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


Descriptive Note : Research memo.


Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA


Personal Author(s) : Vogler, Raymond D


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/102027.pdf


Report Date : 27 Jul 1956


Pagination or Media Count : 56


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 1/16-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.


Descriptors :   *AILERONS , *SPOILERS , DEFLECTION , CONTROL SYSTEMS , WIND TUNNELS


Subject Categories : Aircraft


Distribution Statement : APPROVED FOR PUBLIC RELEASE