Дисертації з теми "Jet engine inlet"
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Hoopes, Kevin M. "A New Method for Generating Swirl Inlet Distortion for Jet Engine Research." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/49545.
Повний текст джерелаA new method capable of recreating any arbitrary swirl distortion profile is needed in order to expand the capabilities of inlet distortion testing. This will allow designers to explore how an engine would react to a particular engine airframe combination as well as methods for creating swirl distortion tolerant engines. The following material will present such a method as well as experimental validation of its effectiveness.
Master of Science
Kumar, Abhinav. "Flow control optimization in a jet engine serpentine inlet duct." [College Station, Tex. : Texas A&M University, 2007. http://hdl.handle.net/1969.1/ETD-TAMU-1399.
Повний текст джерелаTichenor, Nathan Ryan. "Particle image velocimetry in an advanced, serpentine jet engine inlet duct." Thesis, [College Station, Tex. : Texas A&M University, 2007. http://hdl.handle.net/1969.1/ETD-TAMU-1401.
Повний текст джерелаKirk, Aaron Michael. "Active flow control in an advanced serpentine jet engine inlet duct." [College Station, Tex. : Texas A&M University, 2006. http://hdl.handle.net/1969.1/ETD-TAMU-1027.
Повний текст джерелаReilly, Daniel. "An Investigation into Jet Engine Inlet Flow Characteristics for Turbine-Powered Helicopters." The Ohio State University, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=osu1429608968.
Повний текст джерелаYarlagadda, Santosh. "Performance Analysis of J85 Turbojet Engine Matching Thrust with Reduced Inlet Pressure to the Compressor." University of Toledo / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1271367584.
Повний текст джерелаGiuliani, James Edward. "Jet Engine Fan Response to Inlet Distortions Generated by Ingesting Boundary Layer Flow." The Ohio State University, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=osu1468564279.
Повний текст джерелаSivapragasam, M. "Numerical and experimental investigations on multiple air jets in counterflow for generating aircraft gas turbine engine inlet flow distortion patterns." Thesis, Coventry University, 2014. http://curve.coventry.ac.uk/open/items/0ad1d0c2-6693-4c6e-9224-5a2237862074/1.
Повний текст джерелаClark, Adam. "Predicting the Crosswind Performance of High Bypass Ratio Turbofan Engine Inlets." The Ohio State University, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=osu1476265135449178.
Повний текст джерелаLambie, David. "Inlet distortion and turbofan engines." Thesis, University of Cambridge, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.305300.
Повний текст джерелаMathison, Randall Melson. "Experimental and Computational Investigation of Inlet Temperature Profile and Cooling Effects on a One and One-Half Stage High-Pressure Turbine Operating at Design-Corrected Conditions." The Ohio State University, 2009. http://rave.ohiolink.edu/etdc/view?acc_num=osu1250281163.
Повний текст джерелаBabinec, Viktor. "Návrh sacího kanálu turbínového motoru v provedení NACA vstup." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2018. http://www.nusl.cz/ntk/nusl-377522.
Повний текст джерелаAbdullah, Abu Hasan. "The application of high inlet swirl angles for broad operating range turbocharger compressor." Thesis, University of Bath, 1996. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.320555.
Повний текст джерелаMalo-Molina, Faure Joel. "Numerical study of innovative scramjet inlets coupled to combustors using hydrocarbon-air mixture." Diss., Georgia Institute of Technology, 2010. http://hdl.handle.net/1853/33906.
Повний текст джерелаBaig, Saood Saeed. "A simple moving boundary technique and its application to supersonic inlet starting /." Thesis, McGill University, 2008. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=112555.
Повний текст джерелаThe developed technique is rather general and can be used with virtually any finite-volume or finite-difference scheme, since the modifications of the schemes themselves are not required. In the present study the proposed technique has been incorporated into a one-dimensional non-adaptive Euler code and a two-dimensional locally adaptive unstructured Euler code.
It is shown that the new approach is conservative with the order of approximation near the moving boundaries. To reduce the conservation error, it is beneficial to use the method in conjunction with local grid adaptation.
The technique is verified for a number of one and two dimensional test cases with analytical solutions. It is applied to the problem of supersonic inlet starting via variable geometry approach. At first, a classical starting technique of changing exit area by a moving wedge is numerically simulated. Then, the feasibility of some novel ideas such as a collapsing frontal body and "tractor-rocket" are explored.
Eisemann, Kevin Michael. "A Computational Study of Compressor Inlet Boundary Conditions with Total Temperature Distortions." Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/35969.
Повний текст джерелаMaster of Science
Mahapatra, Debabrata. "Investigation Of Ramp/Cowl Shock Interaction Processes Near A Generic Scramjet Inlet At Hypersonic Mach Number." Thesis, 2008. http://hdl.handle.net/2005/807.
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