Theoretical and Experimental Investigation of Biplane Delta Wings
Theoretical and Experimental Investigation of Biplane Delta Wings
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DOI：
10.2514/2.2794
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发表时间：
2001-05
影响因子：
2.2
通讯作者：
L. Traub
中科院分区：
文献类型：
--
作者：
L. Traub
最近对微型飞行器的兴趣导致了对创新空气动力锥体和推进机构的评估，以满足这些机器的要求。有人提出，使用三角翼的双翼飞机可能被证明是一种有效的锥体结构。因此，进行了理论和实验研究，以确定双翼锥体结构中三角翼的特性。风洞研究是使用 75 度三角翼进行的。双翼机翼的间隙（分离）和交错是不同的。开发了一种理论方法，将普朗特的双平面理论（Prandtl, L., and Tietjens, O. G., Applied Hydro and Aeromechanics, Dover, New York, 1934, pp. 211 ‐222）与 Polhamus 的前沿吸力类比（Polhamus, E. C., “Prediction of Vortex-Lift Characteristics by aleading-Edge Suction” 相结合）类比，”《飞机杂志》，第 8 卷，第 4 期，1971 年，第 193 ‐199 页）。实验结果表明，机翼间距对升力有显着的倾斜影响，机翼距离越近，升力越小。双平面锥体结构对交错的敏感性要低得多，仅在攻角大于 15 度时才会出现效果。相对于非交错锥体结构，正交错（上翼向前）增加升力，而负交错减少升力。类似地，正交错增加了最大记录升力系数，而负交错则具有相反的效果。理论方法与实验数据吻合较好，正确预测了间隙和错位对升力的影响。理论分析表明，对于尺寸受限的平面形状，三角翼双翼飞机是中到大机翼分离的有效锥体结构。
Recent interest in micro aerial vehicles has resulted in the evaluation of innovative aerodynamic cone gurations and propulsive mechanisms to meettherequirements ofthesemachines. It is proposed that a biplaneformed using delta wings may proveto be an efe cient cone guration. Accordingly, a theoretical and experimental investigation to determine thecharacteristicsof delta wings in a biplanecone guration wasundertaken. Thewind-tunnel study was performed using 75-deg delta wings. The biplane wing’ s gap (separation) and stagger were varied. A theoretical method was developed that coupled Prandtl’ s biplane theory (Prandtl, L., and Tietjens, O. G., Applied Hydro and Aeromechanics , Dover, New York, 1934, pp. 211 ‐222) with Polhamus’ leading-edge suction analogy (Polhamus, E. C., “ Prediction of Vortex-Lift Characteristics by a Leading-Edge Suction Analogy,”Journal of Aircraft , Vol. 8, No. 4, 1971, pp. 193 ‐199). The experimental results showed that the separation between the wings has a signie cant effect on lift, the lift reducing with closer wing proximity. The biplane cone guration shows far less sensitivity to stagger, with effects only manifesting for angles of attack greater than 15 deg. Positive stagger (upper wing forward)increased lift whereas negative stagger decreased lift relative to an unstaggered cone guration. Similarly, positive stagger increased the maximum recorded lift coefe cient with negative stagger having the opposite effect. The theoretical method showed close accord with the experimental data and correctly predicted the effect of gap and stagger on lift. Theoretical analysis showed that for a dimensionally constrained planform, the delta wing biplane is an effective cone guration for moderate to large wing separation.