GOE 802 B AIRFOIL (goe802b-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 802 B AIRFOIL (goe802b-il) Reynolds number: 100,000 Max Cl/Cd: 53.84 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe802b-il-100000.txt Download as CSV file: xf-goe802b-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 802 B 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3081 0.09884 0.09433 -0.0255 1.0000 0.0602
-7.500 -0.3230 0.09815 0.09374 -0.0239 1.0000 0.0604
-7.250 -0.3347 0.09727 0.09293 -0.0237 1.0000 0.0606
-6.750 -0.3438 0.09264 0.08842 -0.0211 1.0000 0.0611
-6.500 -0.3464 0.09017 0.08600 -0.0193 1.0000 0.0616
-6.250 -0.3484 0.08794 0.08380 -0.0184 1.0000 0.0623
-6.000 -0.3487 0.08572 0.08162 -0.0182 1.0000 0.0632
-5.750 -0.3469 0.08344 0.07935 -0.0187 1.0000 0.0642
-5.500 -0.3022 0.07902 0.07478 -0.0306 0.9932 0.0666
-5.250 -0.2694 0.07441 0.07010 -0.0370 0.9860 0.0675
-5.000 -0.2338 0.07018 0.06580 -0.0431 0.9801 0.0699
-4.750 -0.1854 0.06661 0.06195 -0.0532 0.9706 0.0725
-4.500 -0.1516 0.06217 0.05749 -0.0577 0.9653 0.0740
-4.250 -0.1161 0.05894 0.05410 -0.0627 0.9554 0.0763
-4.000 -0.0620 0.05533 0.05018 -0.0711 0.9497 0.0777
-3.750 -0.0346 0.05211 0.04690 -0.0735 0.9391 0.0789
-3.500 0.0165 0.04905 0.04354 -0.0800 0.9335 0.0813
-3.250 0.0529 0.04660 0.04083 -0.0832 0.9226 0.0823
-3.000 0.0987 0.04320 0.03728 -0.0883 0.9169 0.0846
-2.500 0.1869 0.03840 0.03191 -0.0958 0.9003 0.0875
-2.250 0.2296 0.03619 0.02943 -0.0989 0.8927 0.0897
-2.000 0.2700 0.03536 0.02812 -0.1005 0.8823 0.0912
-1.750 0.3044 0.03263 0.02534 -0.1022 0.8732 0.0927
-1.500 0.3409 0.03151 0.02387 -0.1031 0.8633 0.0955
-1.250 0.3707 0.02975 0.02197 -0.1033 0.8516 0.0978
-1.000 0.4076 0.02898 0.02079 -0.1038 0.8431 0.1007
-0.750 0.4339 0.02735 0.01908 -0.1033 0.8294 0.1025
-0.500 0.4642 0.02673 0.01815 -0.1028 0.8178 0.1055
-0.250 0.4946 0.02518 0.01645 -0.1026 0.8072 0.1092
0.000 0.5211 0.02433 0.01538 -0.1018 0.7929 0.1148
0.250 0.5485 0.02269 0.01358 -0.1013 0.7805 0.1270
0.500 0.5779 0.02129 0.01208 -0.1008 0.7700 0.1352
0.750 0.6032 0.02025 0.01118 -0.1000 0.7552 0.1437
1.000 0.6288 0.01949 0.01056 -0.0991 0.7410 0.1515
1.250 0.6548 0.01896 0.01005 -0.0979 0.7276 0.1566
1.500 0.6831 0.01847 0.00947 -0.0971 0.7158 0.1617
1.750 0.7095 0.01833 0.00925 -0.0963 0.7004 0.1662
2.000 0.7363 0.01825 0.00911 -0.0956 0.6856 0.1696
2.250 0.7633 0.01787 0.00908 -0.0951 0.6714 0.3049
2.500 0.7918 0.01659 0.00896 -0.0943 0.6582 1.0000
2.750 0.8190 0.01677 0.00888 -0.0935 0.6453 1.0000
3.000 0.8444 0.01709 0.00907 -0.0929 0.6308 1.0000
3.250 0.8700 0.01741 0.00927 -0.0923 0.6171 1.0000
3.500 0.8964 0.01772 0.00942 -0.0919 0.6045 1.0000
3.750 0.9229 0.01804 0.00961 -0.0914 0.5924 1.0000
4.000 0.9476 0.01845 0.00999 -0.0909 0.5787 1.0000
4.250 0.9727 0.01879 0.01024 -0.0903 0.5651 1.0000
4.500 0.9984 0.01907 0.01038 -0.0896 0.5516 1.0000
4.750 1.0239 0.01936 0.01056 -0.0890 0.5382 1.0000
5.000 1.0477 0.01978 0.01102 -0.0884 0.5252 1.0000
5.250 1.0729 0.02020 0.01139 -0.0879 0.5141 1.0000
5.500 1.0984 0.02058 0.01171 -0.0875 0.5030 1.0000
5.750 1.1219 0.02106 0.01227 -0.0869 0.4914 1.0000
6.000 1.1481 0.02146 0.01256 -0.0865 0.4815 1.0000
6.250 1.1710 0.02191 0.01310 -0.0858 0.4697 1.0000
6.500 1.1950 0.02237 0.01358 -0.0852 0.4587 1.0000
6.750 1.2205 0.02271 0.01386 -0.0847 0.4479 1.0000
7.000 1.2420 0.02318 0.01446 -0.0838 0.4352 1.0000
7.250 1.2653 0.02363 0.01492 -0.0831 0.4236 1.0000
7.500 1.2905 0.02397 0.01516 -0.0825 0.4118 1.0000
7.750 1.3106 0.02437 0.01567 -0.0813 0.3970 1.0000
8.000 1.3308 0.02473 0.01607 -0.0801 0.3813 1.0000
8.250 1.3505 0.02511 0.01645 -0.0788 0.3650 1.0000
8.500 1.3696 0.02556 0.01691 -0.0775 0.3486 1.0000
8.750 1.3880 0.02609 0.01747 -0.0761 0.3323 1.0000
9.000 1.4061 0.02672 0.01810 -0.0747 0.3167 1.0000
9.250 1.4239 0.02742 0.01878 -0.0733 0.3017 1.0000
9.500 1.4417 0.02814 0.01945 -0.0719 0.2875 1.0000
9.750 1.4573 0.02890 0.02024 -0.0702 0.2737 1.0000
10.000 1.4710 0.02975 0.02122 -0.0683 0.2602 1.0000
10.250 1.4842 0.03059 0.02211 -0.0664 0.2477 1.0000
10.500 1.4970 0.03140 0.02287 -0.0645 0.2360 1.0000
10.750 1.5068 0.03225 0.02376 -0.0623 0.2245 1.0000
11.000 1.5145 0.03330 0.02490 -0.0598 0.2136 1.0000
11.250 1.5229 0.03433 0.02589 -0.0575 0.2041 1.0000
11.500 1.5268 0.03547 0.02714 -0.0546 0.1951 1.0000
11.750 1.5342 0.03678 0.02845 -0.0525 0.1869 1.0000
12.000 1.5393 0.03812 0.02989 -0.0502 0.1791 1.0000
12.250 1.5490 0.03957 0.03132 -0.0486 0.1722 1.0000
12.500 1.5523 0.04119 0.03314 -0.0464 0.1660 1.0000
12.750 1.5634 0.04257 0.03450 -0.0451 0.1601 1.0000
13.000 1.5662 0.04442 0.03653 -0.0432 0.1548 1.0000
13.250 1.5654 0.04629 0.03858 -0.0413 0.1494 1.0000
13.500 1.5722 0.04779 0.04004 -0.0400 0.1439 1.0000
13.750 1.5698 0.05007 0.04255 -0.0384 0.1395 1.0000
14.000 1.5649 0.05250 0.04521 -0.0370 0.1349 1.0000
14.250 1.5649 0.05457 0.04736 -0.0360 0.1302 1.0000
14.500 1.5632 0.05700 0.04988 -0.0351 0.1257 1.0000
14.750 1.5518 0.06045 0.05363 -0.0345 0.1215 1.0000
15.000 1.5450 0.06355 0.05688 -0.0343 0.1170 1.0000
15.250 1.5415 0.06632 0.05963 -0.0341 0.1120 1.0000
15.500 1.5248 0.07110 0.06476 -0.0348 0.1081 1.0000
15.750 1.5120 0.07557 0.06941 -0.0357 0.1032 1.0000
16.000 1.5026 0.07965 0.07346 -0.0367 0.0978 1.0000
16.250 1.4832 0.08585 0.07999 -0.0388 0.0933 1.0000
16.500 1.4683 0.09141 0.08564 -0.0410 0.0880 1.0000
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Polar data table (+)
Polar graphs
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