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Journal of Aerospace Science and Technology، جلد ۱۷، شماره ۱، صفحات ۴۷-۵۹
عنوان فارسی Design and Analysis of Supersonic Inlet for Ramjet Engines: Aerodynamic Considerations and Performance Optimization
چکیده فارسی مقاله This research delves into the intricate realm of supersonic inlet design for ramjet engines, honing in on the critical aerodynamic considerations and optimization of performance factors. At Mach 2.5, the study meticulously scrutinizes pivotal design parameters, including the placement and number of inclined shocks, cowl-lip positioning, throat area, spike location, and diffuser length. Computational fluid dynamics simulations are harnessed to unravel the intricate flow dynamics and assess the proposed inlet geometry's performance.The findings reveal a nuanced relationship between back pressure and shock wave positioning, where increasing back pressure initiates a shift in the shock wave, impacting the flow state. The paper delineates this transition, emphasizing the pivotal back pressure range of 300,000 to 350,000 pascals, where optimal shock wave alignment corresponds with design parameters, achieving a supercritical state.However, elevating back pressure beyond this range triggers a sub-critical state and mass flow overflow as the shock exits the throat.the study explores various performance metrics, encompassing drag coefficient, distortion coefficient, mass flow ratio and total pressure recovery under varying back pressure conditions. The outcomes underscore the merits of higher back pressures, which mitigate drag coefficient and distortion while amplifying TPR.In the sub-critical state, MFR diminishes due to shock wave displacement beyond the intake opening.This research illuminates the intricate dance of aerodynamics within ramjet engine inlets and underscores the paramount significance of optimizing inlet geometry to unlock heightened performance. It effectively encapsulates the essence of the full article, enticing readers to embark on a deeper exploration of this crucial area of aerospace engineering.
کلیدواژه‌های فارسی مقاله
عنوان انگلیسی Design and Analysis of Supersonic Inlet for Ramjet Engines: Aerodynamic Considerations and Performance Optimization
چکیده انگلیسی مقاله This research delves into the intricate realm of supersonic inlet design for ramjet engines, honing in on the critical aerodynamic considerations and optimization of performance factors. At Mach 2.5, the study meticulously scrutinizes pivotal design parameters, including the placement and number of inclined shocks, cowl-lip positioning, throat area, spike location, and diffuser length. Computational fluid dynamics simulations are harnessed to unravel the intricate flow dynamics and assess the proposed inlet geometry's performance.The findings reveal a nuanced relationship between back pressure and shock wave positioning, where increasing back pressure initiates a shift in the shock wave, impacting the flow state. The paper delineates this transition, emphasizing the pivotal back pressure range of 300,000 to 350,000 pascals, where optimal shock wave alignment corresponds with design parameters, achieving a supercritical state.However, elevating back pressure beyond this range triggers a sub-critical state and mass flow overflow as the shock exits the throat.the study explores various performance metrics, encompassing drag coefficient, distortion coefficient, mass flow ratio and total pressure recovery under varying back pressure conditions. The outcomes underscore the merits of higher back pressures, which mitigate drag coefficient and distortion while amplifying TPR.In the sub-critical state, MFR diminishes due to shock wave displacement beyond the intake opening.This research illuminates the intricate dance of aerodynamics within ramjet engine inlets and underscores the paramount significance of optimizing inlet geometry to unlock heightened performance. It effectively encapsulates the essence of the full article, enticing readers to embark on a deeper exploration of this crucial area of aerospace engineering.
کلیدواژه‌های انگلیسی مقاله Ultrasonic air intake, Flow Separation, Total Pressure Recovery, Mass Flow Ratio Designing, numerical simulation
نویسندگان مقاله Mohammad Hossein Moghimi EsfandAbadi |
Department of Mechanical and Aerospace Engineering, Ferdowsi University of Mashhad, Mashhad,Iran

Adnan Mohammadi |
Department of Mechanical and Aerospace Engineering, Ferdowsi University of Mashhad, Mashhad, Iran

Mohammad Hassan Djavareshkian |
Department of Mechanical and Aerospace Engineering, Ferdowsi University of Mashhad, Mashhad, Iran

نشانی اینترنتی https://jast.ias.ir/article_182890_010f57f43ef84aa701d4d4d3ec8f9baf.pdf
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