- Tytuł:
- Improvement of helicopter performance using self - supplying air jet vortex generators
- Autorzy:
- Krzysiak, A.
- Powiązania:
- https://bibliotekanauki.pl/articles/244313.pdf
- Data publikacji:
- 2013
- Wydawca:
- Instytut Techniczny Wojsk Lotniczych
- Tematy:
-
air vehicle
helicopter
applied aerodynamics
vortex generation - Opis:
- The work presents the results of experimental wind tunnel tests of using self-supplying air jet vortex generators to delay dynamic stall on helicopter blade due to attain high angles of attack. The dynamic stall which may appear on retreating helicopter blade is considered as the most severe type of stall, characterized by a strong vortex that forms on the blade’s upper surface. Its appearance is a significant limitation of helicopter performance. To improve helicopter aerodynamic characteristics the using of self-supplying air jet vortex generators was proposed. In comparison with the conventional air-jet vortex generators, which are supplied with the air from an external compressor, the self-supplying generators receive air from the overpressure region situated in the nose part of the blade lower surface at the higher angles of attack. The paper presents a comparison of the effectiveness of both types of generators based on tests performed in low speed wind tunnel T-1 in the Institute of Aviation (IoA) in the range of Mach numbers M =0.05-0.1. The experimental tests modeling periodic changes of flow around helicopter blade airfoil equipped with proposed self-supplying air jet vortex generators were performed in tri-sonic wind tunnel N-3 (with 0.6 x 0.6 m test section) in the IoA for Mach numbers M = 0.2 and 0.3. The NACA 0012 airfoil model of 0.18 m chord length used in wind tunnel test was oscillating in pitch ( alfa = ±50 with frequency 5 Hz) about an axis located at 35% chord length from the airfoil leading edge.
- Źródło:
-
Journal of KONES; 2013, 20, 2; 229-236
1231-4005
2354-0133 - Pojawia się w:
- Journal of KONES
- Dostawca treści:
- Biblioteka Nauki
Artykuł