Journal of Aeronautical Engineering

Journal of Aeronautical Engineering

Experimental investigation of the effects of secondary flow injection on the output flow of the convergent-divergent nozzle at different beveled angles

Document Type : Original Article

Authors
Mohammad Hojaji 1
Seyed Mohammad Hossein Razavi Dehkordi 1
Sayed Ali Hosseini 2
Mostafa Pourmohammadi 2
mohsen norouzi 2
1 Assistant Professor, Department of Engineering, Najafabad Branch, Islamic Azad University, Najafabad, Iran
2 Aerospace and Energy Conversion Research Center, Najafabad Branch, Islamic Azad University, Najafabad, Iran
10.22034/joae.2022.316243.1072
Abstract
In this study, due to the importance of controlling the thrust vector of beveled nozzles, the effects of secondary injection on the output flow deviation from the convergent-divergent beveled nozzle have been investigated experimentally. For this purpose, three beveled nozzles with beveled angles of 25, 45, and 65 degrees have been used. Also, to control the direction of the output flow from the nozzle, a convergent injector has been installed to discharge the secondary flow perpendicular to the center direction of the nozzle at 0.8 divergent nozzle length. The main parameters studied in this research are the effects of changing the stagnation pressure of the main nozzle and the secondary flow and changing the beveled nozzle angle. The output flow deviation from the nozzle in different conditions is extracted from the shadowgraph images, and the results are presented. The results show that the performance of beveled nozzles with a low beveled angle with secondary injection is very good and the flow control in beveled nozzles up to 45֠ angle is much more favorable than high beveled angle nozzles. As the beveled angle increases, the nozzle performance decreases Strongly, So that the rate of reduction of flow deflection in 45֠ beveled nozzle compared to the 25֠, was close to 3%. While this deflection in the 65֠ beveled nozzle is reduced to 83%.
Keywords
convergent-divergent Beveled Nozzle
Thrust Vector Control (TVC)
Secondary Flow Injection
Rocket Engine
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Journal of Aeronautical Engineering
Volume 24, Issue 1
April 2022
Pages 45-56

  • Receive Date 22 November 2021
  • Revise Date 05 January 2022
  • Accept Date 10 May 2022