2064 KB0 KB199920252025Karadeniz, Ziya HaktanKiral, ZekiÜmütlü Ayaz, Hatice Cansuštevilka:1/2letnik:71str. 51-57COBISSID_HOST:235367171ISSN:2536-3948URN:URN:NBN:SI:doc-XM74MA97enFakulteta za strojništvoStrojniški vestnikaerodinamični koeficientiaerodinamični profilaerodynamic coefficientsairfoilaspect ratio effectlow Reynolds numbernizko Reynoldsovo številothree-component balancetri-komponentni merilnik silvetrovnikvitkost krilawind tunnelNumerical and experimental investigation of aspect ratio effect on aerodynamic performance of NACA 4415 airfoil section at low reynolds number|In this study, the effect of aspect ratio on the aerodynamic coefficients is investigated for a NACA 4415 airfoil profile. Four different aspect ratios which are 3, 5, 7, and 9 are evaluated with the computational fluid dynamics (CFD) simulations and the experiments. The CFD studies are performed using a three-dimensional (3D) computational domain and by using the k–? shear stress transport (SST) turbulence model for turbulence calculations. The measurements of the aerodynamic forces are carried out in open jet type wind tunnel using a three-component balance. CFD and experimental studies are performed at angles of attack from 0° to 25° and Reynolds number 85e3. The results show that as the aspect ratio increases, separation points move towards the leading edge of the airfoil and the stall angle reduces. Furthermore, it is observed that the lift coefficients increase with the increasing aspect ratio. The results obtained indicate that there is a harmony between the experimental data and the CFD solutionsV tej študiji je raziskan vpliv vitkosti krila na aerodinamične koeficiente profila krila NACA 4415. S simulacijami računalniške dinamike tekočin (CFD) in eksperimenti so obravnavane štiri različne vrednosti vitkosti kril, in sicer 3, 5, 7 in 9. CFD analize so izvedene s tridimenzionalno (3D) računsko domeno, za izračun turbulence pa se uporablja model k-? za prenos strižne napetosti (SST). Meritve aerodinamičnih sil so bile opravljene v vetrovniku z odprtim tokom z uporabo tri-komponentnega merilnika sil. CFD analize in eksperimentalne meritve so bile izvedene pri naklonskih kotih od 0° do 25° in Reynoldsovem številu 85·103. Rezultati kažejo, da se s povečevanjem vitkosti krila ločilne točke pomikajo proti sprednjemu robu krila in da se kritični vpadni kot zmanjšuje. Poleg tega je opaziti, da se koeficient vzgona povečuje z naraščajočo vitkostjo krila. Dobljeni rezultati kažejo, da obstaja skladnost med eksperimentalnimi meritvami in rezultati CFD analizTEXTznanstveno časopisjejournalsSlovenian National E-content AggregatorNational and University Library of SloveniaUniverza v Ljubljani, Fakulteta za strojništvo