Aeroacoustic measurement of 30P30N high-lift configuration in the test section with Kevlar cloth and perforated plate

Aerodynamic and aeroacoustic performance of high-lift airfoil fitted with slat cove fillers

“…Choudhari and Khorrami [12] showed that the overall slat noise is generated from the unsteady flow within the slat cove region originating from the vortex shedding at the slat cusp and the slat trailing edge. Terracol et al [22] showed that the strong tonal peak in the mid-frequency range (St s = 1 − 5) is generated due to the flow acoustic feedback of slat cove shear layer instabilities, which has also been observed in other studies [12][13][14][15][16][17][18][19][20][21][22][24][25][26][27][28][29][30][31]. The results are also indicative that the tonal peaks are associated with the cavity feedback mechanism, known as the Rossiter modes [56,57].…”

“…A possible quadratic interaction between the tonal peaks has also been observed [23][24][25][26][27]. Apart from these discrete tones, a spectral hump at low-frequency range (St s < 1) were identified in recent studies [22,26,[28][29][30][31]. Pascioni et al [26] suggested that the lowfrequency broadband hump at St s > 1 is related to the slat cove bulk-oscillation, which is associated with the flapping of the slat cusp shear layer.…”

Aeroacoustic Performance of High-lift Airfoil with Slat Cove Fillers

“…Studies on conventional slat and wing configurations have shown that it mainly comprises of broadband and tonal noise components. Several studies on slat noise have shown several discrete tones at mid-frequency range [17][18][19][20][21][22][23][24][25][26][27][28][29]. However, their aeroacoustic mechanism is yet to be fully understood.…”

Aerodynamics of the turbulent flow around a multi­element airfoil in cruse configuration and in takeoff and landing configuration

“…Mathematical modeling of the turbulent flow around multi-element airfoils is a rather difficult task of computational aerodynamics [4,5]. Many publications in the modern scientific literature attempt to solve this problem [6][7][8][9][10][11][12][13].…”

“…Work [7] presents experimental and numerical results from studying the aerodynamic and acoustic characteristics of the airfoil 30P30N at a Mach number of 0.17 and the angles of attack from 0° to 8°. The study focused on an acoustic field analysis, the spectral shape of noise, the tonal frequency and location of the noise source.…”