GOE 535 AIRFOIL (goe535-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 535 AIRFOIL (goe535-il) Reynolds number: 100,000 Max Cl/Cd: 50.88 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe535-il-100000-n5.txt Download as CSV file: xf-goe535-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 535 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.2335 0.14937 0.14355 -0.0386 1.0000 0.0777
-13.250 -0.2345 0.14682 0.14104 -0.0396 1.0000 0.0782
-13.000 -0.2351 0.14418 0.13843 -0.0405 1.0000 0.0784
-12.750 -0.2335 0.14152 0.13582 -0.0410 1.0000 0.0784
-12.500 -0.2329 0.13879 0.13313 -0.0414 1.0000 0.0785
-12.250 -0.2312 0.13609 0.13047 -0.0416 1.0000 0.0785
-11.750 -0.2303 0.13075 0.12522 -0.0417 1.0000 0.0785
-11.250 -0.2325 0.12201 0.11653 -0.0418 1.0000 0.0645
-11.000 -0.2281 0.11998 0.11455 -0.0406 1.0000 0.0639
-10.750 -0.2285 0.11772 0.11236 -0.0398 1.0000 0.0633
-10.500 -0.2317 0.11544 0.11014 -0.0389 1.0000 0.0626
-10.250 -0.2273 0.11187 0.10660 -0.0408 0.9979 0.0621
-10.000 -0.2116 0.10680 0.10152 -0.0463 0.9918 0.0623
-9.750 -0.1985 0.10176 0.09647 -0.0516 0.9846 0.0629
-9.500 -0.1882 0.09626 0.09094 -0.0574 0.9772 0.0636
-9.250 -0.1786 0.09078 0.08545 -0.0628 0.9684 0.0637
-9.000 -0.1731 0.08511 0.07978 -0.0680 0.9580 0.0638
-8.750 -0.1772 0.07717 0.07181 -0.0756 0.9474 0.0642
-8.500 -0.1794 0.06991 0.06454 -0.0827 0.9353 0.0653
-8.250 -0.2572 0.04613 0.04017 -0.1123 0.9036 0.0663
-8.000 -0.2425 0.04117 0.03480 -0.1192 0.8899 0.0679
-7.750 -0.2208 0.03639 0.02940 -0.1253 0.8791 0.0697
-7.500 -0.2015 0.03319 0.02564 -0.1277 0.8651 0.0716
-7.250 -0.1680 0.03209 0.02452 -0.1293 0.8566 0.0733
-7.000 -0.1420 0.03078 0.02304 -0.1299 0.8434 0.0754
-6.750 -0.1133 0.02886 0.02061 -0.1315 0.8321 0.0783
-6.500 -0.0829 0.02772 0.01940 -0.1323 0.8207 0.0801
-6.250 -0.0545 0.02684 0.01842 -0.1326 0.8080 0.0825
-6.000 -0.0220 0.02571 0.01696 -0.1337 0.7973 0.0858
-5.750 0.0044 0.02484 0.01599 -0.1336 0.7834 0.0882
-5.500 0.0342 0.02416 0.01523 -0.1339 0.7715 0.0911
-5.250 0.0631 0.02344 0.01429 -0.1340 0.7587 0.0945
-5.000 0.0905 0.02276 0.01351 -0.1338 0.7458 0.0974
-4.750 0.1201 0.02221 0.01290 -0.1339 0.7343 0.1006
-4.500 0.1462 0.02174 0.01231 -0.1334 0.7211 0.1040
-4.250 0.1745 0.02123 0.01168 -0.1332 0.7096 0.1074
-4.000 0.2003 0.02083 0.01130 -0.1326 0.6968 0.1107
-3.750 0.2273 0.02048 0.01085 -0.1322 0.6853 0.1144
-3.500 0.2538 0.02016 0.01044 -0.1316 0.6735 0.1182
-3.250 0.2797 0.01985 0.01015 -0.1311 0.6621 0.1222
-3.000 0.3062 0.01961 0.00983 -0.1305 0.6508 0.1267
-2.750 0.3319 0.01939 0.00957 -0.1299 0.6395 0.1315
-2.500 0.3584 0.01917 0.00931 -0.1294 0.6288 0.1375
-2.250 0.3843 0.01901 0.00910 -0.1288 0.6181 0.1442
-2.000 0.4108 0.01880 0.00887 -0.1284 0.6080 0.1536
-1.750 0.4368 0.01860 0.00869 -0.1279 0.5978 0.1680
-1.500 0.4630 0.01835 0.00848 -0.1275 0.5878 0.1942
-1.250 0.4889 0.01803 0.00842 -0.1272 0.5786 0.2554
-1.000 0.5143 0.01806 0.00872 -0.1265 0.5691 0.3413
-0.750 0.5414 0.01826 0.00882 -0.1259 0.5610 0.3817
-0.500 0.5671 0.01847 0.00898 -0.1252 0.5515 0.4075
-0.250 0.5936 0.01869 0.00910 -0.1245 0.5438 0.4269
0.000 0.6190 0.01892 0.00932 -0.1237 0.5356 0.4428
0.250 0.6445 0.01918 0.00953 -0.1229 0.5277 0.4607
0.500 0.6710 0.01946 0.00968 -0.1222 0.5212 0.4791
0.750 0.6952 0.01974 0.01000 -0.1212 0.5132 0.4957
1.000 0.7200 0.02000 0.01025 -0.1202 0.5064 0.5108
1.250 0.7462 0.02024 0.01039 -0.1195 0.5005 0.5248
1.500 0.7705 0.02045 0.01061 -0.1186 0.4933 0.5352
1.750 0.7965 0.02061 0.01067 -0.1181 0.4869 0.5421
2.000 0.8234 0.02075 0.01071 -0.1177 0.4816 0.5474
2.250 0.8477 0.02094 0.01092 -0.1170 0.4750 0.5535
2.500 0.8731 0.02114 0.01106 -0.1164 0.4688 0.5595
2.750 0.8996 0.02130 0.01114 -0.1160 0.4634 0.5646
3.000 0.9253 0.02152 0.01135 -0.1155 0.4577 0.5710
3.250 0.9504 0.02178 0.01159 -0.1150 0.4515 0.5779
3.500 0.9766 0.02198 0.01175 -0.1146 0.4457 0.5836
3.750 1.0046 0.02221 0.01187 -0.1145 0.4407 0.5900
4.000 1.0279 0.02251 0.01222 -0.1137 0.4343 0.5973
4.250 1.0528 0.02273 0.01247 -0.1131 0.4281 0.6043
4.500 1.0794 0.02297 0.01262 -0.1128 0.4228 0.6131
4.750 1.1034 0.02326 0.01296 -0.1122 0.4168 0.6215
5.000 1.1265 0.02354 0.01331 -0.1114 0.4105 0.6308
5.250 1.1514 0.02378 0.01355 -0.1108 0.4049 0.6405
5.500 1.1771 0.02406 0.01381 -0.1105 0.3999 0.6521
5.750 1.1979 0.02439 0.01431 -0.1094 0.3937 0.6656
6.000 1.2207 0.02465 0.01467 -0.1085 0.3879 0.6844
6.500 1.2669 0.02490 0.01535 -0.1070 0.3775 1.0000
6.750 1.2865 0.02539 0.01587 -0.1058 0.3716 1.0000
7.000 1.3079 0.02582 0.01625 -0.1048 0.3665 1.0000
7.250 1.3312 0.02625 0.01658 -0.1041 0.3621 1.0000
7.500 1.3459 0.02685 0.01730 -0.1022 0.3561 1.0000
7.750 1.3632 0.02736 0.01783 -0.1006 0.3505 1.0000
8.000 1.3832 0.02779 0.01818 -0.0994 0.3458 1.0000
8.250 1.3972 0.02839 0.01884 -0.0974 0.3405 1.0000
8.500 1.4087 0.02904 0.01955 -0.0950 0.3348 1.0000
8.750 1.4235 0.02959 0.02011 -0.0931 0.3300 1.0000
9.000 1.4426 0.03008 0.02052 -0.0919 0.3259 1.0000
9.250 1.4486 0.03100 0.02158 -0.0891 0.3203 1.0000
9.500 1.4590 0.03176 0.02241 -0.0869 0.3151 1.0000
9.750 1.4735 0.03239 0.02301 -0.0852 0.3106 1.0000
10.000 1.4831 0.03329 0.02396 -0.0831 0.3058 1.0000
10.250 1.4885 0.03441 0.02519 -0.0808 0.3005 1.0000
10.500 1.4986 0.03534 0.02615 -0.0789 0.2959 1.0000
10.750 1.5148 0.03601 0.02677 -0.0777 0.2921 1.0000
11.000 1.5160 0.03756 0.02848 -0.0754 0.2873 1.0000
11.250 1.5194 0.03902 0.03004 -0.0734 0.2825 1.0000
11.500 1.5279 0.04016 0.03119 -0.0719 0.2780 1.0000
11.750 1.5383 0.04125 0.03226 -0.0706 0.2738 1.0000
12.000 1.5318 0.04359 0.03480 -0.0686 0.2686 1.0000
12.250 1.5332 0.04541 0.03668 -0.0671 0.2637 1.0000
12.500 1.5456 0.04640 0.03760 -0.0661 0.2594 1.0000
12.750 1.5375 0.04926 0.04063 -0.0648 0.2549 1.0000
13.000 1.5297 0.05220 0.04371 -0.0638 0.2497 1.0000
13.250 1.5343 0.05400 0.04552 -0.0630 0.2451 1.0000
13.500 1.5341 0.05641 0.04797 -0.0623 0.2407 1.0000
13.750 1.5154 0.06097 0.05274 -0.0620 0.2356 1.0000
14.000 1.5123 0.06389 0.05571 -0.0618 0.2308 1.0000
14.250 1.5220 0.06532 0.05708 -0.0613 0.2265 1.0000
14.500 1.4891 0.07233 0.06436 -0.0623 0.2214 1.0000
14.750 1.4777 0.07677 0.06890 -0.0629 0.2166 1.0000
15.250 1.4619 0.08513 0.07743 -0.0642 0.2087 1.0000
15.500 1.4204 0.09471 0.08724 -0.0672 0.2032 1.0000
15.750 1.4323 0.09603 0.08858 -0.0671 0.1997 1.0000
16.000 1.4460 0.09708 0.08960 -0.0668 0.1965 1.0000
16.250 1.3407 0.11832 0.11123 -0.0757 0.1867 1.0000
16.500 1.3738 0.11587 0.10875 -0.0739 0.1848 1.0000
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Polar data table (+)
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