GOE 446 AIRFOIL (goe446-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 446 AIRFOIL (goe446-il) Reynolds number: 200,000 Max Cl/Cd: 83.12 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe446-il-200000-n5.txt Download as CSV file: xf-goe446-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 446 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.0322 0.09060 0.08656 -0.1025 0.9110 0.0505
-8.750 -0.0349 0.08719 0.08314 -0.1063 0.8983 0.0518
-8.250 -0.0338 0.07709 0.07296 -0.1101 0.8768 0.0389
-8.000 -0.0249 0.07450 0.07033 -0.1109 0.8680 0.0385
-7.750 -0.0212 0.07136 0.06717 -0.1127 0.8574 0.0384
-7.500 -0.0155 0.06752 0.06327 -0.1165 0.8483 0.0385
-7.250 -0.0058 0.06365 0.05935 -0.1206 0.8394 0.0384
-7.000 0.0065 0.05982 0.05545 -0.1248 0.8318 0.0380
-6.750 0.0202 0.05533 0.05086 -0.1300 0.8243 0.0376
-6.500 0.0361 0.04976 0.04514 -0.1365 0.8178 0.0371
-6.250 0.0519 0.04202 0.03712 -0.1442 0.8105 0.0367
-6.000 0.0581 0.02438 0.01782 -0.1542 0.8047 0.0375
-5.750 0.0820 0.02219 0.01515 -0.1547 0.7995 0.0379
-5.500 0.1073 0.02074 0.01334 -0.1548 0.7943 0.0382
-5.250 0.1342 0.01964 0.01193 -0.1551 0.7898 0.0386
-5.000 0.1619 0.01877 0.01080 -0.1553 0.7856 0.0390
-4.750 0.1879 0.01807 0.00994 -0.1551 0.7799 0.0394
-4.500 0.2149 0.01741 0.00918 -0.1552 0.7744 0.0400
-4.250 0.2431 0.01689 0.00855 -0.1553 0.7693 0.0406
-4.000 0.2690 0.01647 0.00807 -0.1551 0.7622 0.0413
-3.750 0.2966 0.01609 0.00758 -0.1550 0.7558 0.0424
-3.500 0.3241 0.01575 0.00714 -0.1550 0.7498 0.0439
-3.250 0.3508 0.01543 0.00674 -0.1548 0.7435 0.0452
-3.000 0.3787 0.01511 0.00638 -0.1548 0.7389 0.0466
-2.750 0.4069 0.01486 0.00608 -0.1549 0.7348 0.0483
-2.500 0.4337 0.01465 0.00585 -0.1548 0.7295 0.0504
-2.250 0.4611 0.01444 0.00563 -0.1547 0.7245 0.0535
-2.000 0.4895 0.01427 0.00544 -0.1548 0.7204 0.0591
-1.750 0.5170 0.01417 0.00538 -0.1548 0.7159 0.0698
-1.500 0.5440 0.01413 0.00539 -0.1546 0.7107 0.0839
-1.250 0.5718 0.01411 0.00534 -0.1546 0.7057 0.0950
-1.000 0.6002 0.01411 0.00524 -0.1547 0.7014 0.1037
-0.750 0.6264 0.01408 0.00527 -0.1544 0.6956 0.1117
-0.500 0.6536 0.01408 0.00523 -0.1543 0.6903 0.1192
-0.250 0.6816 0.01402 0.00518 -0.1544 0.6859 0.1278
0.000 0.7081 0.01404 0.00520 -0.1542 0.6803 0.1371
0.250 0.7347 0.01396 0.00519 -0.1540 0.6745 0.1460
0.500 0.7624 0.01393 0.00510 -0.1540 0.6693 0.1534
0.750 0.7884 0.01388 0.00512 -0.1537 0.6628 0.1619
1.000 0.8149 0.01384 0.00511 -0.1535 0.6563 0.1744
1.250 0.8421 0.01378 0.00510 -0.1534 0.6508 0.1987
1.500 0.8676 0.01367 0.00521 -0.1531 0.6437 0.2607
1.750 0.8849 0.01249 0.00542 -0.1511 0.6377 0.7725
2.250 0.9403 0.01245 0.00546 -0.1507 0.6232 1.0000
2.500 0.9659 0.01259 0.00551 -0.1503 0.6157 1.0000
2.750 0.9908 0.01272 0.00560 -0.1497 0.6071 1.0000
3.000 1.0159 0.01287 0.00568 -0.1492 0.5990 1.0000
3.250 1.0406 0.01303 0.00579 -0.1487 0.5904 1.0000
3.500 1.0652 0.01320 0.00592 -0.1481 0.5819 1.0000
3.750 1.0895 0.01339 0.00604 -0.1475 0.5731 1.0000
4.000 1.1134 0.01358 0.00621 -0.1468 0.5639 1.0000
4.250 1.1372 0.01380 0.00635 -0.1461 0.5549 1.0000
4.500 1.1603 0.01402 0.00656 -0.1453 0.5452 1.0000
4.750 1.1837 0.01427 0.00675 -0.1445 0.5369 1.0000
5.000 1.2066 0.01452 0.00700 -0.1437 0.5282 1.0000
5.250 1.2294 0.01479 0.00723 -0.1429 0.5202 1.0000
5.500 1.2509 0.01508 0.00749 -0.1418 0.5104 1.0000
5.750 1.2720 0.01539 0.00777 -0.1407 0.5007 1.0000
6.000 1.2924 0.01573 0.00805 -0.1394 0.4912 1.0000
6.250 1.3125 0.01606 0.00838 -0.1381 0.4819 1.0000
6.500 1.3315 0.01644 0.00871 -0.1367 0.4729 1.0000
6.750 1.3470 0.01683 0.00907 -0.1345 0.4613 1.0000
7.000 1.3620 0.01726 0.00948 -0.1324 0.4491 1.0000
7.250 1.3779 0.01774 0.00991 -0.1304 0.4391 1.0000
7.500 1.3962 0.01815 0.01037 -0.1290 0.4317 1.0000
7.750 1.4143 0.01860 0.01082 -0.1275 0.4254 1.0000
8.000 1.4328 0.01903 0.01131 -0.1262 0.4193 1.0000
8.250 1.4503 0.01950 0.01182 -0.1247 0.4127 1.0000
8.500 1.4667 0.02002 0.01237 -0.1230 0.4057 1.0000
8.750 1.4806 0.02060 0.01300 -0.1210 0.3957 1.0000
9.000 1.4927 0.02127 0.01370 -0.1188 0.3841 1.0000
9.250 1.5029 0.02204 0.01447 -0.1164 0.3708 1.0000
9.500 1.5121 0.02290 0.01535 -0.1140 0.3560 1.0000
9.750 1.5207 0.02383 0.01630 -0.1116 0.3395 1.0000
10.000 1.5272 0.02494 0.01739 -0.1090 0.3189 1.0000
10.250 1.5281 0.02645 0.01880 -0.1060 0.2921 1.0000
10.500 1.5233 0.02845 0.02065 -0.1026 0.2612 1.0000
10.750 1.5171 0.03073 0.02278 -0.0993 0.2334 1.0000
11.000 1.5130 0.03302 0.02498 -0.0965 0.2108 1.0000
11.250 1.5103 0.03531 0.02720 -0.0941 0.1925 1.0000
11.500 1.5089 0.03759 0.02944 -0.0919 0.1768 1.0000
11.750 1.5089 0.03985 0.03168 -0.0900 0.1632 1.0000
12.000 1.5098 0.04211 0.03393 -0.0884 0.1516 1.0000
12.250 1.5107 0.04442 0.03625 -0.0868 0.1417 1.0000
12.500 1.5100 0.04694 0.03878 -0.0853 0.1319 1.0000
12.750 1.5109 0.04939 0.04124 -0.0840 0.1225 1.0000
13.000 1.5119 0.05187 0.04376 -0.0827 0.1143 1.0000
13.250 1.5105 0.05465 0.04655 -0.0815 0.1058 1.0000
13.500 1.5113 0.05727 0.04920 -0.0805 0.0960 1.0000
13.750 1.5096 0.06021 0.05215 -0.0795 0.0835 1.0000
14.000 1.4975 0.06439 0.05617 -0.0784 0.0526 1.0000
14.250 1.4822 0.06903 0.06067 -0.0774 0.0390 1.0000
14.750 1.4718 0.07632 0.06807 -0.0762 0.0321 1.0000
15.000 1.4680 0.07990 0.07174 -0.0758 0.0303 1.0000
15.250 1.4639 0.08355 0.07548 -0.0755 0.0288 1.0000
15.500 1.4628 0.08690 0.07896 -0.0754 0.0277 1.0000
15.750 1.4605 0.09044 0.08262 -0.0754 0.0267 1.0000
16.000 1.4572 0.09419 0.08649 -0.0755 0.0258 1.0000
16.250 1.4524 0.09818 0.09060 -0.0758 0.0251 1.0000
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Polar data table (+)
Polar graphs
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