169
8 Appendix A
In the following charts is carried out the comparison between experimental and CFD swept wing model Cp. The simulation are performed for Re 30 Million, Mach 0.85 and CL 0.5 for η=0.131, 0.283, 0.502, 0.603, 0.727, 0.846. In some sections the integral of Cp derived from EFD and CFD analysis are very close such as the trend of Cp profile along upper and lower section. On other sections the values are more distant. This behavior can be due to many of the reason underlined in Chapter 4.3 and in addiction to errors in EFD data collecting caused by failure of CP sensors placed over the wing EFD model.
Figure 8-1 EFD and CFD Cp for Re 30 M Mach 0.85 η 0.131
Figure 8-2 EFD and CFD Cp for Re 30 M Mach 0.85 η 0.283 -1.2
-1 -0.8 -0.6 -0.4 -0.2 0 0.2 0.4 0.6 0.8 1
0.00 0.20 0.40 0.60 0.80 1.00
Cp
CFD CP Re 30 M Mach 0,85 CL 0,507
Ƞ 0,131
experimental CFD
-1.2 -1 -0.8 -0.6 -0.4 -0.2 0 0.2 0.4 0.6 0.8
0.00 0.20 0.40 0.60 0.80 1.00
Cp
CFD CP Re 30 M Mach 0,85 CL 0,507
Ƞ 0,283
experimental CFD
170
Figure 8-3 EFD and CFD Cp for Re 30 M Mach 0.85 η 0.502
Figure 8-4 EFD and CFD Cp for Re 30 M Mach 0.85 η 0.603 -1.2
-1 -0.8 -0.6 -0.4 -0.2 0 0.2 0.4 0.6 0.8 1
0.00 0.20 0.40 0.60 0.80 1.00
Cp
CFD CP Re 30 M Mach 0,85 CL 0,507
Ƞ 0,502
experiment alCFD
-1.2 -1 -0.8 -0.6 -0.4 -0.2 0 0.2 0.4 0.6 0.8
0.00 0.20 0.40 0.60 0.80 1.00
Cp
CFD CP Re 30 M Mach 0,85 CL 0,507
Ƞ 0,603
experiment al
CFD
171
Figure 8-5 EFD and CFD Cp for Re 30 M Mach 0.85 η 0.727
Figure 8-6 EFD and CFD Cp for Re 30 M Mach 0.85 η 0.846 -1.2
-1 -0.8 -0.6 -0.4 -0.2 0 0.2 0.4 0.6 0.8
0.00 0.20 0.40 0.60 0.80 1.00
Cp
CFD CP Re 30 M Mach 0,85 CL 0,507
Ƞ 0,727
experime ntal CFD
-1.2 -1 -0.8 -0.6 -0.4 -0.2 0 0.2 0.4 0.6 0.8
0.00 0.20 0.40 0.60 0.80 1.00
Cp
CFD CP Re 30 M Mach 0,85 CL 0,507
Ƞ 0,846
experiment al
CFD
