GOE 599 AIRFOIL (goe599-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 599 AIRFOIL (goe599-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.16 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe599-il-1000000-n5.txt Download as CSV file: xf-goe599-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 599 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.9655 0.08113 0.07891 -0.0290 1.0000 0.0036
-14.750 -1.0193 0.06641 0.06403 -0.0376 1.0000 0.0034
-14.500 -1.0704 0.05076 0.04812 -0.0497 1.0000 0.0034
-14.250 -1.0908 0.04243 0.03957 -0.0573 1.0000 0.0034
-14.000 -1.1027 0.03723 0.03418 -0.0613 1.0000 0.0034
-13.750 -1.1093 0.03408 0.03087 -0.0621 1.0000 0.0034
-13.500 -1.1148 0.03187 0.02851 -0.0605 1.0000 0.0034
-13.250 -1.1147 0.03026 0.02677 -0.0583 1.0000 0.0035
-13.000 -1.1123 0.02848 0.02484 -0.0563 1.0000 0.0035
-12.750 -1.1102 0.02668 0.02286 -0.0538 1.0000 0.0036
-12.500 -1.1028 0.02530 0.02135 -0.0516 1.0000 0.0037
-12.250 -1.0921 0.02419 0.02013 -0.0496 1.0000 0.0038
-12.000 -1.0798 0.02320 0.01904 -0.0477 1.0000 0.0039
-11.750 -1.0661 0.02230 0.01805 -0.0459 1.0000 0.0040
-11.500 -1.0515 0.02145 0.01709 -0.0442 1.0000 0.0041
-11.250 -1.0340 0.02061 0.01615 -0.0430 0.9998 0.0042
-11.000 -1.0087 0.01971 0.01514 -0.0434 0.9989 0.0044
-10.750 -0.9832 0.01886 0.01418 -0.0438 0.9980 0.0045
-10.500 -0.9568 0.01806 0.01328 -0.0443 0.9970 0.0047
-10.250 -0.9293 0.01729 0.01240 -0.0449 0.9960 0.0048
-10.000 -0.9010 0.01659 0.01159 -0.0456 0.9951 0.0050
-9.750 -0.8726 0.01595 0.01086 -0.0463 0.9942 0.0051
-9.500 -0.8461 0.01523 0.01004 -0.0466 0.9927 0.0053
-9.250 -0.8190 0.01453 0.00926 -0.0470 0.9912 0.0057
-9.000 -0.7906 0.01399 0.00867 -0.0476 0.9900 0.0060
-8.750 -0.7613 0.01352 0.00815 -0.0483 0.9889 0.0064
-8.500 -0.7315 0.01308 0.00766 -0.0491 0.9879 0.0068
-8.250 -0.7011 0.01265 0.00717 -0.0500 0.9870 0.0072
-8.000 -0.6701 0.01223 0.00669 -0.0510 0.9862 0.0076
-7.750 -0.6399 0.01171 0.00613 -0.0519 0.9853 0.0084
-7.500 -0.6129 0.01134 0.00573 -0.0519 0.9827 0.0091
-7.250 -0.5839 0.01100 0.00535 -0.0524 0.9806 0.0099
-7.000 -0.5540 0.01069 0.00500 -0.0531 0.9787 0.0106
-6.750 -0.5239 0.01032 0.00461 -0.0538 0.9769 0.0124
-6.500 -0.4936 0.01001 0.00431 -0.0545 0.9751 0.0143
-6.250 -0.4672 0.00975 0.00403 -0.0543 0.9710 0.0162
-6.000 -0.4390 0.00948 0.00379 -0.0545 0.9675 0.0197
-5.750 -0.4095 0.00927 0.00355 -0.0550 0.9644 0.0222
-5.500 -0.3822 0.00905 0.00332 -0.0549 0.9600 0.0248
-5.250 -0.3548 0.00882 0.00310 -0.0549 0.9547 0.0278
-5.000 -0.3261 0.00863 0.00289 -0.0551 0.9502 0.0304
-4.750 -0.2991 0.00848 0.00270 -0.0550 0.9432 0.0317
-4.500 -0.2712 0.00828 0.00248 -0.0550 0.9363 0.0354
-4.250 -0.2440 0.00808 0.00229 -0.0549 0.9270 0.0396
-4.000 -0.2166 0.00788 0.00209 -0.0548 0.9158 0.0480
-3.750 -0.1899 0.00756 0.00189 -0.0546 0.9005 0.0820
-3.500 -0.1627 0.00746 0.00175 -0.0544 0.8815 0.0944
-3.250 -0.1358 0.00739 0.00161 -0.0542 0.8596 0.1032
-3.000 -0.1092 0.00740 0.00149 -0.0538 0.8345 0.1075
-2.750 -0.0825 0.00739 0.00139 -0.0536 0.8110 0.1137
-2.500 -0.0552 0.00736 0.00131 -0.0535 0.7946 0.1207
-2.250 -0.0275 0.00721 0.00121 -0.0535 0.7852 0.1421
-2.000 -0.0005 0.00691 0.00112 -0.0535 0.7771 0.2122
-1.750 0.0274 0.00675 0.00106 -0.0537 0.7696 0.2457
-1.500 0.0553 0.00665 0.00101 -0.0538 0.7618 0.2711
-1.250 0.0829 0.00657 0.00097 -0.0538 0.7472 0.2999
-1.000 0.1095 0.00645 0.00092 -0.0536 0.7195 0.3491
-0.750 0.1363 0.00641 0.00088 -0.0535 0.6910 0.3837
-0.500 0.1625 0.00643 0.00087 -0.0532 0.6498 0.4204
-0.250 0.1890 0.00647 0.00088 -0.0530 0.6126 0.4552
0.000 0.2150 0.00655 0.00091 -0.0528 0.5675 0.4969
0.250 0.2409 0.00673 0.00097 -0.0525 0.5130 0.5263
0.500 0.2663 0.00702 0.00105 -0.0522 0.4449 0.5499
0.750 0.2920 0.00729 0.00115 -0.0520 0.3851 0.5717
1.000 0.3184 0.00749 0.00124 -0.0518 0.3434 0.5920
1.500 0.3707 0.00791 0.00145 -0.0515 0.2532 0.6372
1.750 0.3934 0.00855 0.00172 -0.0508 0.1366 0.6611
2.000 0.4182 0.00894 0.00192 -0.0504 0.0648 0.6872
2.250 0.4449 0.00898 0.00204 -0.0502 0.0579 0.7258
2.500 0.4703 0.00889 0.00218 -0.0497 0.0529 0.7996
2.750 0.4914 0.00870 0.00235 -0.0480 0.0521 0.9064
3.000 0.5195 0.00874 0.00250 -0.0478 0.0509 0.9722
3.250 0.5549 0.00889 0.00265 -0.0496 0.0494 0.9904
3.500 0.5884 0.00907 0.00282 -0.0510 0.0476 0.9986
3.750 0.6155 0.00925 0.00298 -0.0509 0.0459 1.0000
4.000 0.6412 0.00944 0.00317 -0.0505 0.0445 1.0000
4.250 0.6670 0.00965 0.00339 -0.0502 0.0431 1.0000
4.500 0.6925 0.00991 0.00366 -0.0498 0.0417 1.0000
4.750 0.7181 0.01017 0.00395 -0.0494 0.0409 1.0000
5.000 0.7444 0.01034 0.00413 -0.0492 0.0406 1.0000
5.250 0.7709 0.01048 0.00428 -0.0490 0.0398 1.0000
5.500 0.7974 0.01063 0.00443 -0.0488 0.0385 1.0000
5.750 0.8237 0.01081 0.00461 -0.0487 0.0369 1.0000
6.000 0.8498 0.01101 0.00480 -0.0484 0.0353 1.0000
6.250 0.8756 0.01124 0.00503 -0.0482 0.0335 1.0000
6.500 0.9012 0.01149 0.00528 -0.0479 0.0317 1.0000
6.750 0.9274 0.01167 0.00548 -0.0477 0.0299 1.0000
7.000 0.9531 0.01189 0.00566 -0.0474 0.0253 1.0000
7.250 0.9775 0.01225 0.00594 -0.0470 0.0169 1.0000
7.500 1.0012 0.01269 0.00635 -0.0464 0.0123 1.0000
7.750 1.0252 0.01308 0.00678 -0.0458 0.0106 1.0000
8.000 1.0485 0.01355 0.00727 -0.0451 0.0090 1.0000
8.250 1.0720 0.01398 0.00773 -0.0445 0.0081 1.0000
8.500 1.0956 0.01438 0.00818 -0.0439 0.0076 1.0000
8.750 1.1187 0.01483 0.00867 -0.0432 0.0070 1.0000
9.000 1.1412 0.01533 0.00920 -0.0425 0.0065 1.0000
9.250 1.1628 0.01591 0.00983 -0.0416 0.0060 1.0000
9.500 1.1842 0.01649 0.01049 -0.0406 0.0056 1.0000
9.750 1.2062 0.01699 0.01104 -0.0398 0.0054 1.0000
10.000 1.2276 0.01752 0.01162 -0.0390 0.0051 1.0000
10.250 1.2485 0.01808 0.01224 -0.0380 0.0048 1.0000
10.500 1.2688 0.01868 0.01289 -0.0370 0.0046 1.0000
10.750 1.2883 0.01933 0.01360 -0.0359 0.0044 1.0000
11.000 1.3067 0.02005 0.01439 -0.0346 0.0041 1.0000
11.250 1.3234 0.02091 0.01533 -0.0331 0.0039 1.0000
11.500 1.3389 0.02183 0.01635 -0.0314 0.0038 1.0000
11.750 1.3553 0.02257 0.01718 -0.0299 0.0037 1.0000
12.000 1.3691 0.02335 0.01806 -0.0279 0.0036 1.0000
12.250 1.3810 0.02421 0.01901 -0.0257 0.0035 1.0000
12.500 1.3921 0.02513 0.02002 -0.0235 0.0034 1.0000
12.750 1.4022 0.02612 0.02112 -0.0212 0.0034 1.0000
13.000 1.4114 0.02721 0.02231 -0.0190 0.0033 1.0000
13.250 1.4194 0.02840 0.02360 -0.0169 0.0032 1.0000
13.500 1.4266 0.02967 0.02499 -0.0148 0.0031 1.0000
13.750 1.4328 0.03107 0.02651 -0.0128 0.0031 1.0000
14.000 1.4377 0.03262 0.02817 -0.0109 0.0030 1.0000
14.250 1.4414 0.03434 0.03001 -0.0093 0.0029 1.0000
14.500 1.4436 0.03628 0.03206 -0.0078 0.0029 1.0000
14.750 1.4448 0.03844 0.03435 -0.0066 0.0028 1.0000
15.000 1.4440 0.04090 0.03693 -0.0056 0.0028 1.0000
15.250 1.4411 0.04372 0.03988 -0.0050 0.0028 1.0000
15.500 1.4366 0.04689 0.04318 -0.0048 0.0027 1.0000
15.750 1.4298 0.05054 0.04697 -0.0050 0.0027 1.0000
16.000 1.4203 0.05480 0.05138 -0.0058 0.0027 1.0000
16.250 1.4079 0.05973 0.05646 -0.0073 0.0027 1.0000
16.500 1.3930 0.06547 0.06234 -0.0096 0.0026 1.0000
16.750 1.3729 0.07252 0.06957 -0.0130 0.0026 1.0000
17.000 1.3487 0.08082 0.07804 -0.0173 0.0026 1.0000
17.250 1.3178 0.09094 0.08835 -0.0229 0.0027 1.0000
17.500 1.2740 0.10409 0.10172 -0.0300 0.0027 1.0000
17.750 1.1736 0.13130 0.12929 -0.0441 0.0029 1.0000
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Polar data table (+)
Polar graphs
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