Abstract
A typical feature on a transonic airfoil is associated with a quasi-normal shock on the upper surface. When a shock is strong enough, development of a separation bubble changes the flowfield significantly. High intensity of pressure fluctuations is associated with unsteady shock wave. An experimental study was conducted to investigate transonic convex-corner flows, including single- and round-convex corners. Peak pressure fluctuations and zero-crossing frequency are associated with incoming Mach number, total turning angle, and separation length. In the cases of R100 and R200, the level of zero-crossing frequency decreases with increasing turning angle as observed in the single convex-corner flows. An increase in the level of pressure fluctuations corresponds to lower zero-cross frequency. In the cases of R300, there is a roughly constant level of surface pressure fluctuations or the variation of pressure fluctuations with the turning angle is less significant. The zero-crossing frequency would be independent of turning angle in the cases of R300.
Highlights
Aircraft designs have employed flaps for takeoff and landing performance and ailerons for routine turning maneuver
In the previous studies[2,3,4,5,6,7,8,9], a sharp convex corner was adopted as an idealized configuration that models
The typical feature is the conversion of the pressure signal into a “boxcar” of amplitude unity and varying frequency. One such algorithm, which separates pressure fluctuations caused by the shock motion from those of the boundary layer, is based on a two-threshold method (TTM) boxcar conversion technique
Summary
Aircraft designs have employed flaps for takeoff and landing performance and ailerons for routine turning maneuver. In the previous studies[2,3,4,5,6,7,8,9], a sharp convex corner was adopted as an idealized configuration that models. This is an Open Access article published by World Scientific Publishing Company. The surface pressure measurements were conducted to investigate the shock excursion of convex-corner flows. For the round convex-corner flows, a short region of convex surface curvature was presented and the total turning angles were the same as those of sharp convex corners. Before discussing results of the present study, brief details of the experiment are outlined
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