GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Reynolds number: 500,000 Max Cl/Cd: 94.07 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe331-il-500000-n5.txt Download as CSV file: xf-goe331-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 331 (PFALZ 60) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1129 0.10648 0.10392 -0.0656 0.8998 0.0162
-10.000 -0.1066 0.10408 0.10141 -0.0660 0.8754 0.0165
-9.750 -0.0997 0.10161 0.09884 -0.0665 0.8549 0.0169
-9.500 -0.0923 0.09901 0.09614 -0.0675 0.8396 0.0175
-9.250 -0.0847 0.09623 0.09328 -0.0689 0.8277 0.0178
-8.750 -0.0700 0.09047 0.08742 -0.0729 0.8097 0.0180
-8.500 -0.0624 0.08763 0.08453 -0.0749 0.8024 0.0181
-8.250 -0.0530 0.08488 0.08176 -0.0760 0.7965 0.0181
-8.000 -0.0429 0.08237 0.07924 -0.0769 0.7906 0.0183
-7.750 -0.0330 0.07995 0.07680 -0.0783 0.7846 0.0184
-7.500 -0.0232 0.07755 0.07438 -0.0799 0.7787 0.0187
-7.250 -0.0116 0.07503 0.07184 -0.0824 0.7723 0.0190
-7.000 0.0029 0.07231 0.06908 -0.0855 0.7660 0.0195
-6.750 0.0207 0.06914 0.06588 -0.0902 0.7602 0.0203
-6.500 0.0415 0.06569 0.06238 -0.0959 0.7539 0.0205
-6.250 0.0650 0.06212 0.05873 -0.1021 0.7485 0.0205
-6.000 0.0911 0.05845 0.05498 -0.1082 0.7435 0.0206
-5.750 0.1103 0.05561 0.05212 -0.1102 0.7378 0.0206
-5.500 0.1282 0.05328 0.04974 -0.1113 0.7320 0.0208
-5.250 0.1496 0.05096 0.04737 -0.1134 0.7268 0.0211
-5.000 0.1740 0.04851 0.04487 -0.1161 0.7210 0.0215
-4.750 0.2002 0.04592 0.04219 -0.1191 0.7153 0.0220
-4.500 0.2287 0.04321 0.03937 -0.1222 0.7100 0.0227
-4.250 0.2644 0.04002 0.03599 -0.1263 0.7042 0.0232
-4.000 0.2967 0.03715 0.03291 -0.1290 0.6981 0.0233
-3.750 0.3226 0.03472 0.03037 -0.1303 0.6921 0.0234
-3.500 0.3453 0.03297 0.02857 -0.1311 0.6850 0.0236
-3.000 0.3974 0.02958 0.02497 -0.1328 0.6705 0.0241
-2.750 0.4248 0.02795 0.02319 -0.1336 0.6629 0.0246
-2.500 0.4533 0.02631 0.02141 -0.1342 0.6553 0.0253
-2.250 0.4868 0.02445 0.01919 -0.1344 0.6464 0.0263
-2.000 0.5165 0.02288 0.01732 -0.1344 0.6363 0.0264
-1.750 0.5405 0.02146 0.01585 -0.1348 0.6248 0.0266
-1.500 0.5659 0.02049 0.01478 -0.1350 0.6127 0.0270
-1.250 0.5930 0.01952 0.01368 -0.1351 0.6021 0.0274
-1.000 0.6202 0.01859 0.01257 -0.1351 0.5913 0.0279
-0.500 0.6777 0.01710 0.01039 -0.1341 0.5663 0.0298
-0.250 0.7030 0.01599 0.00923 -0.1341 0.5518 0.0302
0.000 0.7287 0.01543 0.00857 -0.1339 0.5367 0.0306
0.250 0.7547 0.01498 0.00798 -0.1336 0.5219 0.0313
0.500 0.7815 0.01467 0.00738 -0.1331 0.5072 0.0341
0.750 0.8066 0.01426 0.00692 -0.1329 0.4908 0.0352
1.000 0.8321 0.01401 0.00652 -0.1324 0.4721 0.0364
1.250 0.8571 0.01375 0.00607 -0.1318 0.4496 0.0360
1.500 0.8822 0.01321 0.00518 -0.1306 0.4228 0.0267
1.750 0.9049 0.01325 0.00503 -0.1298 0.3916 0.0268
2.000 0.9280 0.01330 0.00494 -0.1290 0.3676 0.0270
2.250 0.9519 0.01333 0.00488 -0.1283 0.3522 0.0273
2.500 0.9764 0.01336 0.00484 -0.1278 0.3417 0.0277
2.750 1.0010 0.01343 0.00486 -0.1273 0.3330 0.0287
3.000 1.0258 0.01348 0.00487 -0.1268 0.3265 0.0292
3.250 1.0509 0.01352 0.00488 -0.1264 0.3206 0.0293
3.500 1.0753 0.01361 0.00495 -0.1259 0.3151 0.0295
3.750 1.1001 0.01371 0.00504 -0.1254 0.3108 0.0298
4.000 1.1252 0.01374 0.00510 -0.1251 0.3066 0.0304
4.250 1.1496 0.01386 0.00523 -0.1246 0.3022 0.0311
4.500 1.1732 0.01405 0.00541 -0.1240 0.2979 0.0325
4.750 1.1972 0.01422 0.00558 -0.1234 0.2945 0.0339
5.000 1.2217 0.01435 0.00572 -0.1229 0.2917 0.0348
5.250 1.2456 0.01452 0.00590 -0.1224 0.2887 0.0361
5.500 1.2688 0.01472 0.00611 -0.1217 0.2857 0.0378
5.750 1.2913 0.01496 0.00635 -0.1209 0.2827 0.0426
6.000 1.3114 0.01394 0.00687 -0.1199 0.2800 1.0000
6.250 1.3337 0.01420 0.00712 -0.1191 0.2774 1.0000
6.500 1.3556 0.01442 0.00736 -0.1181 0.2748 1.0000
6.750 1.3767 0.01469 0.00763 -0.1171 0.2713 1.0000
7.000 1.3969 0.01500 0.00793 -0.1160 0.2676 1.0000
7.250 1.4163 0.01536 0.00828 -0.1147 0.2642 1.0000
7.500 1.4357 0.01572 0.00864 -0.1135 0.2616 1.0000
7.750 1.4568 0.01601 0.00898 -0.1126 0.2599 1.0000
8.000 1.4774 0.01633 0.00934 -0.1116 0.2578 1.0000
8.250 1.4974 0.01668 0.00972 -0.1106 0.2553 1.0000
8.500 1.5168 0.01706 0.01014 -0.1094 0.2525 1.0000
8.750 1.5352 0.01750 0.01059 -0.1082 0.2497 1.0000
9.000 1.5526 0.01799 0.01110 -0.1069 0.2469 1.0000
9.250 1.5713 0.01843 0.01158 -0.1058 0.2445 1.0000
9.500 1.5907 0.01883 0.01205 -0.1049 0.2414 1.0000
9.750 1.6090 0.01930 0.01256 -0.1038 0.2372 1.0000
10.000 1.6252 0.01988 0.01315 -0.1024 0.2328 1.0000
10.250 1.6413 0.02049 0.01379 -0.1012 0.2289 1.0000
10.500 1.6594 0.02100 0.01437 -0.1002 0.2246 1.0000
10.750 1.6756 0.02162 0.01503 -0.0990 0.2202 1.0000
11.000 1.6896 0.02241 0.01583 -0.0976 0.2157 1.0000
11.250 1.7057 0.02307 0.01656 -0.0965 0.2104 1.0000
11.500 1.7179 0.02401 0.01749 -0.0951 0.2013 1.0000
11.750 1.7305 0.02496 0.01844 -0.0938 0.1907 1.0000
12.000 1.7404 0.02613 0.01960 -0.0923 0.1793 1.0000
12.250 1.7477 0.02753 0.02096 -0.0906 0.1651 1.0000
12.500 1.7506 0.02931 0.02266 -0.0886 0.1478 1.0000
12.750 1.7504 0.03138 0.02465 -0.0865 0.1314 1.0000
13.000 1.7503 0.03351 0.02674 -0.0846 0.1186 1.0000
13.500 1.7508 0.03788 0.03110 -0.0812 0.0980 1.0000
13.750 1.7498 0.04029 0.03350 -0.0796 0.0863 1.0000
14.000 1.7349 0.04411 0.03720 -0.0775 0.0643 1.0000
14.250 1.7223 0.04790 0.04094 -0.0758 0.0499 1.0000
14.500 1.7122 0.05161 0.04466 -0.0746 0.0405 1.0000
14.750 1.7034 0.05532 0.04841 -0.0736 0.0337 1.0000
15.000 1.6958 0.05903 0.05217 -0.0729 0.0286 1.0000
15.250 1.6890 0.06278 0.05600 -0.0725 0.0251 1.0000
15.500 1.6818 0.06670 0.05999 -0.0722 0.0226 1.0000
15.750 1.6751 0.07062 0.06401 -0.0721 0.0209 1.0000
16.000 1.6667 0.07489 0.06838 -0.0722 0.0196 1.0000
16.250 1.6583 0.07925 0.07285 -0.0725 0.0187 1.0000
16.500 1.6496 0.08376 0.07748 -0.0729 0.0179 1.0000
16.750 1.6393 0.08853 0.08237 -0.0735 0.0173 1.0000
17.000 1.6276 0.09360 0.08755 -0.0743 0.0167 1.0000
17.250 1.6147 0.09896 0.09303 -0.0753 0.0162 1.0000
17.500 1.6004 0.10464 0.09883 -0.0766 0.0158 1.0000
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Polar data table (+)
Polar graphs
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