GOE 422 AIRFOIL (goe422-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 422 AIRFOIL (goe422-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.84 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe422-il-1000000-n5.txt Download as CSV file: xf-goe422-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 422 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.6758 0.03260 0.02903 -0.1478 0.8737 0.0231
-14.000 -0.6819 0.02913 0.02523 -0.1509 0.8410 0.0231
-13.750 -0.6796 0.02737 0.02325 -0.1506 0.8251 0.0231
-13.500 -0.6682 0.02594 0.02165 -0.1506 0.8152 0.0232
-13.250 -0.6536 0.02473 0.02029 -0.1504 0.8077 0.0233
-13.000 -0.6366 0.02366 0.01909 -0.1502 0.8012 0.0234
-12.750 -0.6181 0.02272 0.01801 -0.1499 0.7950 0.0234
-12.500 -0.5983 0.02187 0.01704 -0.1496 0.7896 0.0235
-12.250 -0.5770 0.02107 0.01615 -0.1494 0.7852 0.0235
-12.000 -0.5551 0.02035 0.01533 -0.1491 0.7803 0.0236
-11.750 -0.5325 0.01969 0.01457 -0.1488 0.7753 0.0237
-11.500 -0.5095 0.01910 0.01387 -0.1485 0.7699 0.0237
-11.250 -0.4879 0.01820 0.01288 -0.1482 0.7659 0.0239
-11.000 -0.4648 0.01750 0.01210 -0.1479 0.7611 0.0240
-10.750 -0.4407 0.01692 0.01145 -0.1476 0.7564 0.0242
-10.500 -0.4162 0.01641 0.01087 -0.1474 0.7519 0.0243
-10.250 -0.3909 0.01595 0.01036 -0.1472 0.7481 0.0244
-10.000 -0.3650 0.01552 0.00987 -0.1470 0.7445 0.0246
-9.750 -0.3389 0.01512 0.00943 -0.1469 0.7404 0.0247
-9.500 -0.3127 0.01475 0.00900 -0.1467 0.7362 0.0249
-9.250 -0.2866 0.01441 0.00859 -0.1465 0.7319 0.0250
-9.000 -0.2600 0.01407 0.00820 -0.1463 0.7281 0.0252
-8.750 -0.2330 0.01374 0.00784 -0.1463 0.7244 0.0254
-8.500 -0.2060 0.01343 0.00749 -0.1462 0.7204 0.0256
-8.250 -0.1790 0.01315 0.00715 -0.1460 0.7159 0.0258
-8.000 -0.1522 0.01289 0.00684 -0.1458 0.7112 0.0261
-7.750 -0.1248 0.01261 0.00652 -0.1458 0.7074 0.0263
-7.500 -0.0973 0.01234 0.00621 -0.1457 0.7034 0.0265
-7.250 -0.0700 0.01209 0.00591 -0.1456 0.6987 0.0267
-7.000 -0.0428 0.01187 0.00563 -0.1454 0.6936 0.0268
-6.750 -0.0153 0.01166 0.00538 -0.1453 0.6892 0.0270
-6.500 0.0125 0.01145 0.00514 -0.1453 0.6847 0.0271
-6.250 0.0399 0.01122 0.00486 -0.1452 0.6796 0.0274
-6.000 0.0667 0.01098 0.00458 -0.1449 0.6739 0.0277
-5.750 0.0943 0.01078 0.00435 -0.1448 0.6677 0.0280
-5.500 0.1216 0.01062 0.00415 -0.1447 0.6597 0.0283
-5.250 0.1487 0.01049 0.00398 -0.1444 0.6516 0.0287
-5.000 0.1759 0.01036 0.00381 -0.1443 0.6415 0.0290
-4.750 0.2028 0.01027 0.00366 -0.1440 0.6315 0.0294
-4.500 0.2297 0.01019 0.00352 -0.1437 0.6206 0.0298
-4.250 0.2571 0.01010 0.00339 -0.1436 0.6130 0.0303
-4.000 0.2847 0.01001 0.00327 -0.1434 0.6053 0.0307
-3.750 0.3116 0.00995 0.00317 -0.1432 0.5973 0.0311
-3.500 0.3389 0.00985 0.00304 -0.1430 0.5885 0.0318
-3.250 0.3655 0.00981 0.00296 -0.1427 0.5792 0.0326
-3.000 0.3928 0.00976 0.00288 -0.1426 0.5705 0.0335
-2.500 0.4469 0.00970 0.00276 -0.1421 0.5549 0.0356
-2.250 0.4736 0.00968 0.00272 -0.1419 0.5467 0.0373
-2.000 0.5006 0.00967 0.00268 -0.1416 0.5394 0.0392
-1.750 0.5274 0.00965 0.00265 -0.1414 0.5309 0.0425
-1.500 0.5536 0.00966 0.00264 -0.1411 0.5226 0.0475
-1.250 0.5803 0.00965 0.00263 -0.1408 0.5137 0.0550
-1.000 0.6059 0.00968 0.00265 -0.1404 0.5034 0.0650
-0.750 0.6320 0.00971 0.00269 -0.1400 0.4931 0.0755
-0.500 0.6579 0.00977 0.00273 -0.1397 0.4846 0.0841
-0.250 0.6844 0.00981 0.00277 -0.1394 0.4769 0.0904
0.000 0.7098 0.00990 0.00282 -0.1389 0.4686 0.0951
0.250 0.7361 0.00995 0.00286 -0.1386 0.4600 0.0996
0.500 0.7607 0.01008 0.00293 -0.1380 0.4493 0.1033
0.750 0.7857 0.01016 0.00300 -0.1375 0.4381 0.1097
1.000 0.8098 0.01028 0.00308 -0.1368 0.4264 0.1180
1.250 0.8329 0.01042 0.00319 -0.1360 0.4126 0.1312
1.500 0.8562 0.01040 0.00332 -0.1353 0.4000 0.2064
1.750 0.8790 0.01044 0.00345 -0.1345 0.3902 0.2636
2.000 0.9003 0.01054 0.00360 -0.1333 0.3797 0.3034
2.250 0.9231 0.01061 0.00374 -0.1325 0.3710 0.3483
2.500 0.9448 0.01071 0.00393 -0.1315 0.3615 0.4094
2.750 0.9692 0.01066 0.00413 -0.1312 0.3541 0.5245
3.000 0.9924 0.01053 0.00444 -0.1306 0.3458 0.7160
3.250 1.0156 0.01065 0.00466 -0.1298 0.3396 0.7770
3.500 1.0386 0.01082 0.00486 -0.1290 0.3331 0.8021
3.750 1.0600 0.01103 0.00510 -0.1280 0.3259 0.8305
4.000 1.0823 0.01095 0.00530 -0.1268 0.3208 1.0000
4.250 1.1043 0.01121 0.00553 -0.1259 0.3145 1.0000
4.500 1.1254 0.01153 0.00578 -0.1249 0.3083 1.0000
4.750 1.1486 0.01176 0.00599 -0.1243 0.3042 1.0000
5.000 1.1707 0.01203 0.00623 -0.1234 0.2992 1.0000
5.250 1.1917 0.01235 0.00652 -0.1225 0.2942 1.0000
5.500 1.2133 0.01266 0.00680 -0.1216 0.2899 1.0000
5.750 1.2359 0.01293 0.00705 -0.1209 0.2864 1.0000
6.000 1.2564 0.01328 0.00737 -0.1199 0.2803 1.0000
6.250 1.2756 0.01371 0.00775 -0.1188 0.2742 1.0000
6.500 1.2972 0.01402 0.00806 -0.1180 0.2701 1.0000
6.750 1.3171 0.01443 0.00844 -0.1170 0.2639 1.0000
7.000 1.3352 0.01492 0.00888 -0.1158 0.2575 1.0000
7.250 1.3546 0.01535 0.00930 -0.1148 0.2504 1.0000
7.500 1.3706 0.01597 0.00985 -0.1133 0.2410 1.0000
7.750 1.3847 0.01670 0.01051 -0.1116 0.2277 1.0000
8.000 1.3775 0.01863 0.01214 -0.1072 0.1800 1.0000
8.250 1.3515 0.02189 0.01501 -0.1008 0.1120 1.0000
8.500 1.3545 0.02352 0.01652 -0.0983 0.0899 1.0000
8.750 1.3666 0.02459 0.01758 -0.0969 0.0848 1.0000
9.000 1.3813 0.02550 0.01849 -0.0959 0.0826 1.0000
9.250 1.3957 0.02645 0.01946 -0.0948 0.0814 1.0000
9.500 1.4102 0.02740 0.02042 -0.0938 0.0803 1.0000
9.750 1.4237 0.02846 0.02149 -0.0928 0.0793 1.0000
10.000 1.4373 0.02952 0.02257 -0.0918 0.0784 1.0000
10.250 1.4500 0.03067 0.02373 -0.0908 0.0775 1.0000
10.500 1.4624 0.03184 0.02493 -0.0898 0.0766 1.0000
10.750 1.4744 0.03307 0.02618 -0.0888 0.0757 1.0000
11.000 1.4863 0.03433 0.02747 -0.0879 0.0751 1.0000
11.250 1.4993 0.03551 0.02868 -0.0870 0.0748 1.0000
11.500 1.5108 0.03684 0.03005 -0.0862 0.0746 1.0000
11.750 1.5227 0.03815 0.03140 -0.0853 0.0743 1.0000
12.000 1.5331 0.03959 0.03288 -0.0845 0.0740 1.0000
12.250 1.5436 0.04105 0.03438 -0.0836 0.0738 1.0000
12.500 1.5532 0.04261 0.03599 -0.0828 0.0735 1.0000
12.750 1.5625 0.04423 0.03765 -0.0820 0.0732 1.0000
13.000 1.5711 0.04594 0.03941 -0.0812 0.0729 1.0000
13.250 1.5791 0.04773 0.04124 -0.0805 0.0726 1.0000
13.500 1.5863 0.04960 0.04316 -0.0797 0.0723 1.0000
13.750 1.5930 0.05155 0.04517 -0.0790 0.0720 1.0000
14.000 1.5989 0.05363 0.04730 -0.0783 0.0718 1.0000
14.250 1.6045 0.05574 0.04947 -0.0777 0.0715 1.0000
14.500 1.6087 0.05805 0.05184 -0.0771 0.0712 1.0000
14.750 1.6133 0.06032 0.05416 -0.0765 0.0710 1.0000
15.000 1.6155 0.06288 0.05678 -0.0759 0.0707 1.0000
15.250 1.6182 0.06540 0.05937 -0.0754 0.0704 1.0000
15.500 1.6192 0.06817 0.06219 -0.0749 0.0700 1.0000
15.750 1.6191 0.07110 0.06518 -0.0745 0.0695 1.0000
16.000 1.6184 0.07409 0.06824 -0.0742 0.0689 1.0000
16.250 1.6151 0.07745 0.07167 -0.0738 0.0683 1.0000
16.500 1.6104 0.08100 0.07530 -0.0736 0.0678 1.0000
16.750 1.6068 0.08445 0.07882 -0.0734 0.0674 1.0000
17.000 1.6072 0.08745 0.08189 -0.0734 0.0672 1.0000
17.250 1.6081 0.09038 0.08489 -0.0734 0.0670 1.0000
17.500 1.6080 0.09343 0.08801 -0.0734 0.0668 1.0000
17.750 1.6083 0.09643 0.09108 -0.0735 0.0665 1.0000
18.000 1.6073 0.09963 0.09436 -0.0737 0.0662 1.0000
18.250 1.6054 0.10298 0.09777 -0.0740 0.0659 1.0000
18.500 1.6042 0.10623 0.10110 -0.0743 0.0657 1.0000
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