Supersonic aerodynamic characteristics of delta wings at high angles of attack

Falunin, M. P.; Ul'yanov, G. S.; Makshin, A. A.; Mosin, A. F.

doi:10.1007/bf01029549

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“…3 The Falumin data (C N and x cp ) were obtained using both force balance and pressure measurements. 4 The Baker data (C N , x cp , and y cp ) were obtained from force balance measurements using halfspan wings attached to a reflection plane. 5 The results shown from Nielsen 6 are a tabulation of data that were extracted from existing wind-tunnel data including Refs.…”

Section: Resultsmentioning

confidence: 99%

Wing-Alone Aerodynamic Characteristics at High Angles of Attack

Stallings

Lamb

1982

Journal of Spacecraft and Rockets

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An experimental investigation has been conducted to determine wing-alone supersonic aerodynamic characteristics at high angles of attack. The family of wings tested had aspect ratios of 0.5-4.0 and taper ratios of 0.0-1.0. The wings were tested at angles of attack ranging from -5 to +60 deg and Mach numbers of 1.6-4.6. The aerodynamic characteristics were obtained by integrating local pressures measured over the wing surface. Presented and discussed are results showing the effects of model geometry, Mach number, and angle of attack on aerodynamic characteristics consisting of normal force, pitching moment, bending moment, longitudinal center-of-pressure locations, and lateral center-of-pressure locations. A X Nomenclature--aspect ratio -span = wing half-panel bending moment coefficient, bending moment/ [q(S/2) (b/2)] --pitching moment coefficient, pitching moment/ (qSc) = normal force coefficient, normal force/

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Section: Resultsmentioning

confidence: 99%