S7012 8.75% (s7012-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: S7012 8.75% (s7012-il) Reynolds number: 500,000 Max Cl/Cd: 94.12 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s7012-il-500000.txt Download as CSV file: xf-s7012-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S7012 8.75%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4693 0.08323 0.08102 -0.0211 1.0000 0.0178
-8.250 -0.4702 0.07923 0.07705 -0.0232 1.0000 0.0182
-8.000 -0.4736 0.07510 0.07297 -0.0254 1.0000 0.0185
-7.750 -0.4809 0.07091 0.06883 -0.0279 1.0000 0.0187
-7.500 -0.4839 0.06452 0.06244 -0.0354 1.0000 0.0188
-7.250 -0.4837 0.05862 0.05648 -0.0400 1.0000 0.0190
-7.000 -0.4810 0.05302 0.05075 -0.0430 1.0000 0.0197
-6.750 -0.4742 0.04781 0.04536 -0.0446 1.0000 0.0206
-6.500 -0.4580 0.04507 0.04232 -0.0445 1.0000 0.0220
-6.250 -0.4485 0.04196 0.03895 -0.0439 1.0000 0.0221
-6.000 -0.4515 0.03370 0.03023 -0.0440 1.0000 0.0231
-5.750 -0.4390 0.03082 0.02726 -0.0432 1.0000 0.0239
-5.500 -0.4209 0.02887 0.02521 -0.0428 0.9996 0.0248
-5.250 -0.3855 0.02632 0.02242 -0.0456 0.9967 0.0268
-5.000 -0.3481 0.02401 0.01977 -0.0480 0.9939 0.0296
-4.750 -0.3121 0.01624 0.01092 -0.0479 0.9907 0.0142
-4.500 -0.2764 0.01418 0.00858 -0.0494 0.9871 0.0141
-4.250 -0.2389 0.01285 0.00710 -0.0513 0.9840 0.0144
-4.000 -0.2045 0.01195 0.00610 -0.0526 0.9786 0.0149
-3.750 -0.1684 0.01066 0.00472 -0.0545 0.9738 0.0163
-3.500 -0.1298 0.00989 0.00389 -0.0567 0.9700 0.0173
-3.250 -0.0960 0.00936 0.00328 -0.0578 0.9610 0.0185
-3.000 -0.0604 0.00893 0.00277 -0.0593 0.9523 0.0216
-2.750 -0.0268 0.00789 0.00219 -0.0607 0.9410 0.1365
-2.500 0.0036 0.00723 0.00195 -0.0616 0.9255 0.2610
-2.250 0.0316 0.00655 0.00178 -0.0619 0.9066 0.4189
-2.000 0.0579 0.00599 0.00169 -0.0616 0.8863 0.5710
-1.750 0.0834 0.00580 0.00170 -0.0608 0.8642 0.6714
-1.500 0.1096 0.00578 0.00165 -0.0601 0.8420 0.7076
-1.250 0.1357 0.00579 0.00161 -0.0594 0.8191 0.7360
-1.000 0.1619 0.00583 0.00158 -0.0587 0.7967 0.7598
-0.750 0.1879 0.00587 0.00155 -0.0581 0.7743 0.7791
-0.500 0.2140 0.00592 0.00153 -0.0574 0.7522 0.7975
0.000 0.2659 0.00603 0.00151 -0.0562 0.7091 0.8325
0.250 0.2914 0.00608 0.00151 -0.0554 0.6886 0.8499
0.500 0.3167 0.00613 0.00152 -0.0547 0.6686 0.8682
0.750 0.3415 0.00617 0.00153 -0.0538 0.6496 0.8878
1.000 0.3650 0.00621 0.00154 -0.0526 0.6320 0.9103
1.250 0.3884 0.00622 0.00154 -0.0513 0.6147 0.9391
1.500 0.4205 0.00625 0.00153 -0.0521 0.5963 0.9738
1.750 0.4543 0.00635 0.00154 -0.0534 0.5782 1.0000
2.000 0.4823 0.00649 0.00159 -0.0536 0.5620 1.0000
2.250 0.5101 0.00664 0.00165 -0.0536 0.5465 1.0000
2.500 0.5380 0.00677 0.00174 -0.0537 0.5311 1.0000
2.750 0.5657 0.00691 0.00183 -0.0537 0.5159 1.0000
3.000 0.5933 0.00706 0.00192 -0.0537 0.4999 1.0000
3.250 0.6209 0.00721 0.00203 -0.0537 0.4840 1.0000
3.500 0.6484 0.00737 0.00217 -0.0536 0.4685 1.0000
3.750 0.6758 0.00753 0.00230 -0.0536 0.4525 1.0000
4.000 0.7030 0.00771 0.00244 -0.0535 0.4355 1.0000
4.250 0.7301 0.00790 0.00259 -0.0534 0.4152 1.0000
4.500 0.7571 0.00811 0.00277 -0.0533 0.3945 1.0000
4.750 0.7839 0.00833 0.00295 -0.0531 0.3718 1.0000
5.000 0.8104 0.00861 0.00316 -0.0530 0.3452 1.0000
5.250 0.8356 0.00903 0.00340 -0.0527 0.3014 1.0000
5.500 0.8601 0.00958 0.00373 -0.0523 0.2504 1.0000
5.750 0.8848 0.01011 0.00408 -0.0520 0.2093 1.0000
6.000 0.9094 0.01066 0.00447 -0.0517 0.1714 1.0000
6.500 0.9570 0.01200 0.00545 -0.0509 0.0930 1.0000
6.750 0.9789 0.01295 0.00613 -0.0502 0.0475 1.0000
7.000 0.9986 0.01431 0.00728 -0.0491 0.0153 1.0000
7.250 1.0227 0.01492 0.00797 -0.0485 0.0130 1.0000
7.500 1.0454 0.01571 0.00884 -0.0478 0.0115 1.0000
7.750 1.0643 0.01706 0.01034 -0.0465 0.0104 1.0000
8.000 1.0860 0.01791 0.01129 -0.0457 0.0101 1.0000
8.250 1.1063 0.01893 0.01245 -0.0446 0.0097 1.0000
8.500 1.1251 0.02012 0.01377 -0.0434 0.0093 1.0000
8.750 1.1428 0.02145 0.01523 -0.0420 0.0090 1.0000
9.000 1.1595 0.02295 0.01686 -0.0406 0.0089 1.0000
9.250 1.1754 0.02467 0.01874 -0.0390 0.0088 1.0000
9.500 1.1904 0.02666 0.02092 -0.0374 0.0089 1.0000
9.750 1.2043 0.02899 0.02346 -0.0358 0.0090 1.0000
10.000 1.2170 0.03141 0.02612 -0.0341 0.0090 1.0000
10.250 1.2280 0.03371 0.02867 -0.0324 0.0089 1.0000
10.500 1.2362 0.03605 0.03124 -0.0305 0.0088 1.0000
10.750 1.2397 0.03864 0.03408 -0.0283 0.0087 1.0000
11.000 1.2343 0.04147 0.03717 -0.0252 0.0088 1.0000
11.250 1.2222 0.04479 0.04076 -0.0221 0.0089 1.0000
11.500 1.2093 0.04817 0.04438 -0.0201 0.0090 1.0000
11.750 1.1919 0.05248 0.04893 -0.0192 0.0093 1.0000
12.000 1.1744 0.05719 0.05386 -0.0197 0.0094 1.0000
12.250 1.1571 0.06240 0.05926 -0.0214 0.0095 1.0000
12.500 1.1392 0.06826 0.06530 -0.0241 0.0095 1.0000
12.750 1.1207 0.07483 0.07204 -0.0279 0.0096 1.0000
13.000 1.1015 0.08217 0.07954 -0.0326 0.0097 1.0000
13.250 1.0765 0.09137 0.08890 -0.0386 0.0099 1.0000
13.500 1.0584 0.09990 0.09756 -0.0445 0.0099 1.0000
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Polar data table (+)
Polar graphs
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