Phyo Wai Thaw

The University of Auckland, Mechanical Engineering, Graduate Student

Myanmar Aerospace Engineering University, Fluid Energy and Environmental Engineering Lab, Researcher

Myanmar Aerospace Engineering University, Department of Propulsion and Flight Vehicles, Graduate Student

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As an aerospace engineering graduate, I have got some experience in academic research and reviewing academic journals. I have also published some research journals and conference papers. I am definitely keen on fluid mechanics, computational fluid dynamics, optimization, aerodynamics and wind energy.

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Nanyang Technological University

Naseeb A H M E D Siddiqui

University of Ontario Institute of Technology

IIUM

Virginia Tech

Università degli Studi di Napoli "Federico II"

Amit Thakur

JOSÉ ALEXANDRE A L E X A N D R E T A V A R E S G U E R R E I R O FREGNANI

Taewoo Nam

Sungkyunkwan University

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Papers by Phyo Wai Thaw

Design and Optimization of Aircraft Configuration for Minimum Drag

International Journal of Aviation, Aeronautics, and Aerospace, 2018

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Optimum Line of High Bypass Twin Spool Separated Flow Turbofan Engine

by Phyo Wai Thaw and Than Swe

Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids... more Today’s modern aircraft is based on air-breathing jet propulsion systems, which use moving fluids as substances to transform energy carried by the fluids into power. Throughout aero-vehicle evolution, improvements have been made to the engine performances and pollutants reduction. These goals were achieved by changing of the bypass ratio (B), fan pressure ratio (Pf), overall pressure ratio (OPR), turbine inlet temperature (TIT) as well as using new materials, production and cooling techniques for both turbines and combustion chamber. Such modifications led to improvements in thermal, propulsive and overall efficiencies, decreases in thrust specific fuel consumption (TSFC) and increase the specific thrust. This paper describes an optimization of a twin spool, separated flow, high bypass turbofan engine and focuses on maximum specific thrust (Fs) with optimum specific fuel consumption (SFC). The two variables, fan pressure ratio (Pf) and bypass ratio (B), were selected as ranges of 1....

OPERATIONAL OPTIMIZATION OF MICRO GAS TURBINE ENGINE FOR HIGHER PERFORMANCE

by Phyo Wai Thaw and Zin Win Thu

International Journal of Advance Engineering and Research Development, 2018

This paper present the optimum operation of the Micro Gas Turbine Engine that is minimum specific... more This paper present the optimum operation of the Micro Gas Turbine Engine that is minimum specific fuel consumption and maximum specific thrust. In the turbojet engine, the main operating variables are: compressor pressure ratio and turbine inlet temperature. These variables affect the specific thrust and specific fuel consumption (SFC), which represent the main performance parameters. The analytical results show that the specific thrust and specific fuel consumption strongly depend on TIT and compressor pressure ratio (Pr). From the variation of TIT and Pr, the results show that the optimum running line (ORL) give while the engine is running at optimum (TIT) and (Pr) for higher performance.

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Development and Validation of Hypersonic Engine Inlet Design Code

International Journal of Research and Scientific Innovation, 2018

This paper describes the numerical investigation of scramjet inlet and validation through computa... more This paper describes the numerical investigation of scramjet inlet and validation through computational fluid dynamics (CFD). The scramjet inlet design (SID) program was also developed and used to design a new scramjet inlet geometry which satisfies shock-on-lip (SOL) condition at Mach 3. This inlet design was further tested by means of CFD and the inviscid data showed that it meets SOL condition and reached the required pressure at the isolator exit to get good burning. Nomenclature η KE_ad = adiabatic kinetic energy efficiency A = area l = cowl's placement from inlet's tip θ = deflection, turning angle ρ = density s = entropy x 1 = forebody's horizontal length x 2 = intake ramp's horizontal length y 2 = isolator's height M = Mach number π c = pressure recovery, total pressure ratio y 1 = scramjet inlet's height β = shock wave angle R = specific gas constant γ = specific heat ratio P = static pressure P 0 = total pressure T = temperature í µí¼ = reflected shock wave angle

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Design and Optimization of Aircraft Configuration for Minimum Drag

by Zin Win Thu and Phyo Wai Thaw

IJAAA (Interantional Jouranl of Aviation, Aeronautics and Aerospace), 2018

This paper presents a reliable and robust optimization for minimum drag of an aircraft at the con... more This paper presents a reliable and robust optimization for minimum drag of an aircraft at the conceptual design phase. Firstly, the conceptual design code was developed and existing Single Seat Aerobatic (SSA) aircraft was chosen to validate the reliability of developed code. The resulted data from the developed code showed good agreement with the existing data. Secondly, Sequential Quadratic Programming (SQP) optimizer was created and employed as a tool to explore possible aircraft configurations that are more efficient and less costly than an existing design. The optimized results gave lower Drag and better performance.

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