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Browsing Aeronautical Research Council Current Papers by Author "T. A. Cook"

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Supersonic wind tunnel tests on a 1/12th scale model of the bristol type 188 research aircraft part 1 M = 1.4 to 2.0 part 2 M = 2.0 to 2.7

C. R. Taylor; T. A. Cook (1965)
Wind tunnel measurements at mach numbers up to 2.80 of the effects of gulling on the longitudinal and lateral stability and drag of a cambered, slender ogee wing

T. A. Cook (1965)
Wind tunnel measurements of the far-field pressures due to some lifting, slender delta wings

T. A. Cook (1965)
Wind tunnel tests at mach numbers up to 2.80 to determine the effects of changing spanwise volume distribution on a slender, cambered ogee wing

T. A. Cook (1965)
Wind tunnel tests on a 1/12th scale model of the bristol type 188 research aircraft with rectangular, wedge intakes at mach numbers from 2.0 to 2.7

T. A. Cook (1965)

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