airplane. The control was operated with ram air obtained from wing-tip inlets. The characteristics of ailerons and trailing-edge spoilers were also obtained for comparison with the jet control.
Descriptive Note:
Research memo.
Pages:
0056
Distribution Statement:
Approved for public release; distribution is unlimited.
File Size:
2.85MB
