GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 803 (HACKLINGER) AIRFOIL (goe803h-il) Reynolds number: 100,000 Max Cl/Cd: 69.15 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe803h-il-100000.txt Download as CSV file: xf-goe803h-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.2559 0.10181 0.09734 -0.0196 1.0000 0.0497
-6.500 -0.2680 0.10194 0.09759 -0.0176 1.0000 0.0500
-6.250 -0.2787 0.10221 0.09796 -0.0167 1.0000 0.0502
-6.000 -0.2849 0.10247 0.09830 -0.0177 1.0000 0.0504
-5.750 -0.2835 0.10248 0.09836 -0.0213 1.0000 0.0506
-5.500 -0.2671 0.09858 0.09448 -0.0249 0.9973 0.0509
-5.250 -0.2551 0.09254 0.08846 -0.0220 0.9939 0.0517
-5.000 -0.2302 0.08817 0.08407 -0.0253 0.9879 0.0530
-4.750 -0.1973 0.08426 0.08013 -0.0318 0.9815 0.0548
-4.500 -0.1597 0.08051 0.07634 -0.0400 0.9744 0.0571
-4.250 -0.0710 0.07821 0.07381 -0.0669 0.9646 0.0610
-4.000 -0.0620 0.07272 0.06840 -0.0635 0.9604 0.0620
-3.750 -0.0398 0.06923 0.06490 -0.0653 0.9525 0.0638
-3.500 0.0038 0.06552 0.06114 -0.0730 0.9473 0.0671
-3.250 0.0991 0.06314 0.05840 -0.0966 0.9391 0.0728
-3.000 0.1140 0.05821 0.05358 -0.0953 0.9342 0.0743
-2.750 0.1449 0.05506 0.05044 -0.0984 0.9277 0.0775
-2.500 0.2226 0.05195 0.04704 -0.1140 0.9217 0.0869
-2.250 0.2544 0.04827 0.04343 -0.1163 0.9180 0.0917
-2.000 0.3184 0.04559 0.04049 -0.1273 0.9112 0.1019
-1.750 0.3565 0.04262 0.03753 -0.1309 0.9059 0.1091
-1.500 0.4175 0.03948 0.03425 -0.1396 0.9029 0.1224
-1.250 0.4782 0.03787 0.03230 -0.1478 0.8956 0.1465
-1.000 0.5190 0.03452 0.02903 -0.1512 0.8884 0.1659
-0.750 0.5634 0.03219 0.02661 -0.1547 0.8770 0.1979
-0.500 0.6057 0.02989 0.02425 -0.1574 0.8657 0.2449
0.250 0.6844 0.02503 0.01960 -0.1554 0.8316 0.4616
0.500 0.7751 0.02415 0.01721 -0.1666 0.8222 0.2080
0.750 0.8154 0.02251 0.01489 -0.1668 0.8106 0.1285
1.000 0.8468 0.02154 0.01370 -0.1667 0.7993 0.1263
1.250 0.8789 0.02062 0.01254 -0.1664 0.7892 0.1242
1.500 0.9068 0.02008 0.01185 -0.1656 0.7762 0.1265
1.750 0.9348 0.01958 0.01121 -0.1648 0.7633 0.1330
2.000 0.9624 0.01912 0.01072 -0.1640 0.7501 0.1429
2.250 0.9898 0.01865 0.01022 -0.1630 0.7366 0.1529
2.500 1.0169 0.01831 0.00983 -0.1620 0.7222 0.1702
2.750 1.0443 0.01807 0.00953 -0.1610 0.7067 0.1917
3.000 1.0677 0.01671 0.00944 -0.1595 0.6911 1.0000
3.250 1.0932 0.01684 0.00926 -0.1581 0.6729 1.0000
3.500 1.1181 0.01695 0.00921 -0.1568 0.6525 1.0000
3.750 1.1432 0.01702 0.00911 -0.1555 0.6308 1.0000
4.000 1.1671 0.01713 0.00909 -0.1540 0.6046 1.0000
4.250 1.1909 0.01728 0.00907 -0.1526 0.5755 1.0000
4.500 1.2142 0.01756 0.00914 -0.1511 0.5434 1.0000
4.750 1.2372 0.01801 0.00935 -0.1497 0.5121 1.0000
5.000 1.2606 0.01858 0.00964 -0.1485 0.4854 1.0000
5.250 1.2839 0.01920 0.01015 -0.1475 0.4611 1.0000
5.500 1.3078 0.01986 0.01064 -0.1466 0.4423 1.0000
5.750 1.3320 0.02053 0.01120 -0.1458 0.4265 1.0000
6.000 1.3560 0.02120 0.01181 -0.1451 0.4119 1.0000
6.250 1.3799 0.02188 0.01243 -0.1443 0.3986 1.0000
6.500 1.4041 0.02259 0.01308 -0.1436 0.3872 1.0000
6.750 1.4288 0.02332 0.01372 -0.1430 0.3768 1.0000
7.000 1.4517 0.02402 0.01452 -0.1422 0.3655 1.0000
7.250 1.4749 0.02476 0.01525 -0.1414 0.3547 1.0000
7.750 1.5203 0.02620 0.01674 -0.1396 0.3336 1.0000
8.000 1.5428 0.02700 0.01761 -0.1388 0.3241 1.0000
8.250 1.5657 0.02774 0.01833 -0.1380 0.3144 1.0000
8.500 1.5859 0.02854 0.01934 -0.1368 0.3047 1.0000
8.750 1.6093 0.02940 0.02014 -0.1361 0.2961 1.0000
9.000 1.6277 0.03010 0.02107 -0.1347 0.2855 1.0000
9.250 1.6459 0.03086 0.02196 -0.1332 0.2746 1.0000
9.500 1.6656 0.03158 0.02268 -0.1320 0.2641 1.0000
9.750 1.6818 0.03223 0.02351 -0.1302 0.2530 1.0000
10.000 1.6958 0.03297 0.02449 -0.1281 0.2414 1.0000
10.250 1.7094 0.03368 0.02533 -0.1260 0.2296 1.0000
10.500 1.7205 0.03436 0.02611 -0.1235 0.2168 1.0000
10.750 1.7262 0.03509 0.02699 -0.1202 0.2020 1.0000
11.000 1.7257 0.03596 0.02809 -0.1161 0.1844 1.0000
11.250 1.7195 0.03706 0.02929 -0.1113 0.1660 1.0000
11.500 1.7117 0.03863 0.03083 -0.1068 0.1499 1.0000
11.750 1.7054 0.04075 0.03287 -0.1032 0.1364 1.0000
12.000 1.7020 0.04316 0.03528 -0.1001 0.1260 1.0000
12.250 1.7005 0.04568 0.03774 -0.0975 0.1185 1.0000
12.500 1.7005 0.04812 0.04027 -0.0953 0.1118 1.0000
12.750 1.7031 0.05064 0.04276 -0.0932 0.1063 1.0000
13.000 1.7043 0.05322 0.04555 -0.0913 0.1016 1.0000
13.250 1.7077 0.05561 0.04790 -0.0896 0.0967 1.0000
13.500 1.7054 0.05859 0.05109 -0.0880 0.0924 1.0000
13.750 1.6993 0.06170 0.05440 -0.0868 0.0882 1.0000
14.000 1.7021 0.06421 0.05673 -0.0855 0.0829 1.0000
14.250 1.6897 0.06818 0.06109 -0.0848 0.0803 1.0000
14.500 1.6810 0.07196 0.06510 -0.0843 0.0769 1.0000
14.750 1.6807 0.07483 0.06791 -0.0836 0.0731 1.0000
15.000 1.6739 0.07885 0.07210 -0.0830 0.0702 1.0000
15.250 1.6601 0.08371 0.07728 -0.0833 0.0680 1.0000
15.500 1.6493 0.08827 0.08203 -0.0838 0.0654 1.0000
15.750 1.6561 0.09068 0.08425 -0.0823 0.0608 1.0000
16.000 1.6376 0.09660 0.09052 -0.0838 0.0598 1.0000
16.250 1.6191 0.10292 0.09715 -0.0858 0.0587 1.0000
16.500 1.6006 0.10956 0.10408 -0.0883 0.0576 1.0000
16.750 1.5817 0.11663 0.11141 -0.0915 0.0568 1.0000
17.000 1.5611 0.12444 0.11947 -0.0956 0.0563 1.0000
17.250 1.5344 0.13412 0.12942 -0.1016 0.0566 1.0000
17.500 1.5003 0.14642 0.14200 -0.1102 0.0579 1.0000
17.750 1.4642 0.16035 0.15614 -0.1202 0.0595 1.0000
18.000 1.4269 0.17616 0.17209 -0.1315 0.0613 1.0000
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Polar data table (+)
Polar graphs
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