منابع مشابه
Three-dimensional flows around low-aspect-ratio flat-plate wings at low Reynolds numbers
Three-dimensional flows over impulsively translated low-aspect-ratio flat plates are investigated for Reynolds numbers of 300 and 500, with a focus on the unsteady vortex dynamics at post-stall angles of attack. Numerical simulations, validated by an oil tow-tank experiment, are performed to study the influence of aspect ratio, angle of attack and planform geometry on the wake vortices and the ...
متن کاملFlutter Analysis of a Low Aspect Ratio Swept- Back Trapezoidal Wing at Low Subsonic Flow
A linear, aeroelastic analysis of a low aspect ratio swept back trapezoidal wing modeled as a cantilever plate is presented. An analytical and numerical formulation for both the aerodynamic forcing and structural response of the wing was developed. The analytical model uses a three dimensional time domain vortex lattice aerodynamic method. A Rayleigh-Ritz approach has been used to transfer equa...
متن کاملRoll Stall for Low-Aspect-Ratio Wings
The longitudinal aerodynamics of micro aerial vehicles, although not fully understood, have been the subject of several studies in recent years; however, littleworkhasbeendone to investigate the lateral loading. In this experiment, flat-plate wings with rectangular planforms of aspect ratios AR 0.75, 1, 1.5, and 3 and tapered planforms of λ 0.75, 0.5, and 0.25 were placed in the wind tunnel at ...
متن کاملAn Experimental Investigation of the Flowfield over a Low Aspect Ratio Wing
A wind tunnel investigation was performed to study the flow field over a 70° swept sharped edge delta wing model at high angles of attack. The experiments were conducted in the subsonic wind tunnel at the Department of Mechanical Engineering, Sharif University of Technology. Velocity profiles have been measured using a special pitot tube and hot wire anemometer at angles of attacks of 10 to 35 ...
متن کاملAn Experimental Investigation of the Flowfield over a Low Aspect Ratio Wing
A wind tunnel investigation was performed to study the flow field over a 70° swept sharped edge delta wing model at high angles of attack. The experiments were conducted in the subsonic wind tunnel at the Department of Mechanical Engineering, Sharif University of Technology. Velocity profiles have been measured using a special pitot tube and hot wire anemometer at angles of attacks of 10 to 35 ...
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ژورنال
عنوان ژورنال: Journal of Hydronautics
سال: 1975
ISSN: 0022-1716,1555-5909
DOI: 10.2514/3.63010