wing-body configuration中文是什么意思

• 机翼机身组合型
• 翼身结构

• "wing"中文翻译    n. 1.翼，翅膀；鸟；鸟群；飞行，飞翔。 2.(飞机) ...
• "body"中文翻译    n. 1.身体，体躯，肉体；尸首；躯干，【林业】立木。 ...
• "configuration"中文翻译    n. 1.结构；构造；圆形，外形。 2.组合，布置；配置 ...
• "tin-wing-body configuration" 中文翻译 :    薄翼细身组合型
• "wing configuration" 中文翻译 :    机翼构造; 机翼形状
• "fan-in-wing configuration" 中文翻译 :    机身内风扇式布局
• "forward-swept-wing configuration" 中文翻译 :    前掠翼布局
• "high-wing configuration" 中文翻译 :    上单翼布局
• "high-wing-loading configuration" 中文翻译 :    大翼载布局
• "low-wing configuration" 中文翻译 :    下单翼布局
• "radial wing configuration" 中文翻译 :    辐射翼外形
• "shoulder wing configuration" 中文翻译 :    上单翼布局
• "slender-wing configuration" 中文翻译 :    狭长翼布局
• "tilt-wing configuration" 中文翻译 :    偏转翼布局
• "wedge-wing configuration" 中文翻译 :    楔形翼布局
• "wing-cone configuration" 中文翻译 :    机翼锥体组合型
• "yawed wing configuration" 中文翻译 :    箭形翼布局
• "all-body configuration" 中文翻译 :    无翼型
• "delta-wing-half-cone configuration" 中文翻译 :    三角半锥体组合型
• "double fuselage yawed wing configuration" 中文翻译 :    双机身箭形翼布局
• "single fuselage yawed wing configuration" 中文翻译 :    单机身箭形翼局
• "blended wing body" 中文翻译 :    翼身融合
• "body effect on wing" 中文翻译 :    机身对机翼的影响
• "body in region of wing" 中文翻译 :    机翼区机身
• "body-wing interaction" 中文翻译 :    机翼机身干扰

• The viscous flow around m6 wing and f4 wing - body configuration are simulated and compared with the results of wind tunnel experiment
  为了验证方法和程序的正确性，论文中对m6机翼和f4翼身组合体的流场进行了数值模拟，并与试验结果进行了对比。
• In the dissertation , the unstructured dynamic mesh technique is investigated . full implicit dual - time temporal derivatives and cell - center finite volume method spatial derivatives are adopted to simulate unsteady flow fields of 2 - d airfoil , 3 - d wing and wing - body configuration
  在非结构运动网格技术方面，本文发展了一种适用于解决非定常气动力计算的、高效的、鲁棒性较好的非结构运动网格方法。
• Taking m6 wing and f4 wing - body configuration as computational examples , some results by solving euler and n - s equations are presented . compared with the results of wind tunnel experiment , the results of n - s solver are much better than those of euler solver , and the upwind scheme is better than the central scheme in catching shock wave
  本文以m6机翼和f4翼身组合体为算例，对euler方程和n - s方程的计算结果进行了比较，从算例上可以看出， n - s方程的计算结果更接近实验值；对中心差分格式和迎风格式的比较，可以看出，在激波的捕捉方面，迎风格式比中心差分格式更精确。
• Many test cases are calculated to verify the above study . the cases are either real or standard testing models , including multi - element airfoil , wing - body configuration , cone / cylinder missile model and 3 - d high - lift systems , etc . the results of present calculation are in good agreement with experiment data , and show flexibility and accuracy of the approaches . base on the cartesian grids , this thesis has targeted the development and integration of many algorithms and techniques such as adaptive refinement , omni - tree data structure , hybrid grid method , etc . an analysis software and research methods are designed and developed for the steady - unsteady and viscous - inviscid flow complex systems and configuration
  7 .运用上述研究成果和结论，进行了大量算例的实验验证，外形范围包括多种标模与型号，涉及多段翼型、 m6机翼、细长体模型、翼身组合体、两段机翼增升标模、带缝翼和襟翼的三段增升翼身组合体等复杂外形，计算结果均与实验吻合良好，充分说明了本文发展的各种算法、流场求解、网格生成方法的正确性和鲁棒性。