Computational Study of Fluidic Thrust Vectoring using Separation Control in a Nozzle
Computational Study of Fluidic Thrust Vectoring using Separation Control in a Nozzle
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DOI：
10.2514/6.2003-3803
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发表时间：
2003
期刊：
影响因子：
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通讯作者：
K. Deere;B. Berrier;J. Flamm;Stuart K. Johnson
中科院分区：
文献类型：
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作者：
K. Deere;B. Berrier;J. Flamm;Stuart K. Johnson
对二维喷嘴进行了计算研究，以评估流体喷射对控制流动分离和引起主射流推力矢量的影响。该喷嘴采用凹腔设计，增强了流体推力矢量的换喉方法。采用结构网格计算流体力学代码PAB3D对60多种构型进行了设计和分析。喷嘴设计变量包括空腔收敛角、空腔长度、射流注入角、上游最小高度、尾甲板角和尾甲板形状。所有模拟均在静态自由流马赫数为0.05，喷嘴压力比为3.858，流体喷射流量为一次流量的6%的条件下进行计算。结果表明，凹腔增强了流体推力矢量的换喉方法，在不影响推力效率的情况下允许更大的推力矢量角。
A computational investigation of a two- dimensional nozzle was completed to assess the use of fluidic injection to manipulate flow separation and cause thrust vectoring of the primary jet thrust. The nozzle was designed with a recessed cavity to enhance the throat shifting method of fluidic thrust vectoring. The structured-grid, computational fluid dynamics code PAB3D was used to guide the design and analyze over 60 configurations. Nozzle design variables included cavity convergence angle, cavity length, fluidic injection angle, upstream minimum height, aft deck angle, and aft deck shape. All simulations were computed with a static freestream Mach number of 0.05, a nozzle pressure ratio of 3.858, and a fluidic injection flow rate equal to 6 percent of the primary flow rate. Results indicate that the recessed cavity enhances the throat shifting method of fluidic thrust vectoring and allows for greater thrust-vector angles without compromising thrust efficiency.