GOE 502 AIRFOIL (goe502-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 502 AIRFOIL (goe502-il) Reynolds number: 200,000 Max Cl/Cd: 75.12 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe502-il-200000-n5.txt Download as CSV file: xf-goe502-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 502 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3967 0.04537 0.04008 -0.1397 0.9356 0.0444
-10.750 -0.4027 0.03812 0.03243 -0.1527 0.9249 0.0446
-10.500 -0.3975 0.03509 0.02909 -0.1560 0.9156 0.0449
-10.250 -0.3801 0.03260 0.02628 -0.1592 0.9095 0.0454
-10.000 -0.3541 0.03044 0.02377 -0.1626 0.9057 0.0458
-9.750 -0.3416 0.02925 0.02245 -0.1615 0.8961 0.0462
-9.500 -0.3144 0.02806 0.02123 -0.1627 0.8911 0.0468
-9.250 -0.2825 0.02686 0.01995 -0.1648 0.8873 0.0475
-9.000 -0.2673 0.02603 0.01904 -0.1634 0.8764 0.0481
-8.750 -0.2376 0.02494 0.01780 -0.1647 0.8698 0.0488
-8.500 -0.2183 0.02410 0.01685 -0.1638 0.8595 0.0494
-8.250 -0.1913 0.02319 0.01578 -0.1643 0.8522 0.0501
-8.000 -0.1683 0.02245 0.01490 -0.1639 0.8441 0.0507
-7.750 -0.1436 0.02176 0.01406 -0.1638 0.8360 0.0512
-7.500 -0.1171 0.02092 0.01325 -0.1639 0.8293 0.0519
-7.250 -0.0950 0.02031 0.01263 -0.1632 0.8203 0.0527
-7.000 -0.0667 0.01966 0.01194 -0.1636 0.8137 0.0537
-6.750 -0.0436 0.01915 0.01137 -0.1630 0.8050 0.0548
-6.500 -0.0160 0.01861 0.01072 -0.1631 0.7976 0.0559
-6.250 0.0100 0.01817 0.01018 -0.1629 0.7900 0.0568
-6.000 0.0358 0.01758 0.00959 -0.1628 0.7826 0.0578
-5.750 0.0638 0.01708 0.00904 -0.1630 0.7762 0.0589
-5.500 0.0891 0.01669 0.00860 -0.1626 0.7684 0.0602
-5.250 0.1173 0.01632 0.00812 -0.1628 0.7616 0.0618
-5.000 0.1442 0.01597 0.00770 -0.1627 0.7551 0.0635
-4.750 0.1704 0.01560 0.00730 -0.1625 0.7483 0.0655
-4.500 0.1988 0.01531 0.00690 -0.1626 0.7421 0.0678
-4.250 0.2255 0.01505 0.00658 -0.1624 0.7356 0.0704
-4.000 0.2518 0.01477 0.00629 -0.1621 0.7286 0.0743
-3.750 0.2799 0.01449 0.00600 -0.1622 0.7226 0.0831
-3.500 0.3064 0.01423 0.00582 -0.1619 0.7166 0.1050
-3.250 0.3323 0.01405 0.00569 -0.1615 0.7097 0.1274
-3.000 0.3601 0.01394 0.00556 -0.1614 0.7033 0.1467
-2.750 0.3871 0.01387 0.00548 -0.1612 0.6971 0.1633
-2.500 0.4126 0.01381 0.00544 -0.1606 0.6901 0.1764
-2.250 0.4398 0.01378 0.00539 -0.1603 0.6837 0.1899
-2.000 0.4668 0.01377 0.00534 -0.1600 0.6773 0.2004
-1.750 0.4918 0.01375 0.00534 -0.1593 0.6697 0.2115
-1.500 0.5185 0.01374 0.00531 -0.1589 0.6629 0.2225
-1.250 0.5445 0.01376 0.00530 -0.1584 0.6561 0.2337
-1.000 0.5694 0.01375 0.00532 -0.1576 0.6482 0.2442
-0.750 0.5960 0.01377 0.00529 -0.1572 0.6412 0.2550
-0.500 0.6205 0.01379 0.00533 -0.1564 0.6334 0.2668
-0.250 0.6457 0.01381 0.00535 -0.1557 0.6256 0.2782
0.000 0.6712 0.01386 0.00535 -0.1551 0.6183 0.2902
0.250 0.6954 0.01388 0.00541 -0.1542 0.6098 0.3010
0.750 0.7449 0.01397 0.00548 -0.1527 0.5946 0.3220
1.000 0.7696 0.01404 0.00549 -0.1519 0.5869 0.3325
1.250 0.7938 0.01409 0.00557 -0.1511 0.5796 0.3427
1.500 0.8181 0.01417 0.00563 -0.1502 0.5722 0.3543
1.750 0.8428 0.01425 0.00570 -0.1495 0.5658 0.3659
2.000 0.8665 0.01435 0.00583 -0.1486 0.5587 0.3782
2.250 0.8905 0.01445 0.00593 -0.1478 0.5520 0.3913
2.500 0.9151 0.01457 0.00605 -0.1470 0.5462 0.4049
2.750 0.9386 0.01468 0.00621 -0.1461 0.5400 0.4200
3.000 0.9623 0.01481 0.00635 -0.1452 0.5340 0.4363
3.250 0.9868 0.01496 0.00649 -0.1445 0.5286 0.4535
3.500 1.0097 0.01507 0.00669 -0.1435 0.5229 0.4721
3.750 1.0332 0.01520 0.00688 -0.1426 0.5175 0.4933
4.000 1.0569 0.01534 0.00705 -0.1418 0.5125 0.5178
4.250 1.0795 0.01545 0.00727 -0.1408 0.5075 0.5495
4.500 1.1005 0.01550 0.00754 -0.1394 0.5021 0.6076
4.750 1.1221 0.01531 0.00779 -0.1380 0.4970 0.7891
5.250 1.1745 0.01564 0.00819 -0.1374 0.4853 1.0000
5.500 1.1937 0.01589 0.00842 -0.1358 0.4787 1.0000
5.750 1.2149 0.01618 0.00862 -0.1345 0.4728 1.0000
6.000 1.2330 0.01645 0.00891 -0.1327 0.4666 1.0000
6.250 1.2517 0.01673 0.00919 -0.1310 0.4605 1.0000
6.500 1.2714 0.01703 0.00945 -0.1296 0.4549 1.0000
6.750 1.2895 0.01734 0.00977 -0.1278 0.4490 1.0000
7.000 1.3067 0.01765 0.01010 -0.1260 0.4425 1.0000
7.250 1.3246 0.01800 0.01041 -0.1243 0.4365 1.0000
7.500 1.3411 0.01835 0.01079 -0.1224 0.4300 1.0000
7.750 1.3565 0.01872 0.01118 -0.1204 0.4228 1.0000
8.000 1.3727 0.01913 0.01155 -0.1185 0.4165 1.0000
8.250 1.3887 0.01954 0.01203 -0.1167 0.4104 1.0000
8.500 1.4042 0.01998 0.01249 -0.1148 0.4042 1.0000
8.750 1.4192 0.02046 0.01294 -0.1129 0.3981 1.0000
9.000 1.4334 0.02097 0.01353 -0.1109 0.3911 1.0000
9.250 1.4464 0.02153 0.01410 -0.1088 0.3840 1.0000
9.500 1.4593 0.02213 0.01472 -0.1068 0.3768 1.0000
9.750 1.4708 0.02279 0.01541 -0.1046 0.3685 1.0000
10.000 1.4811 0.02353 0.01616 -0.1024 0.3599 1.0000
10.250 1.4895 0.02438 0.01702 -0.0999 0.3496 1.0000
10.500 1.4978 0.02528 0.01794 -0.0977 0.3392 1.0000
10.750 1.5032 0.02637 0.01899 -0.0951 0.3281 1.0000
11.000 1.5095 0.02749 0.02013 -0.0928 0.3160 1.0000
11.250 1.5146 0.02874 0.02139 -0.0906 0.3039 1.0000
11.500 1.5176 0.03017 0.02280 -0.0882 0.2915 1.0000
11.750 1.5182 0.03185 0.02445 -0.0859 0.2774 1.0000
12.000 1.5171 0.03376 0.02632 -0.0836 0.2617 1.0000
12.250 1.5153 0.03584 0.02836 -0.0814 0.2461 1.0000
12.500 1.5119 0.03817 0.03065 -0.0794 0.2304 1.0000
12.750 1.5090 0.04060 0.03305 -0.0776 0.2162 1.0000
13.000 1.5065 0.04308 0.03551 -0.0761 0.2041 1.0000
13.250 1.5042 0.04566 0.03808 -0.0747 0.1944 1.0000
13.500 1.5008 0.04843 0.04083 -0.0734 0.1856 1.0000
13.750 1.5005 0.05098 0.04341 -0.0724 0.1785 1.0000
14.000 1.4982 0.05379 0.04624 -0.0714 0.1719 1.0000
14.250 1.4983 0.05645 0.04893 -0.0706 0.1663 1.0000
14.500 1.4990 0.05911 0.05163 -0.0700 0.1610 1.0000
14.750 1.4971 0.06209 0.05463 -0.0694 0.1562 1.0000
15.000 1.4994 0.06467 0.05727 -0.0689 0.1518 1.0000
15.250 1.5010 0.06739 0.06006 -0.0686 0.1470 1.0000
15.500 1.4995 0.07051 0.06320 -0.0683 0.1425 1.0000
15.750 1.5018 0.07324 0.06600 -0.0681 0.1384 1.0000
16.000 1.5040 0.07603 0.06887 -0.0680 0.1338 1.0000
16.250 1.5029 0.07924 0.07211 -0.0681 0.1294 1.0000
16.500 1.5044 0.08219 0.07514 -0.0682 0.1251 1.0000
16.750 1.5059 0.08517 0.07820 -0.0683 0.1203 1.0000
17.000 1.5034 0.08872 0.08177 -0.0687 0.1160 1.0000
17.250 1.5054 0.09170 0.08484 -0.0690 0.1111 1.0000
17.500 1.5038 0.09520 0.08838 -0.0695 0.1063 1.0000
17.750 1.5030 0.09861 0.09186 -0.0700 0.1018 1.0000
18.000 1.5023 0.10205 0.09535 -0.0707 0.0970 1.0000
18.250 1.4995 0.10580 0.09914 -0.0715 0.0928 1.0000
18.500 1.4992 0.10919 0.10260 -0.0722 0.0883 1.0000
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Polar data table (+)
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