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Effect of nozzle lateral spacing on afterbody drag and performance of twin-jet afterbody models with convergent nozzles at Mach numbers up to 2.2

机译：喷嘴侧向间距对后拖动效应的影响及双喷射后体模型的收敛喷嘴马赫数为2.2

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摘要

Nozzle lateral spacing effect on drag and performance of twin jet afterbody configurations with convergent nozzles at Mach 0.6 to 2.2

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作者
Maiden, D. L.; Runckel, J. F.;
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年度 1970
页码 1-142
总页数 142
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
AERODYNAMIC DRAG; AFTERBODIES; CONVERGENT NOZZLES; JET NOZZLES; NOZZLE GEOMETRY; AIRCRAFT MODELS; NOZZLE EFFICIENCY; WIND TUNNEL STABILITY TESTS;

机译：空气动力学; aFTERBODIEs; CONVERGENT NOZZLEs; JET NOZZLEs;喷嘴几何;飞机模型;喷嘴效率;风洞稳定性试验;

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1. THREE-DIMENSIONAL AFTERBODY DRAG WITH NOZZLE JET [J] . G.N. Lavrukhin, V.A. Talyzin TsAGI science journal . 2017,第8期

机译：带喷嘴射流的三维人体后遗症
2. Inverse Design Method on Scramjet Nozzle with Full Geometrical Constraints for Nozzle-Afterbody Integration [J] . Yu Kaikai, Chen Yile, Huang Shuai, Journal of aerospace engineering . 2021,第3期

机译：对瘙痒喷嘴的逆设计方法，具有用于喷嘴后的全几何约束
3. Density field of supersonic separated flow past an afterbody nozzle using tomographic reconstruction of BOS data [J] . L. Venkatakrishnan, P. Suriyanarayanan Experiments in Fluids . 2009,第3期

机译：使用BOS数据的层析成像重建通过后喷嘴的超声速分离流的密度场
4. Experimental and Numerical Analysis of a Two-Duct Nozzle/Afterbody Model at Supersonic Mach Numbers [C] . T.Berens AIAA international aerospace planes and hypersonics technologies conference . 1995

机译：超声波马赫数的双管喷嘴/后体模型的实验性和数值分析
5. The effect of exhaust plume/afterbody interaction on installed scramjet performance. [D] . Edwards, Thomas Alan. 1988

机译：排气羽流/车身后部相互作用对安装的超燃冲压发动机性能的影响。
6. Simple convergent-nozzle aerosol injector for single-particle diffractive imaging with X-ray free-electron lasers [O] . R. A. Kirian, S. Awel, N. Eckerskorn, 2015

机译：用于X射线自由电子激光的单粒子衍射成像的简单会聚喷嘴气溶胶注射器
7. Estimation of afterbody drag with jet temperature effects for the afterbody-nozzle configuration of a combat aircraft [O] . Mathur NB 1999

机译：战斗机后喷嘴结构对射流温度影响的后阻力的估计
8. Effect of Nozzle Lateral Spacing on Afterbody Drag and Performance of Twin-Jet Afterbody Models with Convergent-Divergent Nozzles at Mach Numbers Up to 2.2 [R] . Pendergraft, O. C., Schmeer, J. W. 1972

机译：喷嘴横向间距对后体阻力的影响及具有收敛 - 发散喷嘴的双射流后体模型在马赫数2.2下的性能

Effect of nozzle lateral spacing on afterbody drag and performance of twin-jet afterbody models with convergent nozzles at Mach numbers up to 2.2

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