GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Reynolds number: 200,000 Max Cl/Cd: 95.63 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe803h-il-200000.txt Download as CSV file: xf-goe803h-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 803 (HACKLINGER) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2517 0.10439 0.10105 -0.0244 1.0000 0.0299
-7.250 -0.2674 0.10460 0.10138 -0.0211 1.0000 0.0299
-7.000 -0.2825 0.10485 0.10174 -0.0186 0.9996 0.0299
-6.750 -0.2603 0.09927 0.09616 -0.0213 0.9966 0.0302
-6.500 -0.2387 0.09439 0.09127 -0.0233 0.9938 0.0306
-6.250 -0.2115 0.09031 0.08718 -0.0286 0.9881 0.0314
-6.000 -0.1807 0.08638 0.08323 -0.0353 0.9828 0.0325
-5.750 -0.1484 0.08258 0.07941 -0.0427 0.9751 0.0341
-5.500 -0.0926 0.07948 0.07623 -0.0604 0.9650 0.0354
-5.250 -0.0476 0.07469 0.07140 -0.0719 0.9602 0.0357
-5.000 -0.0336 0.07043 0.06716 -0.0703 0.9534 0.0362
-4.750 -0.0031 0.06655 0.06327 -0.0745 0.9488 0.0370
-4.500 0.0349 0.06288 0.05956 -0.0814 0.9437 0.0383
-4.250 0.0760 0.05931 0.05594 -0.0893 0.9362 0.0402
-4.000 0.1617 0.05482 0.05123 -0.1113 0.9316 0.0426
-3.750 0.1785 0.05139 0.04783 -0.1106 0.9225 0.0433
-3.500 0.2130 0.04819 0.04458 -0.1147 0.9167 0.0445
-3.250 0.2493 0.04543 0.04176 -0.1197 0.9063 0.0462
-3.000 0.3251 0.04275 0.03873 -0.1342 0.8985 0.0505
-2.750 0.3616 0.03902 0.03489 -0.1389 0.8879 0.0513
-2.500 0.3825 0.03661 0.03249 -0.1391 0.8758 0.0523
-2.250 0.4112 0.03467 0.03046 -0.1407 0.8642 0.0547
-2.000 0.4758 0.03344 0.02862 -0.1489 0.8534 0.0609
-1.750 0.4962 0.02999 0.02529 -0.1495 0.8405 0.0622
-1.500 0.5229 0.02826 0.02351 -0.1503 0.8277 0.0643
-1.250 0.5565 0.02669 0.02175 -0.1519 0.8146 0.0689
-1.000 0.5963 0.02470 0.01942 -0.1547 0.8028 0.0747
-0.750 0.6249 0.02337 0.01802 -0.1554 0.7912 0.0789
-0.500 0.6595 0.02201 0.01644 -0.1571 0.7810 0.0895
-0.250 0.6925 0.02101 0.01518 -0.1582 0.7719 0.1028
0.000 0.7233 0.02014 0.01414 -0.1589 0.7610 0.1175
0.250 0.7525 0.01913 0.01306 -0.1595 0.7504 0.1337
1.000 0.8538 0.01549 0.00832 -0.1602 0.7185 0.0814
1.250 0.8843 0.01467 0.00719 -0.1600 0.7084 0.0772
1.500 0.9124 0.01427 0.00671 -0.1597 0.6962 0.0818
1.750 0.9405 0.01400 0.00629 -0.1593 0.6842 0.0855
2.000 0.9685 0.01350 0.00581 -0.1591 0.6722 0.0930
2.250 0.9959 0.01334 0.00558 -0.1586 0.6595 0.0999
2.500 1.0232 0.01308 0.00538 -0.1583 0.6452 0.1093
2.750 1.0503 0.01296 0.00526 -0.1578 0.6296 0.1183
3.000 1.0770 0.01291 0.00519 -0.1573 0.6125 0.1311
3.250 1.1039 0.01282 0.00519 -0.1569 0.5920 0.1709
3.500 1.1255 0.01180 0.00523 -0.1553 0.5702 1.0000
3.750 1.1504 0.01203 0.00527 -0.1544 0.5437 1.0000
4.000 1.1744 0.01235 0.00540 -0.1534 0.5113 1.0000
4.250 1.1973 0.01279 0.00558 -0.1522 0.4727 1.0000
4.500 1.2196 0.01334 0.00587 -0.1511 0.4335 1.0000
4.750 1.2420 0.01395 0.00622 -0.1500 0.4020 1.0000
5.000 1.2646 0.01456 0.00664 -0.1490 0.3782 1.0000
5.250 1.2874 0.01517 0.00706 -0.1481 0.3601 1.0000
5.500 1.3106 0.01572 0.00748 -0.1473 0.3446 1.0000
5.750 1.3342 0.01622 0.00790 -0.1465 0.3308 1.0000
6.000 1.3580 0.01669 0.00836 -0.1458 0.3199 1.0000
6.250 1.3814 0.01726 0.00884 -0.1450 0.3115 1.0000
6.500 1.4056 0.01769 0.00931 -0.1443 0.3039 1.0000
6.750 1.4289 0.01832 0.00983 -0.1436 0.2972 1.0000
7.000 1.4529 0.01870 0.01034 -0.1429 0.2900 1.0000
7.250 1.4761 0.01925 0.01086 -0.1421 0.2834 1.0000
7.500 1.4993 0.01972 0.01140 -0.1413 0.2765 1.0000
7.750 1.5219 0.02019 0.01190 -0.1404 0.2691 1.0000
8.000 1.5445 0.02074 0.01250 -0.1396 0.2625 1.0000
8.250 1.5666 0.02116 0.01302 -0.1386 0.2553 1.0000
8.500 1.5880 0.02174 0.01361 -0.1376 0.2481 1.0000
8.750 1.6087 0.02211 0.01410 -0.1365 0.2393 1.0000
9.000 1.6291 0.02266 0.01472 -0.1353 0.2319 1.0000
9.250 1.6489 0.02307 0.01525 -0.1340 0.2232 1.0000
9.500 1.6681 0.02357 0.01586 -0.1327 0.2148 1.0000
9.750 1.6856 0.02407 0.01642 -0.1311 0.2050 1.0000
10.000 1.7036 0.02445 0.01698 -0.1295 0.1922 1.0000
10.250 1.7195 0.02494 0.01755 -0.1277 0.1756 1.0000
10.500 1.7324 0.02567 0.01825 -0.1256 0.1468 1.0000
10.750 1.7335 0.02722 0.01959 -0.1218 0.1173 1.0000
11.000 1.7315 0.02901 0.02127 -0.1177 0.0992 1.0000
11.250 1.7321 0.03072 0.02299 -0.1142 0.0881 1.0000
11.500 1.7325 0.03253 0.02480 -0.1110 0.0811 1.0000
11.750 1.7353 0.03426 0.02660 -0.1084 0.0755 1.0000
12.000 1.7327 0.03654 0.02888 -0.1057 0.0715 1.0000
12.250 1.7368 0.03837 0.03087 -0.1037 0.0680 1.0000
12.500 1.7374 0.04061 0.03319 -0.1019 0.0646 1.0000
12.750 1.7327 0.04346 0.03609 -0.1000 0.0619 1.0000
13.000 1.7311 0.04615 0.03891 -0.0984 0.0598 1.0000
13.250 1.7312 0.04875 0.04168 -0.0972 0.0576 1.0000
13.500 1.7290 0.05170 0.04475 -0.0961 0.0555 1.0000
13.750 1.7233 0.05511 0.04825 -0.0952 0.0535 1.0000
14.000 1.7137 0.05902 0.05220 -0.0942 0.0517 1.0000
14.250 1.7093 0.06247 0.05581 -0.0935 0.0500 1.0000
14.500 1.7047 0.06604 0.05957 -0.0932 0.0480 1.0000
14.750 1.6978 0.07000 0.06366 -0.0931 0.0460 1.0000
15.000 1.6886 0.07432 0.06806 -0.0932 0.0442 1.0000
15.250 1.6779 0.07856 0.07228 -0.0924 0.0420 1.0000
15.500 1.6700 0.08318 0.07716 -0.0932 0.0404 1.0000
15.750 1.6610 0.08800 0.08215 -0.0940 0.0384 1.0000
16.000 1.6524 0.09267 0.08689 -0.0948 0.0365 1.0000
16.250 1.6449 0.09639 0.09054 -0.0937 0.0340 1.0000
16.500 1.6347 0.10188 0.09629 -0.0955 0.0327 1.0000
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Polar data table (+)
Polar graphs
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