Experimental and numerical investigation into the wake of a supercritical airfoil in a compressible unsteady flow

• Published in: Proceedings of the Institution of Mechanical Engineers. Part G, Journal of aerospace engineering Journal of aerospace engineering, 2017-03, Vol.231 (3), p.419-434
• Main Authors: Beheshti Boroumand, B, Mani, M, Fallahpour, N
• Format: Article
• Language: English
• Subjects: Aerodynamics; Amplitudes; Compressibility; Computational fluid dynamics; Computer simulation; Correlation analysis; Incidence angle; Mach number; Power spectral density; Sensors; Supercritical airfoils; Turbulence intensity; Unsteady flow; Velocity measurement
• ISSN: 0954-4100; 2041-3025
• DOI: 10.1177/0954410016638873

Experimental investigations were carried out to study the wake characteristics of a pitching supercritical airfoil at Mach number of 0.6. Flow field inside the wake was measured by a hot-wire anemometry at downstream distances from trailing edge of 0.25 and 0.5 times the chord length. All data were taken at mean incidence angles of 0 and 3°. The amplitudes of oscillation were 1 and 3° while the oscillation frequencies were 3 and 6 Hz. Output signals acquired from sensors were analyzed besides the effects of such parameters as frequency and oscillation amplitude. Moreover, a comprehensive numerical study was carried out for the same airfoil under similar experimental test conditions; then, the results of numerical simulations were analyzed and compared with those of experimental tests. Results of the present research could be summarized as: observation of hysteresis and how it is affected by frequency and amplitude variations, observation of increasing turbulence intensity by root mean square investigation and also increasing signal energy by means of power spectral density diagram for those sensors lied inside the wake, and finally, study of correlation between wake’s interior sensors and exterior ones.