GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Reynolds number: 200,000 Max Cl/Cd: 78.33 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe330-il-200000.txt Download as CSV file: xf-goe330-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 330 (PFALZ 59) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2869 0.11586 0.11257 -0.0306 1.0000 0.0332
-9.250 -0.2952 0.11466 0.11142 -0.0281 1.0000 0.0337
-9.000 -0.3031 0.11336 0.11017 -0.0259 1.0000 0.0341
-8.750 -0.2927 0.11007 0.10689 -0.0286 0.9979 0.0351
-8.500 -0.2773 0.10628 0.10309 -0.0332 0.9949 0.0365
-8.250 -0.2652 0.10311 0.09992 -0.0398 0.9898 0.0381
-8.000 -0.2572 0.10051 0.09734 -0.0505 0.9818 0.0386
-7.750 -0.2423 0.09527 0.09211 -0.0564 0.9753 0.0390
-7.500 -0.2247 0.09109 0.08792 -0.0521 0.9754 0.0401
-7.250 -0.2034 0.08745 0.08426 -0.0556 0.9722 0.0416
-7.000 -0.1869 0.08397 0.08077 -0.0599 0.9654 0.0432
-6.750 -0.1625 0.07984 0.07662 -0.0677 0.9596 0.0456
-6.500 -0.1202 0.07472 0.07127 -0.0905 0.9476 0.0475
-6.250 -0.1085 0.06975 0.06640 -0.0875 0.9456 0.0484
-6.000 -0.0815 0.06638 0.06303 -0.0890 0.9436 0.0502
-5.750 -0.0562 0.06307 0.05967 -0.0931 0.9367 0.0531
-5.250 0.0269 0.05241 0.04864 -0.1130 0.9275 0.0592
-5.000 0.0419 0.05016 0.04639 -0.1123 0.9186 0.0606
-4.750 0.0747 0.04707 0.04320 -0.1160 0.9145 0.0641
-4.500 0.1124 0.04309 0.03866 -0.1221 0.9060 0.0703
-4.250 0.1369 0.03994 0.03558 -0.1231 0.9006 0.0717
-4.000 0.1684 0.03736 0.03293 -0.1251 0.8970 0.0745
-3.750 0.2015 0.03756 0.03235 -0.1258 0.8864 0.0821
-3.500 0.2255 0.03224 0.02722 -0.1275 0.8821 0.0846
-3.250 0.2458 0.03066 0.02563 -0.1267 0.8720 0.0881
-3.000 0.2789 0.02861 0.02315 -0.1280 0.8669 0.0980
-2.750 0.2999 0.02701 0.02156 -0.1273 0.8569 0.1013
-2.500 0.3307 0.02547 0.01968 -0.1279 0.8511 0.1133
-2.250 0.3552 0.02497 0.01903 -0.1271 0.8409 0.1241
-2.000 0.3805 0.02296 0.01699 -0.1272 0.8333 0.1337
-1.500 0.4439 0.01917 0.01207 -0.1253 0.8161 0.0792
-1.250 0.4740 0.01831 0.01073 -0.1244 0.8076 0.0697
-1.000 0.5000 0.01708 0.00939 -0.1238 0.7976 0.0685
-0.750 0.5293 0.01622 0.00834 -0.1236 0.7897 0.0685
-0.500 0.5548 0.01581 0.00782 -0.1227 0.7781 0.0695
-0.250 0.5806 0.01486 0.00689 -0.1222 0.7676 0.0728
0.000 0.6082 0.01432 0.00631 -0.1218 0.7582 0.0751
0.250 0.6337 0.01389 0.00587 -0.1211 0.7462 0.0781
0.500 0.6595 0.01357 0.00551 -0.1203 0.7337 0.0821
0.750 0.6848 0.01302 0.00502 -0.1197 0.7209 0.0915
1.000 0.7106 0.01259 0.00463 -0.1190 0.7075 0.1240
1.250 0.7519 0.01055 0.00450 -0.1219 0.6932 1.0000
1.500 0.7773 0.01064 0.00439 -0.1211 0.6778 1.0000
1.750 0.8023 0.01077 0.00433 -0.1203 0.6609 1.0000
2.000 0.8269 0.01095 0.00431 -0.1195 0.6429 1.0000
2.250 0.8513 0.01119 0.00435 -0.1186 0.6245 1.0000
2.500 0.8751 0.01144 0.00444 -0.1177 0.6057 1.0000
2.750 0.8984 0.01169 0.00458 -0.1167 0.5865 1.0000
3.000 0.9218 0.01194 0.00471 -0.1158 0.5680 1.0000
3.250 0.9451 0.01219 0.00485 -0.1149 0.5505 1.0000
3.500 0.9684 0.01244 0.00500 -0.1140 0.5341 1.0000
3.750 0.9917 0.01270 0.00516 -0.1131 0.5189 1.0000
4.000 1.0151 0.01297 0.00534 -0.1123 0.5050 1.0000
4.250 1.0386 0.01326 0.00555 -0.1115 0.4926 1.0000
4.500 1.0623 0.01358 0.00579 -0.1108 0.4818 1.0000
4.750 1.0860 0.01392 0.00604 -0.1101 0.4716 1.0000
5.000 1.1098 0.01424 0.00633 -0.1094 0.4617 1.0000
5.250 1.1340 0.01463 0.00664 -0.1089 0.4532 1.0000
5.500 1.1579 0.01495 0.00699 -0.1083 0.4449 1.0000
5.750 1.1827 0.01537 0.00734 -0.1079 0.4379 1.0000
6.000 1.2065 0.01570 0.00772 -0.1073 0.4303 1.0000
6.250 1.2318 0.01616 0.00811 -0.1070 0.4238 1.0000
6.500 1.2549 0.01648 0.00855 -0.1063 0.4165 1.0000
6.750 1.2794 0.01692 0.00894 -0.1058 0.4095 1.0000
7.000 1.3007 0.01724 0.00935 -0.1048 0.4001 1.0000
7.250 1.3212 0.01759 0.00972 -0.1036 0.3891 1.0000
7.500 1.3411 0.01794 0.01004 -0.1024 0.3778 1.0000
7.750 1.3591 0.01818 0.01040 -0.1007 0.3662 1.0000
8.000 1.3774 0.01849 0.01078 -0.0992 0.3549 1.0000
8.250 1.3950 0.01882 0.01116 -0.0976 0.3436 1.0000
8.500 1.4105 0.01916 0.01153 -0.0956 0.3303 1.0000
8.750 1.4250 0.01952 0.01195 -0.0934 0.3161 1.0000
9.000 1.4369 0.01989 0.01239 -0.0909 0.2987 1.0000
9.250 1.4453 0.02043 0.01294 -0.0878 0.2743 1.0000
9.500 1.4510 0.02128 0.01366 -0.0846 0.2398 1.0000
9.750 1.4500 0.02271 0.01481 -0.0808 0.1960 1.0000
10.000 1.4446 0.02467 0.01646 -0.0768 0.1574 1.0000
10.250 1.4332 0.02726 0.01859 -0.0726 0.0854 1.0000
10.500 1.4165 0.03044 0.02144 -0.0683 0.0465 1.0000
10.750 1.4162 0.03252 0.02354 -0.0658 0.0395 1.0000
11.000 1.4167 0.03462 0.02574 -0.0636 0.0363 1.0000
11.250 1.4151 0.03699 0.02826 -0.0615 0.0343 1.0000
11.500 1.4166 0.03917 0.03063 -0.0598 0.0333 1.0000
11.750 1.4153 0.04168 0.03331 -0.0582 0.0323 1.0000
12.000 1.4119 0.04451 0.03631 -0.0568 0.0315 1.0000
12.250 1.4066 0.04767 0.03962 -0.0557 0.0307 1.0000
12.500 1.3996 0.05117 0.04325 -0.0548 0.0300 1.0000
12.750 1.3912 0.05502 0.04722 -0.0543 0.0293 1.0000
13.000 1.3814 0.05916 0.05147 -0.0539 0.0287 1.0000
13.250 1.3710 0.06347 0.05588 -0.0537 0.0281 1.0000
13.500 1.3610 0.06771 0.06019 -0.0534 0.0276 1.0000
13.750 1.3545 0.07135 0.06388 -0.0527 0.0271 1.0000
14.000 1.3555 0.07426 0.06688 -0.0522 0.0268 1.0000
14.250 1.3578 0.07694 0.06966 -0.0517 0.0265 1.0000
14.500 1.3618 0.07930 0.07209 -0.0508 0.0261 1.0000
14.750 1.3680 0.08131 0.07418 -0.0498 0.0258 1.0000
15.000 1.3760 0.08304 0.07598 -0.0485 0.0254 1.0000
15.250 1.3843 0.08483 0.07785 -0.0474 0.0250 1.0000
15.500 1.3913 0.08690 0.08001 -0.0465 0.0243 1.0000
15.750 1.3979 0.08905 0.08225 -0.0458 0.0237 1.0000
16.000 1.4064 0.09092 0.08420 -0.0448 0.0232 1.0000
16.250 1.4150 0.09291 0.08632 -0.0437 0.0230 1.0000
16.500 1.4209 0.09543 0.08899 -0.0430 0.0229 1.0000
16.750 1.4233 0.09858 0.09234 -0.0427 0.0230 1.0000
17.000 1.4209 0.10250 0.09650 -0.0431 0.0232 1.0000
17.250 1.4146 0.10709 0.10135 -0.0440 0.0235 1.0000
17.500 1.4055 0.11223 0.10675 -0.0455 0.0239 1.0000
17.750 1.3948 0.11778 0.11256 -0.0475 0.0243 1.0000
18.000 1.3828 0.12370 0.11872 -0.0499 0.0248 1.0000
18.250 1.3701 0.12990 0.12514 -0.0528 0.0253 1.0000
18.500 1.3571 0.13633 0.13177 -0.0560 0.0257 1.0000
18.750 1.3442 0.14292 0.13854 -0.0593 0.0263 1.0000
19.000 1.3570 0.14498 0.14068 -0.0581 0.0276 1.0000
19.250 1.3353 0.15355 0.14951 -0.0650 0.0283 1.0000
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