GOE 646 AIRFOIL (goe646-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 646 AIRFOIL (goe646-il) Reynolds number: 500,000 Max Cl/Cd: 77.17 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe646-il-500000-n5.txt Download as CSV file: xf-goe646-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 646 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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.8042 0.08972 0.08546 -0.0798 1.0000 0.0365
-17.500 -0.8086 0.08634 0.08207 -0.0809 1.0000 0.0368
-17.250 -0.8158 0.08258 0.07828 -0.0823 1.0000 0.0372
-17.000 -0.8232 0.07890 0.07458 -0.0836 1.0000 0.0376
-16.750 -0.8319 0.07516 0.07080 -0.0848 1.0000 0.0379
-16.500 -0.8399 0.07164 0.06725 -0.0858 1.0000 0.0382
-16.250 -0.8499 0.06803 0.06358 -0.0867 1.0000 0.0385
-16.000 -0.8573 0.06414 0.05964 -0.0887 0.9996 0.0388
-15.750 -0.8553 0.05998 0.05540 -0.0928 0.9983 0.0393
-15.500 -0.8530 0.05588 0.05122 -0.0970 0.9962 0.0397
-15.250 -0.8502 0.05185 0.04711 -0.1012 0.9936 0.0402
-15.000 -0.8497 0.04786 0.04303 -0.1049 0.9904 0.0405
-14.750 -0.8487 0.04392 0.03900 -0.1087 0.9862 0.0409
-14.500 -0.8470 0.03960 0.03460 -0.1136 0.9821 0.0414
-14.250 -0.8466 0.03565 0.03057 -0.1173 0.9754 0.0419
-14.000 -0.8398 0.03200 0.02684 -0.1216 0.9689 0.0426
-13.750 -0.8350 0.02890 0.02365 -0.1246 0.9592 0.0434
-13.500 -0.8190 0.02619 0.02083 -0.1288 0.9532 0.0442
-13.250 -0.8040 0.02388 0.01841 -0.1321 0.9428 0.0450
-13.000 -0.7791 0.02201 0.01642 -0.1362 0.9351 0.0461
-12.750 -0.7505 0.02070 0.01504 -0.1393 0.9273 0.0474
-12.500 -0.7139 0.01965 0.01391 -0.1430 0.9219 0.0492
-12.000 -0.6540 0.01806 0.01217 -0.1468 0.9058 0.0528
-11.750 -0.6304 0.01748 0.01152 -0.1470 0.8976 0.0549
-11.500 -0.6073 0.01697 0.01095 -0.1470 0.8902 0.0570
-11.250 -0.5833 0.01647 0.01040 -0.1470 0.8838 0.0594
-11.000 -0.5642 0.01611 0.00998 -0.1459 0.8769 0.0619
-10.750 -0.5430 0.01570 0.00953 -0.1451 0.8706 0.0641
-10.250 -0.4984 0.01504 0.00877 -0.1437 0.8590 0.0690
-10.000 -0.4774 0.01468 0.00838 -0.1427 0.8525 0.0714
-9.750 -0.4535 0.01438 0.00802 -0.1422 0.8466 0.0741
-9.500 -0.4304 0.01413 0.00772 -0.1414 0.8412 0.0764
-9.250 -0.4090 0.01379 0.00737 -0.1404 0.8353 0.0790
-9.000 -0.3854 0.01352 0.00706 -0.1398 0.8294 0.0818
-8.750 -0.3604 0.01329 0.00676 -0.1393 0.8241 0.0846
-8.500 -0.3384 0.01299 0.00646 -0.1383 0.8177 0.0874
-8.250 -0.3147 0.01274 0.00618 -0.1375 0.8108 0.0905
-8.000 -0.2897 0.01253 0.00590 -0.1370 0.8043 0.0935
-7.750 -0.2667 0.01226 0.00564 -0.1361 0.7970 0.0973
-7.500 -0.2423 0.01205 0.00539 -0.1354 0.7897 0.1016
-7.250 -0.2181 0.01181 0.00514 -0.1347 0.7827 0.1069
-6.750 -0.1695 0.01139 0.00469 -0.1333 0.7663 0.1204
-6.500 -0.1456 0.01117 0.00449 -0.1325 0.7572 0.1299
-6.250 -0.1216 0.01098 0.00429 -0.1317 0.7473 0.1413
-6.000 -0.0975 0.01081 0.00412 -0.1309 0.7359 0.1516
-5.750 -0.0734 0.01068 0.00395 -0.1300 0.7239 0.1603
-5.500 -0.0498 0.01055 0.00379 -0.1290 0.7105 0.1688
-5.250 -0.0256 0.01047 0.00366 -0.1282 0.6971 0.1769
-5.000 -0.0019 0.01037 0.00354 -0.1272 0.6844 0.1852
-4.500 0.0460 0.01025 0.00334 -0.1254 0.6601 0.2026
-4.250 0.0701 0.01023 0.00326 -0.1245 0.6497 0.2101
-4.000 0.0947 0.01018 0.00319 -0.1237 0.6399 0.2185
-3.750 0.1193 0.01018 0.00313 -0.1229 0.6312 0.2258
-3.500 0.1443 0.01013 0.00309 -0.1222 0.6229 0.2347
-3.250 0.1689 0.01015 0.00305 -0.1213 0.6148 0.2421
-3.000 0.1943 0.01012 0.00302 -0.1207 0.6081 0.2493
-2.750 0.2196 0.01012 0.00300 -0.1200 0.6009 0.2567
-2.250 0.2695 0.01013 0.00298 -0.1186 0.5869 0.2726
-2.000 0.2946 0.01016 0.00296 -0.1178 0.5798 0.2792
-1.750 0.3190 0.01018 0.00297 -0.1170 0.5738 0.2866
-1.500 0.3449 0.01018 0.00297 -0.1164 0.5683 0.2945
-1.250 0.3701 0.01019 0.00297 -0.1157 0.5623 0.3004
-1.000 0.3945 0.01022 0.00298 -0.1149 0.5565 0.3058
-0.750 0.4194 0.01025 0.00300 -0.1142 0.5510 0.3113
-0.500 0.4448 0.01027 0.00301 -0.1135 0.5451 0.3166
-0.250 0.4693 0.01029 0.00303 -0.1127 0.5400 0.3220
0.000 0.4936 0.01033 0.00306 -0.1118 0.5355 0.3277
0.250 0.5187 0.01036 0.00309 -0.1111 0.5314 0.3335
0.500 0.5439 0.01039 0.00312 -0.1104 0.5267 0.3390
0.750 0.5677 0.01040 0.00316 -0.1095 0.5220 0.3452
1.000 0.5909 0.01045 0.00320 -0.1084 0.5176 0.3518
1.250 0.6140 0.01052 0.00324 -0.1073 0.5137 0.3579
1.500 0.6380 0.01051 0.00329 -0.1064 0.5097 0.3649
1.750 0.6614 0.01054 0.00335 -0.1054 0.5049 0.3718
2.000 0.6839 0.01061 0.00340 -0.1041 0.4997 0.3784
2.250 0.7054 0.01068 0.00348 -0.1028 0.4948 0.3857
2.500 0.7294 0.01071 0.00355 -0.1019 0.4904 0.3933
2.750 0.7519 0.01078 0.00363 -0.1007 0.4845 0.4009
3.000 0.7718 0.01088 0.00374 -0.0991 0.4773 0.4101
3.250 0.7938 0.01096 0.00384 -0.0978 0.4703 0.4192
3.500 0.8135 0.01107 0.00397 -0.0961 0.4607 0.4291
3.750 0.8340 0.01119 0.00409 -0.0947 0.4524 0.4410
4.000 0.8531 0.01130 0.00425 -0.0929 0.4423 0.4568
4.250 0.8721 0.01143 0.00441 -0.0912 0.4318 0.4763
4.500 0.8892 0.01159 0.00461 -0.0891 0.4201 0.5002
4.750 0.9068 0.01175 0.00482 -0.0872 0.4066 0.5289
5.000 0.9222 0.01197 0.00507 -0.0848 0.3916 0.5602
5.250 0.9370 0.01224 0.00535 -0.0825 0.3767 0.5904
5.500 0.9513 0.01254 0.00566 -0.0800 0.3633 0.6171
6.000 0.9819 0.01316 0.00629 -0.0756 0.3406 0.6579
6.250 0.9962 0.01352 0.00664 -0.0733 0.3315 0.6749
6.500 1.0133 0.01380 0.00695 -0.0715 0.3239 0.6928
7.000 1.0421 0.01443 0.00770 -0.0670 0.3086 0.7413
7.250 1.0581 0.01454 0.00817 -0.0652 0.2996 0.8688
7.500 1.1267 0.01510 0.00876 -0.0745 0.2873 1.0000
7.750 1.1430 0.01560 0.00922 -0.0729 0.2808 1.0000
8.000 1.1604 0.01606 0.00967 -0.0715 0.2738 1.0000
8.250 1.1779 0.01653 0.01013 -0.0701 0.2674 1.0000
8.500 1.1931 0.01713 0.01068 -0.0685 0.2609 1.0000
8.750 1.2115 0.01760 0.01116 -0.0674 0.2552 1.0000
9.000 1.2281 0.01816 0.01171 -0.0661 0.2489 1.0000
9.250 1.2430 0.01883 0.01235 -0.0646 0.2427 1.0000
9.500 1.2603 0.01939 0.01292 -0.0635 0.2368 1.0000
9.750 1.2756 0.02008 0.01360 -0.0621 0.2306 1.0000
10.000 1.2903 0.02081 0.01432 -0.0608 0.2251 1.0000
10.250 1.3057 0.02153 0.01505 -0.0596 0.2183 1.0000
10.500 1.3177 0.02247 0.01595 -0.0581 0.2111 1.0000
10.750 1.3317 0.02331 0.01679 -0.0569 0.2034 1.0000
11.000 1.3431 0.02435 0.01780 -0.0555 0.1966 1.0000
11.250 1.3563 0.02529 0.01876 -0.0544 0.1907 1.0000
11.500 1.3675 0.02639 0.01985 -0.0531 0.1841 1.0000
11.750 1.3785 0.02754 0.02100 -0.0519 0.1790 1.0000
12.000 1.3902 0.02867 0.02214 -0.0508 0.1737 1.0000
12.250 1.3991 0.03002 0.02349 -0.0496 0.1684 1.0000
12.500 1.4098 0.03128 0.02477 -0.0485 0.1641 1.0000
12.750 1.4189 0.03269 0.02618 -0.0475 0.1580 1.0000
13.000 1.4253 0.03436 0.02785 -0.0464 0.1528 1.0000
13.250 1.4358 0.03573 0.02926 -0.0455 0.1483 1.0000
13.500 1.4423 0.03746 0.03100 -0.0446 0.1426 1.0000
13.750 1.4494 0.03918 0.03274 -0.0437 0.1381 1.0000
14.000 1.4565 0.04094 0.03453 -0.0430 0.1318 1.0000
14.250 1.4611 0.04296 0.03655 -0.0422 0.1252 1.0000
14.500 1.4626 0.04531 0.03889 -0.0414 0.1159 1.0000
14.750 1.4613 0.04797 0.04152 -0.0406 0.1038 1.0000
15.000 1.4568 0.05101 0.04451 -0.0399 0.0924 1.0000
15.250 1.4537 0.05395 0.04744 -0.0393 0.0858 1.0000
15.500 1.4525 0.05675 0.05026 -0.0388 0.0816 1.0000
15.750 1.4508 0.05965 0.05319 -0.0384 0.0786 1.0000
16.000 1.4516 0.06233 0.05592 -0.0382 0.0763 1.0000
16.250 1.4512 0.06518 0.05883 -0.0379 0.0744 1.0000
16.500 1.4485 0.06832 0.06201 -0.0378 0.0725 1.0000
16.750 1.4463 0.07141 0.06516 -0.0377 0.0711 1.0000
17.000 1.4470 0.07424 0.06806 -0.0377 0.0701 1.0000
17.250 1.4473 0.07712 0.07101 -0.0378 0.0691 1.0000
17.500 1.4461 0.08021 0.07417 -0.0379 0.0680 1.0000
17.750 1.4438 0.08345 0.07748 -0.0381 0.0670 1.0000
18.000 1.4410 0.08677 0.08087 -0.0383 0.0661 1.0000
18.250 1.4362 0.09042 0.08458 -0.0388 0.0653 1.0000
18.500 1.4313 0.09409 0.08831 -0.0392 0.0645 1.0000
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