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- W4366127914 abstract "Indian Space Research Organization (ISRO) is in the process of developing a new breed of “On Demand” relatively smaller launch vehicle. This class of vehicle is configured with upper stage solid rocket motors having higher area ratio nozzle (52 AR). Hence, it is highly imperative to ascertain the exact realizable vacuum specific impulse (Isp) which is crucial for mission studies. Also, it is required to understand the nozzle efficiency in terms of nozzle contour, particle impingement if any etc. As the numerical prediction (CFD) of vacuum specific impulse for this 52 area ratio nozzle has its own limitations, with multiple assumptions like two phase flow loss, gas molecular weight estimation, and particle impingement etc, a suitable scale model hot flow experimental study with high altitude test (HAT) simulation has been initiated. This experimental study with exact solid propellant configuration would bring out the exact vacuum specific impulse (Isp) for this 52 AR nozzle. For this purpose, a HAT configuration was conceived, designed and realized. Subsequently a hot flow scale model study has been conducted at High Altitude Test Facility of Satish Dhawan Space Center (SDSC), SHAR, ISRO. Hot flow Simulation test configuration includes the design of scaled down solid rocket motor, contour nozzle with 52 AR, a newly designed supersonic zero co-flow ejector system (straight cylindrical diffuser-SED), external spray cooling system and a single component axial tension type thrust measurement system etc. This paper deals with the exact simulation parameters, HAT configuration and the performance characteristics of supersonic diffuser in starting the higher AR (52) nozzle in order to compute the exact realizable vacuum Isp." @default.
- W4366127914 created "2023-04-19" @default.
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- W4366127914 date "2023-01-01" @default.
- W4366127914 modified "2023-10-09" @default.
- W4366127914 title "Experimental Evaluation of Vacuum Specific Impulse for Higher Area Ratio Nozzle Adopting A Supersonic Straight Cylindrical Exhaust Diffuser using Scaled Solid Rocket Motor" @default.
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- W4366127914 doi "https://doi.org/10.1007/978-981-19-6270-7_8" @default.
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