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  • 1990-1994  (3)
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  • 1
    facet.materialart.
    Unknown
    In:  Other Sources
    Publication Date: 2011-08-24
    Description: A comprehensive development history of missile airframe aerodynamics is presented, encompassing ground-, ground vehicle-, ship-, and air-launched categories of all ranges short of strategic. Emphasis is placed on the swift acceleration of missile configuration aerodynamics by German researchers in the course of the Second World War and by U.S. research establishments thereafter, often on the foundations laid by German workers. Examples are given of foundational airframe design criteria established by systematic researches undertaken in the 1950s, regarding L/D ratios, normal force and pitching moment characteristics, minimum drag forebodies and afterbodies, and canard and delta winged configuration aerodynamics.
    Keywords: GENERAL
    Format: text
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  • 2
    Publication Date: 2018-12-01
    Description: The aerodynamic characteristics in the transition from high to low angles of attack at supersonic speeds have been experimentally and theoretically studied for a series of lifting bodies with various upper and lower surface camber designs. The configurations under consideration have a 75-degree swept delta planform with a rounded nose. Data obtained indicate that changes in the camber design cause some distinct changes in the aerodynamic characteristics that shoud be taken into account in the selection of a lifting body shape. The flat bottom designs with upper surface camber are found to provide greater drag for retardation at high angles of attack but are considerably out of trim longitudinally. The flat top designs with lower surface camber provide less drag at high angles of attack but can be more easily trimmed. Calculated results are found to be in good agreement with the experimental data.
    Keywords: AERODYNAMICS
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  • 3
    Publication Date: 2019-07-13
    Description: Experimental and theoretical results are presented for a family of aerodynamic configurations for flight Mach numbers as high as Mach 8. All of these generic configurations involved 70-deg sweep delta planform wings of three different areas and three fuselage shapes with circular-to-elliptical cross sections. It is noted that fuselage ellipticity enhances lift-curve slope and maximum L/D, while decreasing static longitudinal stability (especially with smaller wing areas).
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-4246 , ; 10 p.|AIAA, Aircraft Design Systems Meeting; Aug 24, 1992 - Aug 26, 1992; Hilton Head Island, SC; United States
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