| 低速风洞半模实验壁压法洞壁干扰修正 |
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| 引用本文： | 张文华. 低速风洞半模实验壁压法洞壁干扰修正[J]. 航空学报, 1990, 11(4): 188-191 |
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| 作者姓名： | 张文华 |
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| 作者单位： | 南京航空学院 |
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| 摘 要： | <正> 1.前言 低速风洞半模实验有许多优点,但伴随而来的是洞壁干扰修正问题。大迎角、大堵塞度情况洞壁干扰修正值相当大。如某后掠大展弦比机翼半模,迎角90°时堵塞度达18％,阻力系数洞壁干扰修正值可达真实值的70％。又如某农机机翼半模,迎角40°时堵塞度达8％。压力系数洞壁干扰修正值达真实值的30％。因此,在进行半模实验时,洞壁干扰修正的准确性十分重要。
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| 收稿时间： | 1988-02-16; |
A WALL PRESSURE CORRECTION METHOD FOR HALF-MODEL EXPERIMENT IN CLOSED SUBSONIC WIND TUNNEL TEST SECTION |
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| Nanjing Aeronautical Institute Zhang Wenhua. A WALL PRESSURE CORRECTION METHOD FOR HALF-MODEL EXPERIMENT IN CLOSED SUBSONIC WIND TUNNEL TEST SECTION[J]. Acta Aeronautica et Astronautica Sinica, 1990, 11(4): 188-191 |
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| Authors: | Nanjing Aeronautical Institute Zhang Wenhua |
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| Affiliation: | Nanjing Aeronautical Institute Zhang Wenhua |
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| Abstract: | A wall pressure correction method for half-model experiment in closed subsonic wind tunnel test section is presented. Not only forces but also pressure distributions on the model are correctedo Experimental examinations of the method give good results on high angles of attack, aa well as large blockings. The method provided by this paper is applicable for practical purpose. |
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| Keywords: | low speed wind tunnel wall interference correction wind tunnel experimental technique. |
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