GOE 630 AIRFOIL (goe630-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 630 AIRFOIL (goe630-il) Reynolds number: 500,000 Max Cl/Cd: 103.66 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe630-il-500000.txt Download as CSV file: xf-goe630-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 630 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.0869 0.08973 0.08696 -0.1211 0.8850 0.0290
-9.750 0.1086 0.08649 0.08362 -0.1214 0.8705 0.0293
-9.500 0.1221 0.08424 0.08127 -0.1219 0.8547 0.0295
-9.250 0.1335 0.08237 0.07931 -0.1222 0.8409 0.0301
-9.000 0.1415 0.08041 0.07730 -0.1225 0.8286 0.0307
-8.750 0.1486 0.07836 0.07520 -0.1229 0.8180 0.0313
-8.500 0.1550 0.07622 0.07300 -0.1235 0.8086 0.0320
-8.250 0.1428 0.07389 0.07066 -0.1260 0.7973 0.0334
-8.000 0.1365 0.07137 0.06811 -0.1271 0.7886 0.0336
-7.750 0.1430 0.06860 0.06534 -0.1265 0.7813 0.0338
-7.500 0.1584 0.06672 0.06339 -0.1255 0.7750 0.0341
-7.250 0.1649 0.06495 0.06163 -0.1248 0.7681 0.0343
-7.000 0.1712 0.06340 0.06005 -0.1243 0.7612 0.0347
-6.750 0.1795 0.06158 0.05821 -0.1248 0.7548 0.0354
-6.500 0.1875 0.05946 0.05609 -0.1259 0.7483 0.0363
-6.250 0.1969 0.05707 0.05364 -0.1280 0.7422 0.0373
-6.000 0.2074 0.05049 0.04695 -0.1393 0.7361 0.0390
-5.750 0.2198 0.04868 0.04513 -0.1383 0.7299 0.0393
-5.500 0.2357 0.04704 0.04342 -0.1383 0.7244 0.0397
-5.250 0.2526 0.04544 0.04182 -0.1386 0.7185 0.0402
-5.000 0.2712 0.04351 0.03984 -0.1397 0.7126 0.0411
-4.750 0.3048 0.03696 0.03282 -0.1483 0.7077 0.0450
-4.500 0.3187 0.03410 0.02999 -0.1482 0.7021 0.0456
-4.250 0.3386 0.03283 0.02869 -0.1481 0.6960 0.0460
-3.750 0.3823 0.03002 0.02572 -0.1483 0.6841 0.0478
-3.500 0.4073 0.02521 0.02031 -0.1497 0.6787 0.0530
-3.250 0.4297 0.02404 0.01911 -0.1495 0.6729 0.0537
-3.000 0.4527 0.02304 0.01809 -0.1491 0.6659 0.0545
-2.750 0.4763 0.02203 0.01695 -0.1488 0.6591 0.0559
-2.500 0.4972 0.01624 0.00997 -0.1470 0.6539 0.0453
-2.250 0.5215 0.01512 0.00866 -0.1463 0.6466 0.0454
-2.000 0.5464 0.01431 0.00763 -0.1456 0.6398 0.0454
-1.750 0.5713 0.01344 0.00666 -0.1450 0.6317 0.0458
-1.500 0.5961 0.01288 0.00596 -0.1443 0.6239 0.0462
-1.250 0.6214 0.01246 0.00550 -0.1437 0.6146 0.0470
-1.000 0.6464 0.01215 0.00510 -0.1430 0.6058 0.0478
-0.750 0.6715 0.01191 0.00480 -0.1424 0.5959 0.0490
-0.500 0.6965 0.01172 0.00454 -0.1417 0.5863 0.0506
-0.250 0.7210 0.01161 0.00433 -0.1408 0.5762 0.0518
0.000 0.7452 0.01127 0.00395 -0.1400 0.5657 0.0532
0.250 0.7688 0.01109 0.00373 -0.1391 0.5551 0.0551
0.500 0.7922 0.01105 0.00363 -0.1382 0.5439 0.0573
0.750 0.8163 0.01102 0.00356 -0.1374 0.5327 0.0600
1.000 0.8394 0.01093 0.00343 -0.1364 0.5224 0.0638
1.250 0.8624 0.01096 0.00341 -0.1354 0.5120 0.0681
1.500 0.8862 0.01096 0.00338 -0.1346 0.5022 0.0735
1.750 0.9088 0.01103 0.00342 -0.1335 0.4929 0.0829
2.000 0.9319 0.01099 0.00347 -0.1326 0.4837 0.1168
2.250 0.9521 0.01074 0.00368 -0.1313 0.4753 0.3246
2.500 1.0112 0.00983 0.00404 -0.1387 0.4644 1.0000
2.750 1.0343 0.01002 0.00414 -0.1378 0.4566 1.0000
3.000 1.0566 0.01023 0.00427 -0.1367 0.4490 1.0000
3.250 1.0792 0.01044 0.00441 -0.1357 0.4423 1.0000
3.500 1.1019 0.01063 0.00455 -0.1348 0.4356 1.0000
3.750 1.1228 0.01091 0.00472 -0.1335 0.4294 1.0000
4.000 1.1461 0.01107 0.00488 -0.1327 0.4237 1.0000
4.250 1.1678 0.01129 0.00505 -0.1316 0.4180 1.0000
4.500 1.1883 0.01158 0.00526 -0.1303 0.4126 1.0000
4.750 1.2110 0.01175 0.00544 -0.1293 0.4077 1.0000
5.000 1.2317 0.01198 0.00563 -0.1281 0.4024 1.0000
5.250 1.2502 0.01228 0.00586 -0.1264 0.3976 1.0000
5.500 1.2709 0.01248 0.00607 -0.1251 0.3936 1.0000
5.750 1.2910 0.01269 0.00629 -0.1238 0.3894 1.0000
6.000 1.3100 0.01296 0.00653 -0.1223 0.3853 1.0000
6.250 1.3287 0.01331 0.00682 -0.1208 0.3813 1.0000
6.500 1.3492 0.01353 0.00708 -0.1196 0.3780 1.0000
6.750 1.3694 0.01376 0.00734 -0.1184 0.3745 1.0000
7.000 1.3888 0.01405 0.00762 -0.1170 0.3708 1.0000
7.250 1.4075 0.01439 0.00794 -0.1156 0.3672 1.0000
7.500 1.4273 0.01475 0.00829 -0.1145 0.3639 1.0000
7.750 1.4473 0.01501 0.00861 -0.1133 0.3611 1.0000
8.000 1.4669 0.01531 0.00894 -0.1122 0.3581 1.0000
8.250 1.4861 0.01564 0.00929 -0.1110 0.3552 1.0000
8.500 1.5048 0.01602 0.00967 -0.1098 0.3521 1.0000
8.750 1.5246 0.01647 0.01009 -0.1088 0.3486 1.0000
9.000 1.5414 0.01678 0.01049 -0.1073 0.3452 1.0000
9.250 1.5584 0.01715 0.01091 -0.1059 0.3414 1.0000
9.500 1.5744 0.01759 0.01136 -0.1044 0.3372 1.0000
9.750 1.5902 0.01814 0.01188 -0.1030 0.3325 1.0000
10.000 1.6069 0.01855 0.01239 -0.1017 0.3292 1.0000
10.250 1.6220 0.01904 0.01294 -0.1002 0.3247 1.0000
10.500 1.6362 0.01964 0.01354 -0.0987 0.3203 1.0000
10.750 1.6503 0.02027 0.01420 -0.0973 0.3156 1.0000
11.000 1.6653 0.02084 0.01486 -0.0960 0.3110 1.0000
11.250 1.6782 0.02156 0.01562 -0.0946 0.3060 1.0000
11.500 1.6906 0.02238 0.01642 -0.0931 0.3019 1.0000
11.750 1.7056 0.02303 0.01721 -0.0920 0.2973 1.0000
12.000 1.7175 0.02390 0.01811 -0.0907 0.2915 1.0000
12.250 1.7270 0.02495 0.01918 -0.0892 0.2859 1.0000
12.500 1.7400 0.02583 0.02015 -0.0881 0.2794 1.0000
12.750 1.7460 0.02720 0.02152 -0.0865 0.2714 1.0000
13.000 1.7546 0.02845 0.02283 -0.0852 0.2609 1.0000
13.250 1.7609 0.02992 0.02432 -0.0838 0.2502 1.0000
13.500 1.7600 0.03202 0.02638 -0.0821 0.2333 1.0000
13.750 1.7507 0.03490 0.02918 -0.0799 0.2103 1.0000
14.000 1.7318 0.03879 0.03291 -0.0775 0.1824 1.0000
14.250 1.7079 0.04334 0.03732 -0.0752 0.1563 1.0000
14.500 1.6829 0.04828 0.04216 -0.0732 0.1326 1.0000
14.750 1.6569 0.05358 0.04737 -0.0717 0.1093 1.0000
15.000 1.6280 0.05951 0.05323 -0.0705 0.0887 1.0000
15.250 1.6024 0.06535 0.05905 -0.0698 0.0734 1.0000
15.500 1.5773 0.07137 0.06507 -0.0695 0.0581 1.0000
15.750 1.5510 0.07776 0.07143 -0.0695 0.0434 1.0000
16.000 1.5258 0.08421 0.07790 -0.0697 0.0345 1.0000
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