Page 212 - Computational Fluid Dynamics for Engineers

200 6. Inviscid Flow Equations for Incompressible Flows

0.00 n

-0.02+

-0.03 +

-0.04+

-0.05-1 H 1 1 1 I -I 1-
0 2 4 6 8 10 12 14 16 1B 20
a
Fig. 6.11. Variation of the moment coefficient c m with angle of attack, a for the NACA
0012 airfoil.

Fig. 6.12. Distribution of the pressure coefficients around a circular cylinder for four
values of 7.

revised computer program and contains the modifications required to each sub-
routine (except GAUSS and CLCM) of the panel program and to its MAIN
program.
Figure 6.12 shows the computed pressure coefficients around the circular
cylinder for values of r (GAMMA) equal to 0, 1, 2 and 3. These results are in
excellent agreement with the analytical solution with

v r (6.6.3)
— = 2 s i n 0 + —
r
Voo 27rV 00ro
obtained from inviscid flow theory as described, for example, in Anderson [2].