低速風洞模型阻塞效應氣動力數據修正方法之研究

Investigation of Aerodynamic Data Correction Methods for Model Blockage Effects in Low Speed Wind Tunnel Test

劉益仲(Liu, Y. C.) ； 歐陽駿塏(Ouyang, J. K.) ； 周宏彥(Chou, H. Y.)

《航空安全及管理季刊》 4卷4期 (2017/10) Pp. 300-320

摘要

本篇研究針對本院現有低速風洞儀電量測裝備，進行模型阻塞效應氣動力試驗數據分析，探討模型尺度與高攻角量測姿態下，模型阻塞對風洞六分量氣動力量測數據之影響，藉以驗證程式架構於數據修正上，是否滿足量測數據擷取需求。本量測以穩態穩流之實驗條件為主，力與力矩則用MK.28嵌入式六分量平衡儀進行量測，測力模型部分選用NASA TP-1803標準模型，而數據解析部分則以基本氣動力係數重複性誤差分析及阻塞效應修正兩部分為主，為搭配現有支撐之液油壓系統，本次使用之標準模型以幾何相似放大1.6倍進行設計搭配及製作。由試驗結果可發現，六分量試驗數據量測誤差皆在預期範圍之內，而模型阻塞效應修正之氣動力參數與文獻結果比對吻合，然受限於不同模型之氣動力特性及取樣攻角多寡等因素，現有儀電僅能針對失速前及升力斜率線性區間，提供合理之修正，然失速後或升力斜率非線性之數據，仍需進一步進行界定及修正，因此，試驗量測之升力線性與非線性區間之確立，取決於攻角擷取點之疏密程度，若取樣過少，則升力非線性區間較容易失真而影響後續阻塞效應修正之結果，本研究將可提供完善的試驗數據供後續低速風洞阻塞效應修正實驗參酌。

關鍵字

阻塞效應 ； 攻角 ； 幾何相似 ； 升力斜率

並列摘要

This paper study the model blockage effect of aerodynamic data analysis using low speed wind tunnel instrumentation in NCSIST. To study the effect of model scale and measured attitude at high angle of attack on the accuracy of the aerodynamic data, data corrected methods for model blockage effect are used and analyzed in the present studies. The experimental flow condition is steady state and the aerodynamic data are measured by MK. 28 internal strain gage balances, and the NASA TP-1803 standard test model is used in experiment. The data analysis include data uncertainty analysis and blockage effect corrected methods. In order to satisfy the size of MK.28 strain gage balances and hydraulic model support system in low speed wind tunnel, the test model is geometrically scaled up 1.6 times of a standard model. The experimental results show that the preliminary aerodynamic parameters of data uncertainty analysis are met as expected, and the data analyzed with model blockage correction methods are consistent with those of the literature results. However, the present instrumentation can only provide good blockage correction data in linear slope of lift curve. Therefore, the data sampling rate will influence the linear region of experimental results and influence the accuracy of blockage corrected methods. There are still more of the data blockage correction in the nonlinear region and stall condition to be studied. This study can well served as reference technical document for data blockage corrected methods and the related experiment in low speed wind tunnel test.

並列關鍵字

Blockage Effect ； Angle of Attack ； Geometry Similarity ； Slope of Lift Curve

參考文獻

鍾武錕、何志遠、臧瑞傳()。,未出版。

Huang, C.Y.,Matsuda, Y.,Gregory, J.,Nagai, H.,Asai, K.(2015).The Applications of Pressure-Sensitive Paint in Microfluidic Systems.Microfluidicsand Nanofluidics.18,739-753.

Maskell, E. C.(1963).A Theory of the Blockage Effects on Bluff Bodies and Stalled Wings in a Closed Wing Tunnel.

Hsiao, F. B.,Liu, Y. C.(2012).Aerodynamic Investigations of Low-Aspect-Ratio Thin Plate Wings at Low Reynolds Numbers.Journal of Mechanics.8(1),77-89.

Luckring, J. M.(1979).Subsonic Longitudinal and Lateral Aerodynamic Characteristics for a systematic Series of Strake-Wing Configurations.,未出版.