Experimental study of flow field distribution over a generic cranked double delta wing

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• 作者：Mojtaba Dehghan Manshadi ; ^{mdmanshadi@mut-es.ac.ir" class="auth_mail" title="E-mail the corresponding author}Author Vitae ; Mehdi Eilbeigi ; Mohammad Kazem Sobhani ; Mehrdad Bazaz Zadeh ; Mohammad Ali Vaziry
• 关键词：Cranked double delta wing ; Flow field ; Hot wire ; Leading edge shape ; Vortical flow
• 刊名：Chinese Journal of Aeronautics
• 出版年：2016
• 出版时间：October 2016
• 年：2016
• 卷：29
• 期：5
• 页码：1196-1204
• 全文大小：2501 K

文摘

The flow fields over a generic cranked double delta wing were investigated. Pressure and velocity distributions were obtained using a Pitot tube and a hot wire anemometer. Two different leading edge shapes, namely “sharp” and “round”, were applied to the wing. The wing had two sweep angles of 55° and 30°. The experiments were conducted in a closed circuit wind tunnel at velocity 20 m/s and angles of attack of 5°–20° with the step of 5°. The Reynolds number of the model was about 2 × 10⁵ according to the root chord. A dual vortex structure was formed above the wing surface. A pressure drop occurred at the vortex core and the root mean square of the measured velocity increased at the core of the vortices, reflecting the instability of the flow in that region. The magnitude of power spectral density increased strongly in spanwise direction and had the maximum value at the vortex core. By increasing the angle of attack, the pressure drop increased and the vortices became wider; the vortices moved inboard along the wing, and away from the surface; the flow separation was initiated from the outer portion of the wing and developed to its inner part. The vortices of the wing of the sharp leading edge were stronger than those of the round one.