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表面粗糙度對NACA 0015機翼表面壓力特性之影響分析
The Effects of Surface Roughness on the Characteristics of Surface Pressure of NACA 0015 Airfoil
摘要
本研究主要以實驗方法探討二維對稱機翼模型(NACA 0015)表面因噴砂所造成表面粗糙度改變對機翼上下表面壓力變化之影響。實驗於低速開放式風洞中進行，自由流速所對應之雷諾數範圍?3.8×10^4~1.5×10^5，實驗之參數?攻角、雷諾數、噴砂號數及噴砂寬度。本文之目的?探討在不同實驗參數下對機翼表面壓力變化分佈及翼面受力之影響情形，進而瞭解不同噴砂參數對機翼表面壓力動力行?之關係。本文實驗結果顯示機翼表面壓力之變化隨著不同實驗參數而有不同的分佈型態。當流場在低雷諾數下，噴砂效應對機翼表面流場的影響並不明顯；當流場在較高雷諾數時，噴砂效應對機翼表面流場則有較顯著的影響。噴砂寬度與機翼上下表面壓力分佈之壓升動力行?並不具備正比關係，機翼表面之壓升動力行?並未如預期在噴砂寬度w=3mm達到最大，反而在噴砂寬度2 mm時有較大值。
並列摘要
The present study is intended to investigate the surface pressure of NACA 0015 airfoil at upper and lower surface due to the surface roughness. The experiment is proceeded in an low-speed wind tunnel. The dynamic behaviors of surface pressure of NACA 0015 airfoil were analyzed at various angles of attack, Reynolds number, number of sandblast, and width of sandblast. The free stream velocity is operated at 5~20 m/s and the corresponding Reynolds number at 3.8×10^4~1.5×10^5 which is based on the chord of the wing. The purpose of this study is intended to understand the relation between surface pressure of the airfoil and relevant sandblast parameters.