Investigation of the Flowfield At Sonic and Supersonic Mach Numbers with Sudden Expansion
Ambareen Khan1, Nurul Musfirah Mazlan2, Mohd Azmi Ismail3
1Ambareen. Khan, School of Aerospace Engineering, Engineering Campus, University Sains Malaysia, Nibong Tebal, Penang, Malaysia.
2Nurul Musfirah. Mazlan, School of Aerospace Engineering, Engineering Campus, University Sains Malaysia, Nibong Tebal, Penang, Malaysia.
3Mohd Azmi. Ismail, School of Mechanical Engineering, Engineering Campus, University Sains Malaysia, Nibong Tebal, Penang, Malaysia.
Manuscript received on 05 April 2019 | Revised Manuscript received on 14 April 2019 | Manuscript Published on 24 May 2019 | PP: 91-95 | Volume-8 Issue-6S3 April 2019 | Retrieval Number: F10160486S319/19©BEIESP
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open-access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: This paper presents the results of an experimental investigation conducted at sonic and supersonic Mach number. The objective of the study was to measure the base pressure, the flow development in the suddenly expanded duct, and the pressure loss at the two points in the flow network (i.e., from settling chamber to the exit of the duct). Experiments were conducted for converging and converging-diverging nozzle at Mach 1 and 1.2. The area ratio of the study is 7.84 for a fixed L/D ratio of 8. The results indicate that there is a continuous decrease in the base pressure despite jet being highly underexpanded the base pressure continue to decrease due to the large area ratio. The pressure loss is 30 % for lower Mach number, but it is around 80 % at NPR 7. The wall pressure assumes the lowest values for NPR 7 and the highest values at NPR 1.5.
Keywords: Presents the Results of an Experimental Investigation Conducted at Sonic and Supersonic Mach Number.
Scope of the Article: Aerospace Engineering