Tab Aspect Ratio Effect on Supersonic Jet Mixing
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Mrinal Kaushik
und
E. Rathakrishnan
Abstract
The efficacy of introducing mixing promoting small-scale vortices by two rectangular tabs, of aspect ratio 1.0, 1.5 and 2.0, placed at diametrically opposite locations at the exit of a Mach 1.73 convergent–divergent circular nozzle has been experimentally investigated, for NPRs from 4 to 8, covering overexpanded, correctly expanded and underexpanded states of the jet. The area blockage due to the each tab was 2.5% of the nozzle exit area. Keeping the blockage constant, the aspect ratio (defined as the ratio of length to width of the tab) was varied. A maximum core length reduction of 84.6% was caused by the tabs of aspect ratio 1.0, at underexpanded conditions corresponding to NPR (nozzle pressure ratio) 6. At this NPR, tabs of aspect ratio 1.5 and 2.0 caused core length reduction of 76.9% and 61.5%, respectively. The mixing promoting efficiency of aspect ratio 1.0 is found to be better than 1.5 and 2.0, at all NPRs of the present study, except NPR 5. The shadowgraph pictures of the uncontrolled and controlled jets clearly demonstrate the effectiveness of the tabs in weakening the waves in the jet core.
References
1. BradburyLJ, KhademAH. The distortion of a jet by tabs. J Fluid Mech1975;70:801–13.10.1017/S0022112075002352Suche in Google Scholar
2. AhujaKK, BrownWH. Shear flow control by mechanical tabs. AIAA–1989–994.10.2514/6.1989-994Suche in Google Scholar
3. ZamanKB. Stream wise vorticity generation and mixing enhancement in free jets by delta-tabs. AIAA–1993–3253.10.2514/6.1993-3253Suche in Google Scholar
4. BohlD, FossJF. Enhancement of passive mixing tabs by the addition of secondary tabs. AIAA–1996–54.10.2514/6.1996-545Suche in Google Scholar
5. Wishart, DP, Krothapalli, A, and Mungal, MG. Supersonic jet control disturbances inside the nozzle. AIAA J1993;31(7):1340–1.10.2514/3.11773Suche in Google Scholar
6. Zaman, KBMQ, Reeder, MF, and Samimy, M. Control of an axi-symmetric jet using vortex generators. Phys of Fluids1994;6:778–93.10.1063/1.868316Suche in Google Scholar
7. LovarajuP, PaparaoKPV, RathakrishnanE. Shifted cross-wire for supersonic jet control. AIAA–2004–4080.Suche in Google Scholar
8. Navin KumarS, RathakrishnanE. Sonic jet control with tabs. Int J Turbo Jet-Engines2002;19:107–18.10.1515/TJJ.2002.19.1-2.107Suche in Google Scholar
9. SreejithRB, RathakrishnanE. Cross-wire as passive device for supersonic jet control. AIAA–2002–4052.Suche in Google Scholar
10. JayaprakashS, ThanigaiarasuS, ElangovanS, RathakrishnanE. Influence of tab geometry and its orientation on underexpanded sonic jets. Inst Mech Eng (UK) Part G, J Aerosp Eng2008;222:331–9.10.1243/09544100JAERO299Suche in Google Scholar
11. TakamaY, SuzukiK, RathakrishnanE. Visualization and size measurement of vortex shed by flat and arc plates in a uniform flow. Int Rev Aerosp Eng (IREASE)2008;1:55–60.Suche in Google Scholar
12. RathakrishnanE. Experimental studies on the limiting tab. AIAA J2009;47:2475–8510.2514/1.43790Suche in Google Scholar
13. RathakrishnanE. Applied gas dynamics. Hoboken, NJ: John Wiley, 2007.Suche in Google Scholar
14. RathakrishnanE. Instrumentation, measurements and experiments in fluids. Boca Raton, FL: CRC Press, 2007.Suche in Google Scholar
15. RathakrishnanE. Waves in correctly expanded supersonic jets. Int Rev Aerosp Eng (IREASE)2008;1:536–8Suche in Google Scholar
16. KaushikM, RathakrishnanE. Mixing characteristics of a supersonic jet in the presence of two neighboring jets. Int Rev Aerosp Eng (IREASE)2010;3:2–7.Suche in Google Scholar
17. KaushikM, RathakrishnanE. Corrugated limiting tab for jet mixing. Int J Turbo Jet Engines2013;30:359–73.10.1515/tjj-2013-0016Suche in Google Scholar
©2015 by De Gruyter
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- Compressor Instability Active Control via Closed-Coupled Valve and Throttle Actuators
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Artikel in diesem Heft
- Frontmatter
- Numerical Modeling of Unsteady Oil Film Motion Characteristics in Bearing Chambers
- Frequency Domain Identification of Multivariable Model for Aero-Engine using an Improved Maximum Likelihood Method
- Compressor Instability Active Control via Closed-Coupled Valve and Throttle Actuators
- Tab Aspect Ratio Effect on Supersonic Jet Mixing
- The Rotating Cavitation Performance of a Centrifugal Pump with a Splitter-Bladed Inducer under Different Rotational Speed
- Global Needs for Jet-Engine-Steered (JES) Strike Drones vs. Lack of Updated Textbooks to Design 6th Generation UCLASS Due to UCAV Failure
- Lightweight Magnesium Bipolar Plates of Direct NaBH4/H2O2 Fuel Cell for AIP Application
- Multidisciplinary Design Exploration for Sounding Launch Vehicle using Hybrid Rocket Engine in View of Ballistic Performance
