问题描述：
英语翻译
内容如下,
The differences between results obtained with the full potential equation and those obtained with the small-perturbation potential equation are graphically illustrated in Fig.14.9,which shows data calculated by Keyfitz et al.(Ref.106).Here,the pressure coefficient distributions over the top and bottom surfaces of a joukowski airfoil are shown;only the leading-edge region is shown,where 0＜x/c＜0.1(Note that,in contrast to the usual aerodynamic convention,in Fig.14.9positive values of CP are plotted in the upper quadrant.)As described earlier,it is this leading-edge region of the airfoil where the assumption of small perturbations is least accurate.In Fig.14.9,TSD stands for transonic small disturbance(solution of the small-perturbation potential equation as discussed in Sec.14.4),and FPE stands for full potential equation (solution of the full velocity potential equation as discussed in the present section).Also,the solid line in Fig.14.9 represents an analytical solution to the small-perturbation potential equation in the leading-edge region,as reported in Ref.106; this analytical solution agrees well with the TSD numerical solution.Howevr,the primary message conveyed by Fig.14.9 is that the more accurate FPE solution is quite different from the TSD solution in the leading-edge region;note that,for the most part.the TSDsolution underpredicts the pressure,and shows a more rapid rise in pressure as theleading edge is approached.T should be noted that Keyfitz et al.examined the effect ofmesh size on the results,and found that the TSD results in the nose region were very sensitive to the fineness of the grid in that region.The results shown in Fig.14.9 were obtained with a mesh fine enough such that the results are relatively grid-independent.
内容如下,
The differences between results obtained with the full potential equation and those obtained with the small-perturbation potential equation are graphically illustrated in Fig.14.9,which shows data calculated by Keyfitz et al.(Ref.106).Here,the pressure coefficient distributions over the top and bottom surfaces of a joukowski airfoil are shown;only the leading-edge region is shown,where 0＜x/c＜0.1(Note that,in contrast to the usual aerodynamic convention,in Fig.14.9positive values of CP are plotted in the upper quadrant.)As described earlier,it is this leading-edge region of the airfoil where the assumption of small perturbations is least accurate.In Fig.14.9,TSD stands for transonic small disturbance(solution of the small-perturbation potential equation as discussed in Sec.14.4),and FPE stands for full potential equation (solution of the full velocity potential equation as discussed in the present section).Also,the solid line in Fig.14.9 represents an analytical solution to the small-perturbation potential equation in the leading-edge region,as reported in Ref.106; this analytical solution agrees well with the TSD numerical solution.Howevr,the primary message conveyed by Fig.14.9 is that the more accurate FPE solution is quite different from the TSD solution in the leading-edge region;note that,for the most part.the TSDsolution underpredicts the pressure,and shows a more rapid rise in pressure as theleading edge is approached.T should be noted that Keyfitz et al.examined the effect ofmesh size on the results,and found that the TSD results in the nose region were very sensitive to the fineness of the grid in that region.The results shown in Fig.14.9 were obtained with a mesh fine enough such that the results are relatively grid-independent.
问题解答：
我来补答展开全文阅读