Prilog numeričkoj analizi aerodinamičkih karakteristika aeroprofila
A contribution to the numerical analysis of the aerodynamic characteristics of airfoils
Abstract
U radu je prikazan algoritam namenjen numeričkom određivanju aerodinamičkih koeficijenata vazduhoplovnih aroprofila pri različitim napadnim uglovima Reynoldsovim brojevima i podzvučnim i okozvučnim Machovim brojevima. Korišćen je zonalni model strujnog polja i uvedeni su specifični pristupi u modeliranju graničnog sloja za odgovarajuće dijapazone napadnih uglova, kao i algoritam proračuna talasnog otpora za oblast niže transonike, koji obezbeđuje stabilnu konvergenciju rešenja i pouzdane rezultate. Proračun se po ovom algoritmu vrši u okviru softverskog paketa koji analizu obavlja sukcesivno na seriji pravougaonih mreža čija se gustina u fazama progresivno uvećava, čime je omogućena vrlo brza konvergencija rešenja.
This paper presents an algorithm for the numerical calculations of the aerodynamic characteristics of aviation airfoils at different angles of attack, Reynolds numbers and subsonic and transonic Mach numbers. The zonal flowfield model is applied, and special approaches have been used in boundary layer calculations for different ranges of angles of attack and also in lower transonic flow analysis, enabling stable convergence of the solutions and reliable results. The calculation is done on a series of rectangular grids with successively increasing fineness. Calculations are confined to 2D single element airfoil analyses, and angles of attack up to around-critical values. Results obtained using this algorithm, in the available domains of application, verified by comparison with reliable experimental data, are quite compatible with the results of much more complex software packages. Another advantage of here presented model is that the influence of the user experience factor on the qualit...y of the results has been reduced to a minimum. Applications of this algorithm in some special aspects of airfoil design have also been presented.
Keywords:
Rejnoldsov broj / napadni ugao / aerodinamički koeficijent / Reynolds numbers / angles of attack / aerodynamic characteristicsSource:
Tehnika - Mašinstvo, 2006, 55, 5, 19-26Publisher:
- Savez inženjera i tehničara Srbije, Beograd
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Institution/Community
Mašinski fakultetTY - JOUR AU - Kostić, Ivan PY - 2006 UR - https://machinery.mas.bg.ac.rs/handle/123456789/605 AB - U radu je prikazan algoritam namenjen numeričkom određivanju aerodinamičkih koeficijenata vazduhoplovnih aroprofila pri različitim napadnim uglovima Reynoldsovim brojevima i podzvučnim i okozvučnim Machovim brojevima. Korišćen je zonalni model strujnog polja i uvedeni su specifični pristupi u modeliranju graničnog sloja za odgovarajuće dijapazone napadnih uglova, kao i algoritam proračuna talasnog otpora za oblast niže transonike, koji obezbeđuje stabilnu konvergenciju rešenja i pouzdane rezultate. Proračun se po ovom algoritmu vrši u okviru softverskog paketa koji analizu obavlja sukcesivno na seriji pravougaonih mreža čija se gustina u fazama progresivno uvećava, čime je omogućena vrlo brza konvergencija rešenja. AB - This paper presents an algorithm for the numerical calculations of the aerodynamic characteristics of aviation airfoils at different angles of attack, Reynolds numbers and subsonic and transonic Mach numbers. The zonal flowfield model is applied, and special approaches have been used in boundary layer calculations for different ranges of angles of attack and also in lower transonic flow analysis, enabling stable convergence of the solutions and reliable results. The calculation is done on a series of rectangular grids with successively increasing fineness. Calculations are confined to 2D single element airfoil analyses, and angles of attack up to around-critical values. Results obtained using this algorithm, in the available domains of application, verified by comparison with reliable experimental data, are quite compatible with the results of much more complex software packages. Another advantage of here presented model is that the influence of the user experience factor on the quality of the results has been reduced to a minimum. Applications of this algorithm in some special aspects of airfoil design have also been presented. PB - Savez inženjera i tehničara Srbije, Beograd T2 - Tehnika - Mašinstvo T1 - Prilog numeričkoj analizi aerodinamičkih karakteristika aeroprofila T1 - A contribution to the numerical analysis of the aerodynamic characteristics of airfoils EP - 26 IS - 5 SP - 19 VL - 55 UR - https://hdl.handle.net/21.15107/rcub_machinery_605 ER -
@article{ author = "Kostić, Ivan", year = "2006", abstract = "U radu je prikazan algoritam namenjen numeričkom određivanju aerodinamičkih koeficijenata vazduhoplovnih aroprofila pri različitim napadnim uglovima Reynoldsovim brojevima i podzvučnim i okozvučnim Machovim brojevima. Korišćen je zonalni model strujnog polja i uvedeni su specifični pristupi u modeliranju graničnog sloja za odgovarajuće dijapazone napadnih uglova, kao i algoritam proračuna talasnog otpora za oblast niže transonike, koji obezbeđuje stabilnu konvergenciju rešenja i pouzdane rezultate. Proračun se po ovom algoritmu vrši u okviru softverskog paketa koji analizu obavlja sukcesivno na seriji pravougaonih mreža čija se gustina u fazama progresivno uvećava, čime je omogućena vrlo brza konvergencija rešenja., This paper presents an algorithm for the numerical calculations of the aerodynamic characteristics of aviation airfoils at different angles of attack, Reynolds numbers and subsonic and transonic Mach numbers. The zonal flowfield model is applied, and special approaches have been used in boundary layer calculations for different ranges of angles of attack and also in lower transonic flow analysis, enabling stable convergence of the solutions and reliable results. The calculation is done on a series of rectangular grids with successively increasing fineness. Calculations are confined to 2D single element airfoil analyses, and angles of attack up to around-critical values. Results obtained using this algorithm, in the available domains of application, verified by comparison with reliable experimental data, are quite compatible with the results of much more complex software packages. Another advantage of here presented model is that the influence of the user experience factor on the quality of the results has been reduced to a minimum. Applications of this algorithm in some special aspects of airfoil design have also been presented.", publisher = "Savez inženjera i tehničara Srbije, Beograd", journal = "Tehnika - Mašinstvo", title = "Prilog numeričkoj analizi aerodinamičkih karakteristika aeroprofila, A contribution to the numerical analysis of the aerodynamic characteristics of airfoils", pages = "26-19", number = "5", volume = "55", url = "https://hdl.handle.net/21.15107/rcub_machinery_605" }
Kostić, I.. (2006). Prilog numeričkoj analizi aerodinamičkih karakteristika aeroprofila. in Tehnika - Mašinstvo Savez inženjera i tehničara Srbije, Beograd., 55(5), 19-26. https://hdl.handle.net/21.15107/rcub_machinery_605
Kostić I. Prilog numeričkoj analizi aerodinamičkih karakteristika aeroprofila. in Tehnika - Mašinstvo. 2006;55(5):19-26. https://hdl.handle.net/21.15107/rcub_machinery_605 .
Kostić, Ivan, "Prilog numeričkoj analizi aerodinamičkih karakteristika aeroprofila" in Tehnika - Mašinstvo, 55, no. 5 (2006):19-26, https://hdl.handle.net/21.15107/rcub_machinery_605 .