Turbulent triggers and the model quality influence on aerodynamic characteristics of the laminar aerofoil in transonic flow regime

• Autorzy: Placek Robert , Ruchała Paweł

Identyfikatory

DOI

10.2478/kones-2019-0083

• Języki publikacji: EN

Abstrakty

EN

The test with a roughness application on the laminar aerofoil has been conducted in the N-3 trisonic wind tunnel of the Institute of Aviation in Warsaw. The main goal of tests was to investigate the influence of the boundary layer transition triggers on a laminar profile aerodynamic characteristic. For baseline configuration, the natural transition was applied. As a local roughness on the upper model surface, the carborundum strips with different heights were applied. These were positioned on the upper model surface in the front of the shock position occurrence. The Mach number during test was equal Ma = 0.7 and Reynolds number was about 2.85·106 . Tests have been conducted for different model incidence in range 0º-7º. Current article refers partially to the previous study, where aerofoil model with lower quality of surface had been tested. Investigation results from previous work indicated that some of transition positions improved an aerodynamic characteristic by reducing the drag coefficient value and decreasing shock wave unsteadiness in the transonic regime. However, current article indicates that beneficial effects in respect to the baseline configuration are also strictly dependent on the model quality and turbulent triggers size. Improved surface quality of the laminar aerofoil model affected on aerodynamic characteristics with and without turbulent triggers. Resultant aerodynamic coefficients of all tested cases i.e. drag, lift and lift to drag ratio were compared.

Słowa kluczowe

EN

transonic flow; aerofoil; model quality; aerodynamic characteristics; shock wave

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2019
• Tom: Vol. 26, No. 3
• Strony: 165--172
• Opis fizyczny: Bibliogr. 4 poz., rys.

Twórcy

autor

Placek Robert

• Łukasiewicz Research Network – Institute of Aviation Department of Aerodynamics Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 360, 312

autor

Ruchała Paweł

• Łukasiewicz Research Network – Institute of Aviation Department of Aerodynamics Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 360, 312

Bibliografia

• [1] Braslow, A. L., Knox, E. C., Simplified method for determination of critical height of distributed roughness particles for boundary-layer transition at Mach numbers from 0 to 5, NACA-TN-4363, 1958.
• [2] Placek, R., Miller, M., Ruchała, P., The flow separation development analysis in subsonic and transonic flow regime of the laminar airfoil, Transportation Research Procedia, Vol. 29, pp. 323-329, 2018.
• [3] Placek, R., Miller, M., Ruchała, P., The roughness position influence on laminar aerofoil aerodynamic characteristic in transonic flow regime, Proceedings of ICAS, nr 2016_0561, Daejeon 2016.
• [4] Placek, R., Stryczniewicz, W., Identification of the boundary layer shock wave interaction type in transonic flow regime, Journal of KONES Powertrain and Transport, Vol. 23, No. 2, pp. 285-292, 2016.

Uwagi

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2019).