20.500.12556/RUL-174350 Research on a rapid method for obtaining the matching point of the static operating pressure of a supersonic jet in a wind tunnel In the wind tunnel test, mismatched operating pressures can cause the jet flow field to produce expansion waves, compression waves, and wave interference. The current wind tunnel pressure matching study requires continuous adjustment of the operating pressure at the inlet and outlet to obtain an ideal supersonic jet in an expanded state, and the pressure matching workload is substantial. This study presents a numerical simulation of the flow field of a supersonic wind tunnel under different outlet pressures based on the Reynolds-averaged Navier-Stokes (RANS) method. A method for quickly obtaining the static operating pressure matching point of a supersonic jet is proposed, which can quickly determine the matching operating pressure. When the Mach number of the monitoring point on the axis of the core area of the jet is within 5 % of the standard Mach number at the nozzle outlet, the jet in the wind tunnel test chamber is in an ideal expansion state, and the outlet pressure under this condition is the standard operating pressure for pressure matching. At the same time, the flow field structures under the conditions of over-expansion, ideal expansion, and under-expansion were compared, and it was shown that the key physical parameters in the core region of the supersonic jet field under the ideal expansion state obtained by this rapid matching method were stably distributed, which allowed the uniform region of the jet to exceed the limits of the diamond region and achieve uniform flow within the boundary of the supersonic jet. Pri preskusih v vetrovniku lahko neusklajeni obratovalni tlaki povzročijo, da se v toku curka pojavijo ekspanzijski valovi, kompresijski valovi in valovne interference. Trenutne raziskave usklajevanja tlakov v vetrovniku zahtevajo stalno prilagajanje obratovalnih tlakov na vstopu in izstopu, da se doseže idealno razširjeno stanje nadzvočnega curka, kar predstavlja veliko delovno obremenitev. V tej študiji predstavljamo numerično simulacijo toka v nadzvočnem vetrovniku pri različnih izstopnih tlakih na osnovi Reynoldsove metode povprečenih Navier-Stokesovih enačb (RANS). Predlagana je metoda za hitro določitev točke ujemanja statičnega obratovalnega tlaka nadzvočnega curka, s katero lahko hitro ugotovimo ustrezen obratovalni tlak. Kadar je Machovo število kontrolne točke na osi jedrnega območja curka znotraj 5 % standardnega Machovega števila na izstopu šobe, je curek v preskusni komori vetrovnika v stanju idealne ekspanzije. Izstopni tlak v teh razmerah predstavlja standardni obratovalni tlak. Hkrati smo primerjali strukture toka v pogojih prekomerne ekspanzije, idealne ekspanzije in premajhne ekspanzije. Pokazalo se je, da so ključni fizikalni parametri v jedrnem območju nadzvočnega curka v stanju idealne ekspanzije, pridobljene s to hitro metodo, stabilno porazdeljeni, kar omogoča, da enakomerno območje curka preseže meje rombastega območja in zagotovi enakomeren tok znotraj meja nadzvočnega curka. supersonic jet pressure matching expansion wave compression wave nadzvočni curek ujemanje tlaka ekspanzijski val kompresijski val true false true Angleški jezik Slovenski jezik Članek v reviji 2025-10-01 11:07:01 2025-10-01 11:07:07 2025-11-21 03:37:02 0000-00-00 00:00:00 2025 0 0 13 str. no. 3/4 Vol. 71 2025 0000-00-00 Zaloznikova Objavljeno NiDoloceno 0000-00-00 0000-00-00 0000-00-00 621 2536-3948 10.5545/sv-jme.2024.1199 251132163 RAZ_Liu_Peng_2025.pdf RAZ_Liu_Peng_2025.pdf 1 F09D33ACA02DBD3E8D8B9CD482DD953F 5f2530ae17d99de07a9e853a1c2f329df0c5ff161100c4e81288b8ca5ec1b31a 15888667-9ea6-11f0-9328-0050569b8976 https://repozitorij.uni-lj.si/Dokument.php?lang=slv&id=219143 https://www.sv-jme.eu/sl/article/research-on-a-rapid-method-for-obtaining-the-matching-point-of-the-static-operating-pressure-of-a-supersonic-jet-in-a-wind-tunnel/ 1 cee811f1-9ea5-11f0-9328-0050569b8976 https://repozitorij.uni-lj.si/Dokument.php?lang=slv&id=219142 Fakulteta za strojništvo Strojniški vestnik 0 0 0