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- W633869874 abstract "Report presenting an investigation in the supersonic blowdown tunnel of spoilers on two unswept wing arrangements at Mach numbers of 1.90 and 1.96. The effect of pressure-distribution tests on an unswept airfoil in the presence of a fuselage but without tip effects indicated that spoilers could be oppositely deflected in a manner similar to flap-type ailerons to obtain roll effectiveness without loss in lift. Results regarding force and moment tests are also provided." @default.
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- W633869874 date "1951-01-24" @default.
- W633869874 modified "2023-09-26" @default.
- W633869874 title "Effects of Spoiler on Airfoil Pressure Distribution and Effects of Size and Location of Spoilers on the Aerodynamic Characteristics of a Tapered Unswept Wing of Aspect Ratio 2.5 at a Mach Number of 1.90" @default.
- W633869874 hasPublicationYear "1951" @default.
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