GOE 497 AIRFOIL (goe497-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 497 AIRFOIL (goe497-il) Reynolds number: 100,000 Max Cl/Cd: 60.48 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe497-il-100000-n5.txt Download as CSV file: xf-goe497-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 497 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3152 0.09161 0.08646 -0.0607 0.9835 0.0574
-9.250 -0.3176 0.08507 0.07993 -0.0662 0.9762 0.0579
-8.750 -0.4273 0.04075 0.03453 -0.1174 0.9388 0.0598
-8.500 -0.4033 0.03902 0.03273 -0.1192 0.9333 0.0611
-8.250 -0.3742 0.03654 0.03000 -0.1228 0.9295 0.0627
-8.000 -0.3526 0.03432 0.02747 -0.1246 0.9232 0.0644
-7.750 -0.3269 0.03203 0.02477 -0.1268 0.9175 0.0670
-7.500 -0.2947 0.02979 0.02206 -0.1297 0.9141 0.0697
-7.250 -0.2599 0.02864 0.02086 -0.1319 0.9118 0.0718
-7.000 -0.2412 0.02781 0.01992 -0.1309 0.9037 0.0737
-6.750 -0.2095 0.02669 0.01856 -0.1324 0.8998 0.0772
-6.500 -0.1751 0.02553 0.01715 -0.1343 0.8969 0.0810
-6.250 -0.1489 0.02490 0.01651 -0.1345 0.8912 0.0842
-6.000 -0.1216 0.02417 0.01564 -0.1347 0.8855 0.0881
-5.750 -0.0886 0.02336 0.01466 -0.1360 0.8821 0.0935
-5.500 -0.0540 0.02273 0.01400 -0.1376 0.8794 0.0997
-5.250 -0.0323 0.02229 0.01339 -0.1366 0.8718 0.1058
-5.000 -0.0017 0.02174 0.01288 -0.1374 0.8673 0.1133
-4.750 0.0327 0.02114 0.01219 -0.1387 0.8641 0.1231
-4.500 0.0584 0.02083 0.01184 -0.1385 0.8580 0.1328
-4.250 0.0865 0.02047 0.01149 -0.1386 0.8522 0.1434
-4.000 0.1210 0.02001 0.01099 -0.1398 0.8482 0.1564
-3.750 0.1483 0.01974 0.01068 -0.1397 0.8414 0.1693
-3.500 0.1778 0.01945 0.01036 -0.1398 0.8348 0.1838
-3.250 0.2130 0.01906 0.00997 -0.1410 0.8306 0.2011
-3.000 0.2367 0.01895 0.00986 -0.1402 0.8219 0.2171
-2.750 0.2690 0.01866 0.00956 -0.1407 0.8161 0.2356
-2.500 0.2978 0.01845 0.00935 -0.1407 0.8091 0.2529
-2.250 0.3255 0.01830 0.00919 -0.1405 0.8016 0.2701
-2.000 0.3589 0.01806 0.00892 -0.1412 0.7972 0.2882
-1.750 0.3821 0.01808 0.00894 -0.1403 0.7891 0.3033
-1.500 0.4121 0.01793 0.00879 -0.1404 0.7833 0.3205
-1.250 0.4417 0.01782 0.00867 -0.1405 0.7776 0.3376
-1.000 0.4668 0.01783 0.00869 -0.1399 0.7697 0.3538
-0.750 0.4984 0.01767 0.00853 -0.1403 0.7647 0.3717
-0.500 0.5225 0.01773 0.00863 -0.1394 0.7568 0.3893
-0.250 0.5513 0.01765 0.00858 -0.1394 0.7504 0.4089
0.000 0.5789 0.01760 0.00857 -0.1391 0.7435 0.4283
0.250 0.6050 0.01758 0.00858 -0.1385 0.7356 0.4464
0.500 0.6351 0.01745 0.00845 -0.1386 0.7293 0.4654
0.750 0.6595 0.01750 0.00855 -0.1378 0.7205 0.4836
1.000 0.6913 0.01735 0.00840 -0.1382 0.7147 0.5052
1.250 0.7144 0.01743 0.00855 -0.1372 0.7052 0.5256
1.500 0.7453 0.01726 0.00843 -0.1374 0.6986 0.5511
1.750 0.7686 0.01728 0.00856 -0.1364 0.6883 0.5787
2.000 0.7967 0.01710 0.00849 -0.1360 0.6795 0.6175
2.250 0.8204 0.01693 0.00855 -0.1349 0.6689 0.6782
2.500 0.8440 0.01643 0.00848 -0.1333 0.6583 1.0000
2.750 0.8737 0.01648 0.00839 -0.1333 0.6480 1.0000
3.000 0.8988 0.01665 0.00850 -0.1327 0.6357 1.0000
3.250 0.9242 0.01683 0.00861 -0.1321 0.6237 1.0000
3.500 0.9511 0.01698 0.00868 -0.1317 0.6125 1.0000
3.750 0.9771 0.01714 0.00876 -0.1311 0.5999 1.0000
4.000 1.0003 0.01738 0.00896 -0.1302 0.5859 1.0000
4.250 1.0241 0.01762 0.00918 -0.1293 0.5730 1.0000
4.500 1.0488 0.01786 0.00938 -0.1286 0.5616 1.0000
4.750 1.0737 0.01811 0.00958 -0.1280 0.5506 1.0000
5.000 1.0965 0.01842 0.00991 -0.1270 0.5388 1.0000
5.250 1.1201 0.01871 0.01020 -0.1262 0.5279 1.0000
5.500 1.1445 0.01900 0.01044 -0.1255 0.5175 1.0000
5.750 1.1666 0.01934 0.01080 -0.1244 0.5059 1.0000
6.000 1.1891 0.01969 0.01115 -0.1234 0.4948 1.0000
6.250 1.2121 0.02004 0.01146 -0.1225 0.4842 1.0000
6.500 1.2340 0.02044 0.01187 -0.1214 0.4733 1.0000
6.750 1.2551 0.02086 0.01231 -0.1203 0.4622 1.0000
7.000 1.2754 0.02130 0.01271 -0.1189 0.4494 1.0000
7.250 1.2943 0.02178 0.01313 -0.1174 0.4352 1.0000
7.500 1.3111 0.02231 0.01360 -0.1155 0.4198 1.0000
7.750 1.3258 0.02287 0.01418 -0.1133 0.4041 1.0000
8.000 1.3383 0.02343 0.01477 -0.1109 0.3890 1.0000
8.250 1.3499 0.02402 0.01540 -0.1083 0.3740 1.0000
8.500 1.3609 0.02466 0.01607 -0.1057 0.3589 1.0000
8.750 1.3718 0.02534 0.01681 -0.1032 0.3439 1.0000
9.000 1.3824 0.02607 0.01758 -0.1008 0.3289 1.0000
9.250 1.3920 0.02688 0.01841 -0.0983 0.3134 1.0000
9.500 1.4006 0.02779 0.01931 -0.0958 0.2979 1.0000
9.750 1.4082 0.02881 0.02031 -0.0934 0.2832 1.0000
10.000 1.4153 0.02993 0.02143 -0.0910 0.2696 1.0000
10.250 1.4216 0.03118 0.02265 -0.0887 0.2568 1.0000
10.500 1.4265 0.03257 0.02401 -0.0864 0.2445 1.0000
10.750 1.4322 0.03400 0.02548 -0.0843 0.2317 1.0000
11.000 1.4371 0.03554 0.02706 -0.0823 0.2193 1.0000
11.250 1.4408 0.03723 0.02878 -0.0803 0.2072 1.0000
11.500 1.4432 0.03909 0.03068 -0.0785 0.1949 1.0000
11.750 1.4459 0.04100 0.03267 -0.0768 0.1815 1.0000
12.000 1.4477 0.04306 0.03480 -0.0752 0.1678 1.0000
12.250 1.4484 0.04532 0.03709 -0.0738 0.1552 1.0000
12.500 1.4477 0.04777 0.03956 -0.0724 0.1449 1.0000
12.750 1.4459 0.05043 0.04221 -0.0713 0.1371 1.0000
13.000 1.4453 0.05310 0.04491 -0.0702 0.1300 1.0000
13.250 1.4435 0.05596 0.04779 -0.0694 0.1245 1.0000
13.500 1.4442 0.05868 0.05060 -0.0687 0.1186 1.0000
13.750 1.4416 0.06181 0.05373 -0.0681 0.1136 1.0000
14.000 1.4422 0.06471 0.05672 -0.0677 0.1083 1.0000
14.250 1.4408 0.06792 0.06001 -0.0676 0.1031 1.0000
14.500 1.4376 0.07137 0.06345 -0.0675 0.0985 1.0000
14.750 1.4376 0.07464 0.06691 -0.0676 0.0935 1.0000
15.000 1.4350 0.07828 0.07063 -0.0680 0.0893 1.0000
15.250 1.4324 0.08193 0.07432 -0.0684 0.0858 1.0000
15.500 1.4321 0.08545 0.07805 -0.0689 0.0820 1.0000
15.750 1.4299 0.08931 0.08205 -0.0697 0.0786 1.0000
16.000 1.4265 0.09332 0.08610 -0.0706 0.0757 1.0000
16.250 1.4244 0.09730 0.09025 -0.0716 0.0724 1.0000
16.500 1.4210 0.10159 0.09472 -0.0729 0.0690 1.0000
16.750 1.4161 0.10615 0.09938 -0.0744 0.0661 1.0000
17.000 1.4116 0.11067 0.10397 -0.0760 0.0632 1.0000
17.250 1.4070 0.11543 0.10895 -0.0779 0.0598 1.0000
17.500 1.4011 0.12040 0.11404 -0.0801 0.0569 1.0000
17.750 1.3955 0.12526 0.11893 -0.0823 0.0544 1.0000
18.000 1.3895 0.13048 0.12439 -0.0847 0.0511 1.0000
18.250 1.3832 0.13573 0.12974 -0.0874 0.0484 1.0000
18.500 1.3778 0.14075 0.13477 -0.0900 0.0463 1.0000
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