By J. H. Whitelaw (auth.), Dr. Tuncer Cebeci (eds.)
This quantity incorporates a number of the papers offered on the Fourth Symposium on Numerical and actual points of Aerodynamic Flows, which was once held on the California kingdom college, lengthy seashore, from 16-19 January 1989. It comprises the Stewartson Memorial Lecture of Professor J. H. Whitelaw, and is split into 3 elements. the 1st is a suite of papers that describe the prestige of present expertise in - and 3-dimensional regular flows, the second one bargains with - and 3-dimensional unsteady flows, and the papers within the 3rd handle balance and transition. all the 3 elements starts off with an outline of present learn, as defined within the following chapters. the person papers are edited models of the chosen papers initially submitted to the symposium. 4 years have handed because the 3rd Symposium, and likely traits be come transparent if one compares the papers contained during this quantity with these of prior volumes. There are extra 3- than two-dimensional difficulties consid ered partly 1 and the latter handle more challenging difficulties than some time past, for instance, the extension to raised angles of assault, to transonic stream, to best part ice accretion, and to thick hydrofoils. the massive variety of papers within the first half displays the emphasis of present learn and improvement and the desires of industry.
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Additional info for Numerical and Physical Aspects of Aerodynamic Flows IV
This time increment is chosen such that the effect of ice buildup on airfoil flowfield, and thus droplet trajectory paths, is thought td be minimal. Once the ice shape is calculated, then a viscous flowfield calculation is performed using the predicted ice shape if aerodynamic performance degradation levels are required. If it is desired to continue to computationally accrete ice on the airfoil, then the looping process is repeated for as many time increments as is required to reach the overall icing encounter time.
26 ______ _ Fig. 9. Comparison of calculated and measured heat transfer coefficients on smooth surface "iced" cylinder model Fig. 10. Comparison of calculated and measured heat transfer coefficients on rough surface "iced" cylinder model ,, f\ --()-- EXPERIMENTAL PREDICTED I I I I I I I I I I I I \ I I I I \ ' .. _ .... comparison of this rough surface heat transfer is shown in Fig. 10. The same general remarks can be made as were already made for the smooth surface ice shape. Also a comparison of Figs.
Kutta condition. In the trailing edge a "viscous" Kutta condition is applied, which demands continuity of the pressure on both sides of the airfoil surface p(x = XTel, y = 0) = p(x = XTeu, y = 0). Since the pressure is assumed constant through the shear layer it follows that (poheu = (po)rel. (uahe =0 Compressibility. To incorporate the effects of compressibility, a PrandtlGlauert transformation is applied to the equations above. This is easily accomplished by replacing the vertical velocity v (and its symmetric and antisymmetric parts) according to v v --+ (1 - M~)t/2 Details of the formulation of the interaction law can be foun
Numerical and Physical Aspects of Aerodynamic Flows IV by J. H. Whitelaw (auth.), Dr. Tuncer Cebeci (eds.)