A.R.L.低速風洞模型尾流阻塞修正量之探討

The Investigations of Model Wake Blockage Corrections in A.R.L. Low Speed Wind Tunnel

莊書豪(Shu-Hao Chuang) ； 陳登發(Deng-Fa Chen)

《中國航空太空學會學刊》 27卷1期 (1995/03) Pp. 13-22

https://doi.org/10.6124/TAASRC.199503_27(1).02

摘要

本試驗利用中山科學研究院航空研究所A.R.L.之7呎×10呎低速風洞進行，以一個1.6倍NASA TP 1803風洞模型中之機身加上機翼加上垂直尾翼及輔助翼(Strake-wing) (AD17)所組成模型及三個75°後掠角三角翼測力模型，分別使用阻力分析法和風洞壁面壓力分析法求得模型之尾流阻塞因子(BF(下標 b))修正式。並配合附著流之既有理論公式，獲得一涵蓋整個攻角範圍之完整阻塞因子修正，使風洞試驗更接近自由流飛行的模擬。雖然使用不同模型所求得的模型尾流阻塞因子修正式並不相同，但是在試驗值以內，彼此間差異在合理誤差範圍內，所以可合併得一綜合修正式。以此修正式對1.6倍NASA TP 1803風洞模型試驗數據做修正，發現與A.R.L.以前所吹試的數據在高攻角處亦相當接近。

關鍵字

阻力分析法 ； 壁壓力分析法 ； 尾流阻塞因子修正

並列摘要

This paper is to explore the model blockage corrections using the experimental results carried out in the A.R.L. 7'×10' low speed wind tunnel. The 1.6 times NASA TP 1803 and a 75° of sweep delta wing model arc measured experimentally by employing the drag-analysis method and wall-pressure-analysis method for finding their wake blockage corrections and for fitting the existing theoretical equations concerning the attached flow for a complete blockage corrections prevailing in all extent of the angle of attack. Though, the wake blockage corrections associated with the various models are not exactly same, the difference is reasonable between them in the testing data. In addition, the lift coefficient performed by the present results is closed with the previous experimental data of A.R.L.

並列關鍵字

dray-analysis method ； wall-pressure-analysis method ； wake btockage correction