The Experts below are selected from a list of 3 Experts worldwide ranked by ideXlab platform
A A Yatskikh - One of the best experts on this subject based on the ideXlab platform.
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influence of small attack angles on the transition on the wing with the Subsonic Leading Edge at m 2
HIGH-ENERGY PROCESSES IN CONDENSED MATTER (HEPCM 2020): Proceedings of the XXVII Conference on High-Energy Processes in Condensed Matter dedicated to , 2020Co-Authors: N V Semionov, A D Kosinov, Yu G Yermolaev, V L Kocharin, S A Shipul, A A YatskikhAbstract:The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with a swept angle of 72° at Mach 2 which corresponds to a Subsonic Leading Edge. The transition location was determined using a constant temperature hot-wire anemometer. A comparison of the influence of small angles of attack on the transition position with a model with a supersonic Leading Edge is shown. The transition to a wing model with a Subsonic Leading Edge occurs earlier than on a wing model with a supersonic Leading Edge. The angle of attack has a significant effect on the position of the transition point from the laminar to turbulent flow. The data presented in the article are among the first results for a swept wing with a Subsonic Leading Edge.
N V Semionov - One of the best experts on this subject based on the ideXlab platform.
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influence of small attack angles on the transition on the wing with the Subsonic Leading Edge at m 2
HIGH-ENERGY PROCESSES IN CONDENSED MATTER (HEPCM 2020): Proceedings of the XXVII Conference on High-Energy Processes in Condensed Matter dedicated to , 2020Co-Authors: N V Semionov, A D Kosinov, Yu G Yermolaev, V L Kocharin, S A Shipul, A A YatskikhAbstract:The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with a swept angle of 72° at Mach 2 which corresponds to a Subsonic Leading Edge. The transition location was determined using a constant temperature hot-wire anemometer. A comparison of the influence of small angles of attack on the transition position with a model with a supersonic Leading Edge is shown. The transition to a wing model with a Subsonic Leading Edge occurs earlier than on a wing model with a supersonic Leading Edge. The angle of attack has a significant effect on the position of the transition point from the laminar to turbulent flow. The data presented in the article are among the first results for a swept wing with a Subsonic Leading Edge.
A D Kosinov - One of the best experts on this subject based on the ideXlab platform.
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influence of small attack angles on the transition on the wing with the Subsonic Leading Edge at m 2
HIGH-ENERGY PROCESSES IN CONDENSED MATTER (HEPCM 2020): Proceedings of the XXVII Conference on High-Energy Processes in Condensed Matter dedicated to , 2020Co-Authors: N V Semionov, A D Kosinov, Yu G Yermolaev, V L Kocharin, S A Shipul, A A YatskikhAbstract:The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with a swept angle of 72° at Mach 2 which corresponds to a Subsonic Leading Edge. The transition location was determined using a constant temperature hot-wire anemometer. A comparison of the influence of small angles of attack on the transition position with a model with a supersonic Leading Edge is shown. The transition to a wing model with a Subsonic Leading Edge occurs earlier than on a wing model with a supersonic Leading Edge. The angle of attack has a significant effect on the position of the transition point from the laminar to turbulent flow. The data presented in the article are among the first results for a swept wing with a Subsonic Leading Edge.
Yu G Yermolaev - One of the best experts on this subject based on the ideXlab platform.
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influence of small attack angles on the transition on the wing with the Subsonic Leading Edge at m 2
HIGH-ENERGY PROCESSES IN CONDENSED MATTER (HEPCM 2020): Proceedings of the XXVII Conference on High-Energy Processes in Condensed Matter dedicated to , 2020Co-Authors: N V Semionov, A D Kosinov, Yu G Yermolaev, V L Kocharin, S A Shipul, A A YatskikhAbstract:The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with a swept angle of 72° at Mach 2 which corresponds to a Subsonic Leading Edge. The transition location was determined using a constant temperature hot-wire anemometer. A comparison of the influence of small angles of attack on the transition position with a model with a supersonic Leading Edge is shown. The transition to a wing model with a Subsonic Leading Edge occurs earlier than on a wing model with a supersonic Leading Edge. The angle of attack has a significant effect on the position of the transition point from the laminar to turbulent flow. The data presented in the article are among the first results for a swept wing with a Subsonic Leading Edge.
V L Kocharin - One of the best experts on this subject based on the ideXlab platform.
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influence of small attack angles on the transition on the wing with the Subsonic Leading Edge at m 2
HIGH-ENERGY PROCESSES IN CONDENSED MATTER (HEPCM 2020): Proceedings of the XXVII Conference on High-Energy Processes in Condensed Matter dedicated to , 2020Co-Authors: N V Semionov, A D Kosinov, Yu G Yermolaev, V L Kocharin, S A Shipul, A A YatskikhAbstract:The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with a swept angle of 72° at Mach 2 which corresponds to a Subsonic Leading Edge. The transition location was determined using a constant temperature hot-wire anemometer. A comparison of the influence of small angles of attack on the transition position with a model with a supersonic Leading Edge is shown. The transition to a wing model with a Subsonic Leading Edge occurs earlier than on a wing model with a supersonic Leading Edge. The angle of attack has a significant effect on the position of the transition point from the laminar to turbulent flow. The data presented in the article are among the first results for a swept wing with a Subsonic Leading Edge.
