GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Reynolds number: 200,000 Max Cl/Cd: 85.78 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe803h-il-200000-n5.txt Download as CSV file: xf-goe803h-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2404 0.10382 0.10029 -0.0265 1.0000 0.0238
-7.750 -0.2372 0.10160 0.09812 -0.0258 1.0000 0.0240
-7.500 -0.2364 0.09974 0.09633 -0.0248 1.0000 0.0242
-7.250 -0.2263 0.09715 0.09377 -0.0263 0.9968 0.0246
-7.000 -0.2062 0.09376 0.09038 -0.0306 0.9881 0.0251
-6.500 -0.1647 0.08704 0.08367 -0.0395 0.9609 0.0266
-6.250 -0.1373 0.08352 0.08012 -0.0464 0.9474 0.0275
-6.000 -0.1006 0.07989 0.07643 -0.0571 0.9351 0.0279
-5.750 -0.0682 0.07569 0.07220 -0.0647 0.9252 0.0282
-5.500 -0.0467 0.07200 0.06849 -0.0662 0.9168 0.0288
-5.250 -0.0160 0.06860 0.06503 -0.0717 0.9071 0.0296
-5.000 0.0141 0.06541 0.06177 -0.0773 0.8952 0.0304
-4.750 0.0449 0.06229 0.05859 -0.0830 0.8832 0.0314
-4.500 0.0823 0.05914 0.05534 -0.0908 0.8713 0.0328
-4.250 0.1350 0.05563 0.05166 -0.1036 0.8599 0.0333
-4.000 0.1788 0.05213 0.04802 -0.1123 0.8484 0.0335
-3.750 0.1932 0.04919 0.04510 -0.1115 0.8376 0.0338
-3.500 0.2125 0.04699 0.04286 -0.1117 0.8275 0.0348
-3.250 0.2433 0.04471 0.04051 -0.1152 0.8168 0.0369
-3.000 0.2986 0.04163 0.03721 -0.1250 0.8071 0.0394
-2.750 0.3482 0.03856 0.03387 -0.1324 0.7971 0.0398
-2.500 0.3875 0.03574 0.03084 -0.1368 0.7855 0.0398
-2.250 0.4239 0.03305 0.02795 -0.1402 0.7737 0.0399
-2.000 0.4564 0.02937 0.02411 -0.1431 0.7620 0.0332
-1.500 0.5342 0.02435 0.01849 -0.1494 0.7370 0.0333
-1.250 0.5670 0.02264 0.01657 -0.1511 0.7236 0.0329
-1.000 0.6024 0.02074 0.01435 -0.1530 0.7103 0.0327
-0.750 0.6386 0.01875 0.01193 -0.1547 0.6983 0.0328
-0.500 0.6723 0.01727 0.01008 -0.1559 0.6874 0.0340
-0.250 0.7005 0.01697 0.00972 -0.1561 0.6769 0.0358
0.000 0.7319 0.01600 0.00845 -0.1566 0.6665 0.0368
0.250 0.7627 0.01510 0.00725 -0.1569 0.6553 0.0378
0.500 0.7927 0.01437 0.00623 -0.1570 0.6444 0.0394
0.750 0.8210 0.01403 0.00580 -0.1569 0.6332 0.0415
1.000 0.8487 0.01386 0.00555 -0.1567 0.6210 0.0450
1.250 0.8770 0.01353 0.00507 -0.1565 0.6080 0.0478
1.500 0.9047 0.01328 0.00483 -0.1564 0.5941 0.0511
1.750 0.9318 0.01326 0.00470 -0.1560 0.5790 0.0568
2.000 0.9590 0.01311 0.00457 -0.1558 0.5622 0.0628
2.250 0.9857 0.01313 0.00449 -0.1554 0.5432 0.0680
2.500 1.0121 0.01311 0.00444 -0.1551 0.5221 0.0741
2.750 1.0383 0.01322 0.00445 -0.1546 0.4985 0.0782
3.000 1.0642 0.01338 0.00450 -0.1541 0.4736 0.0835
3.250 1.0894 0.01361 0.00461 -0.1535 0.4460 0.0923
3.500 1.1143 0.01388 0.00479 -0.1529 0.4162 0.1081
4.000 1.1589 0.01351 0.00536 -0.1508 0.3605 1.0000
4.250 1.1826 0.01400 0.00565 -0.1500 0.3381 1.0000
4.500 1.2065 0.01447 0.00597 -0.1493 0.3201 1.0000
4.750 1.2304 0.01493 0.00630 -0.1486 0.3047 1.0000
5.000 1.2545 0.01536 0.00663 -0.1479 0.2917 1.0000
5.250 1.2789 0.01575 0.00697 -0.1472 0.2818 1.0000
5.500 1.3026 0.01619 0.00736 -0.1465 0.2735 1.0000
5.750 1.3271 0.01655 0.00771 -0.1459 0.2657 1.0000
6.000 1.3503 0.01702 0.00811 -0.1451 0.2579 1.0000
6.250 1.3746 0.01736 0.00849 -0.1444 0.2503 1.0000
6.500 1.3978 0.01781 0.00892 -0.1436 0.2435 1.0000
6.750 1.4215 0.01819 0.00934 -0.1429 0.2380 1.0000
7.000 1.4450 0.01859 0.00977 -0.1421 0.2323 1.0000
7.250 1.4675 0.01905 0.01024 -0.1413 0.2272 1.0000
7.500 1.4906 0.01946 0.01073 -0.1405 0.2225 1.0000
7.750 1.5136 0.01986 0.01121 -0.1396 0.2170 1.0000
8.000 1.5349 0.02037 0.01172 -0.1386 0.2104 1.0000
8.250 1.5576 0.02076 0.01221 -0.1377 0.2039 1.0000
8.500 1.5788 0.02123 0.01276 -0.1367 0.1967 1.0000
8.750 1.6003 0.02168 0.01329 -0.1357 0.1885 1.0000
9.000 1.6206 0.02218 0.01383 -0.1345 0.1767 1.0000
9.250 1.6402 0.02272 0.01440 -0.1333 0.1606 1.0000
9.500 1.6574 0.02345 0.01509 -0.1318 0.1416 1.0000
9.750 1.6716 0.02439 0.01595 -0.1298 0.1232 1.0000
10.000 1.6841 0.02546 0.01697 -0.1277 0.1067 1.0000
10.250 1.6944 0.02665 0.01811 -0.1252 0.0897 1.0000
10.500 1.7006 0.02794 0.01935 -0.1222 0.0731 1.0000
10.750 1.7054 0.02930 0.02069 -0.1191 0.0626 1.0000
11.000 1.7106 0.03067 0.02209 -0.1161 0.0566 1.0000
11.250 1.7156 0.03211 0.02358 -0.1134 0.0526 1.0000
11.500 1.7205 0.03361 0.02517 -0.1109 0.0496 1.0000
11.750 1.7233 0.03537 0.02702 -0.1085 0.0470 1.0000
12.000 1.7243 0.03739 0.02911 -0.1062 0.0450 1.0000
12.250 1.7288 0.03918 0.03108 -0.1044 0.0438 1.0000
12.500 1.7320 0.04118 0.03324 -0.1028 0.0425 1.0000
12.750 1.7335 0.04343 0.03564 -0.1013 0.0411 1.0000
13.000 1.7331 0.04599 0.03834 -0.0999 0.0397 1.0000
13.250 1.7304 0.04892 0.04139 -0.0988 0.0383 1.0000
13.500 1.7249 0.05229 0.04489 -0.0979 0.0370 1.0000
13.750 1.7169 0.05610 0.04883 -0.0972 0.0360 1.0000
14.000 1.7134 0.05946 0.05236 -0.0967 0.0352 1.0000
14.250 1.7107 0.06281 0.05589 -0.0965 0.0343 1.0000
14.500 1.7063 0.06648 0.05974 -0.0964 0.0333 1.0000
14.750 1.6999 0.07050 0.06393 -0.0965 0.0323 1.0000
15.000 1.6922 0.07488 0.06847 -0.0969 0.0313 1.0000
15.250 1.6829 0.07966 0.07341 -0.0977 0.0303 1.0000
15.500 1.6714 0.08495 0.07884 -0.0988 0.0295 1.0000
15.750 1.6578 0.09072 0.08475 -0.1003 0.0287 1.0000
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Polar data table (+)
Polar graphs
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