GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Reynolds number: 100,000 Max Cl/Cd: 69.74 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe803h-il-100000-n5.txt Download as CSV file: xf-goe803h-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2358 0.10157 0.09681 -0.0242 1.0000 0.0382
-7.000 -0.2431 0.10072 0.09608 -0.0220 1.0000 0.0387
-6.750 -0.2501 0.10012 0.09560 -0.0207 0.9990 0.0392
-6.500 -0.2118 0.09787 0.09331 -0.0354 0.9862 0.0398
-6.250 -0.1913 0.09307 0.08853 -0.0380 0.9789 0.0402
-6.000 -0.1723 0.08850 0.08396 -0.0391 0.9726 0.0408
-5.750 -0.1486 0.08476 0.08021 -0.0430 0.9639 0.0416
-5.500 -0.1233 0.08130 0.07673 -0.0478 0.9538 0.0426
-5.250 -0.0944 0.07783 0.07323 -0.0537 0.9447 0.0438
-5.000 -0.0592 0.07420 0.06956 -0.0612 0.9376 0.0454
-4.750 -0.0146 0.07103 0.06630 -0.0726 0.9277 0.0470
-4.500 0.0480 0.06742 0.06253 -0.0893 0.9208 0.0477
-4.250 0.0558 0.06334 0.05851 -0.0857 0.9127 0.0486
-4.000 0.0856 0.05995 0.05508 -0.0891 0.9070 0.0505
-3.750 0.1210 0.05690 0.05198 -0.0949 0.8974 0.0526
-3.500 0.1779 0.05358 0.04847 -0.1065 0.8912 0.0557
-3.250 0.2466 0.05075 0.04531 -0.1208 0.8816 0.0568
-3.000 0.2652 0.04692 0.04155 -0.1208 0.8742 0.0577
-2.750 0.2916 0.04433 0.03894 -0.1226 0.8642 0.0592
-2.500 0.3279 0.04187 0.03639 -0.1267 0.8559 0.0621
-2.250 0.3849 0.03916 0.03337 -0.1357 0.8474 0.0687
-2.000 0.4113 0.03691 0.03112 -0.1369 0.8383 0.0713
-1.750 0.4500 0.03480 0.02886 -0.1406 0.8300 0.0751
-1.500 0.4991 0.03269 0.02639 -0.1464 0.8206 0.0815
-1.250 0.5415 0.02929 0.02269 -0.1496 0.8122 0.0547
-1.000 0.5777 0.02725 0.02041 -0.1519 0.7997 0.0520
-0.750 0.6141 0.02558 0.01842 -0.1536 0.7856 0.0537
-0.500 0.6492 0.02388 0.01637 -0.1549 0.7695 0.0526
-0.250 0.6834 0.02237 0.01446 -0.1558 0.7530 0.0516
0.000 0.7163 0.02114 0.01287 -0.1564 0.7384 0.0517
0.250 0.7479 0.02023 0.01162 -0.1568 0.7266 0.0537
0.500 0.7793 0.01955 0.01051 -0.1569 0.7164 0.0569
0.750 0.8084 0.01878 0.00963 -0.1570 0.7046 0.0586
1.000 0.8368 0.01825 0.00899 -0.1568 0.6934 0.0610
1.250 0.8650 0.01790 0.00846 -0.1565 0.6820 0.0665
1.500 0.8928 0.01746 0.00797 -0.1562 0.6694 0.0714
1.750 0.9200 0.01724 0.00769 -0.1558 0.6556 0.0790
2.000 0.9472 0.01695 0.00739 -0.1554 0.6413 0.0853
2.250 0.9738 0.01685 0.00720 -0.1548 0.6265 0.0939
2.500 1.0006 0.01674 0.00704 -0.1543 0.6111 0.1004
2.750 1.0272 0.01673 0.00700 -0.1537 0.5945 0.1126
3.000 1.0536 0.01675 0.00697 -0.1532 0.5767 0.1273
3.250 1.0781 0.01575 0.00719 -0.1526 0.5578 0.7267
3.500 1.1010 0.01583 0.00716 -0.1511 0.5358 1.0000
3.750 1.1256 0.01614 0.00726 -0.1501 0.5115 1.0000
4.000 1.1497 0.01650 0.00743 -0.1492 0.4849 1.0000
4.250 1.1734 0.01691 0.00765 -0.1482 0.4580 1.0000
4.500 1.1967 0.01737 0.00795 -0.1472 0.4319 1.0000
4.750 1.2199 0.01787 0.00829 -0.1463 0.4079 1.0000
5.000 1.2427 0.01842 0.00867 -0.1453 0.3875 1.0000
5.250 1.2655 0.01899 0.00911 -0.1443 0.3703 1.0000
5.500 1.2883 0.01956 0.00961 -0.1434 0.3558 1.0000
5.750 1.3114 0.02014 0.01012 -0.1425 0.3440 1.0000
6.000 1.3343 0.02074 0.01065 -0.1416 0.3339 1.0000
6.250 1.3565 0.02137 0.01120 -0.1406 0.3225 1.0000
6.500 1.3788 0.02195 0.01180 -0.1397 0.3104 1.0000
6.750 1.4007 0.02256 0.01238 -0.1387 0.2995 1.0000
7.000 1.4220 0.02323 0.01297 -0.1377 0.2900 1.0000
7.250 1.4441 0.02378 0.01362 -0.1368 0.2802 1.0000
7.500 1.4651 0.02444 0.01428 -0.1357 0.2717 1.0000
7.750 1.4865 0.02502 0.01496 -0.1347 0.2632 1.0000
8.000 1.5072 0.02570 0.01565 -0.1336 0.2564 1.0000
8.250 1.5284 0.02630 0.01640 -0.1326 0.2494 1.0000
8.500 1.5482 0.02700 0.01713 -0.1314 0.2430 1.0000
8.750 1.5683 0.02763 0.01795 -0.1302 0.2356 1.0000
9.000 1.5867 0.02832 0.01873 -0.1288 0.2280 1.0000
9.250 1.6051 0.02901 0.01957 -0.1274 0.2203 1.0000
9.500 1.6213 0.02974 0.02039 -0.1258 0.2113 1.0000
9.750 1.6377 0.03043 0.02131 -0.1241 0.2013 1.0000
10.000 1.6522 0.03122 0.02221 -0.1223 0.1924 1.0000
10.250 1.6660 0.03201 0.02318 -0.1203 0.1814 1.0000
10.500 1.6783 0.03285 0.02419 -0.1182 0.1681 1.0000
10.750 1.6858 0.03384 0.02527 -0.1155 0.1530 1.0000
11.000 1.6901 0.03511 0.02658 -0.1125 0.1370 1.0000
11.250 1.6915 0.03674 0.02819 -0.1096 0.1227 1.0000
11.500 1.6906 0.03871 0.03017 -0.1067 0.1105 1.0000
11.750 1.6882 0.04099 0.03247 -0.1041 0.1001 1.0000
12.000 1.6870 0.04332 0.03492 -0.1018 0.0909 1.0000
12.250 1.6831 0.04602 0.03770 -0.0998 0.0844 1.0000
12.500 1.6797 0.04882 0.04062 -0.0981 0.0789 1.0000
12.750 1.6729 0.05210 0.04401 -0.0967 0.0752 1.0000
13.000 1.6680 0.05535 0.04742 -0.0956 0.0722 1.0000
13.250 1.6618 0.05887 0.05111 -0.0948 0.0694 1.0000
13.500 1.6532 0.06284 0.05520 -0.0944 0.0669 1.0000
13.750 1.6417 0.06731 0.05978 -0.0943 0.0649 1.0000
14.000 1.6313 0.07180 0.06441 -0.0944 0.0629 1.0000
14.250 1.6216 0.07635 0.06916 -0.0948 0.0608 1.0000
14.500 1.6101 0.08135 0.07432 -0.0955 0.0589 1.0000
14.750 1.5973 0.08673 0.07986 -0.0967 0.0573 1.0000
15.000 1.5838 0.09242 0.08566 -0.0981 0.0559 1.0000
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Polar data table (+)
Polar graphs
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