GOE 503 AIRFOIL (goe503-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 503 AIRFOIL (goe503-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.77 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe503-il-1000000-n5.txt Download as CSV file: xf-goe503-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 503 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.3324 0.08412 0.08176 -0.1090 0.9649 0.0076
-14.250 -0.3365 0.07821 0.07580 -0.1143 0.9618 0.0076
-14.000 -0.3426 0.07266 0.07018 -0.1188 0.9553 0.0077
-13.750 -0.3538 0.06506 0.06250 -0.1269 0.9493 0.0076
-13.500 -0.5180 0.03324 0.02999 -0.1618 0.9109 0.0070
-13.250 -0.5380 0.02569 0.02203 -0.1632 0.8905 0.0070
-13.000 -0.5292 0.02324 0.01934 -0.1626 0.8728 0.0071
-12.750 -0.5226 0.02174 0.01762 -0.1604 0.8525 0.0072
-12.500 -0.5120 0.02086 0.01656 -0.1581 0.8305 0.0073
-12.250 -0.5027 0.02006 0.01555 -0.1553 0.8068 0.0075
-12.000 -0.4915 0.01938 0.01469 -0.1528 0.7849 0.0076
-11.750 -0.4788 0.01873 0.01388 -0.1504 0.7686 0.0077
-11.500 -0.4633 0.01820 0.01321 -0.1484 0.7560 0.0079
-11.000 -0.4303 0.01709 0.01185 -0.1448 0.7354 0.0080
-10.750 -0.4148 0.01642 0.01105 -0.1428 0.7267 0.0083
-10.500 -0.3968 0.01582 0.01034 -0.1412 0.7195 0.0085
-10.250 -0.3780 0.01532 0.00975 -0.1396 0.7130 0.0088
-10.000 -0.3576 0.01488 0.00922 -0.1383 0.7074 0.0090
-9.750 -0.3364 0.01449 0.00876 -0.1371 0.7013 0.0093
-9.500 -0.3156 0.01414 0.00831 -0.1358 0.6952 0.0096
-9.250 -0.2934 0.01378 0.00788 -0.1348 0.6899 0.0099
-9.000 -0.2710 0.01345 0.00748 -0.1337 0.6845 0.0102
-8.750 -0.2487 0.01317 0.00711 -0.1326 0.6793 0.0105
-8.500 -0.2262 0.01281 0.00669 -0.1316 0.6746 0.0109
-8.250 -0.2034 0.01248 0.00630 -0.1306 0.6691 0.0115
-8.000 -0.1809 0.01220 0.00595 -0.1295 0.6631 0.0121
-7.750 -0.1574 0.01194 0.00563 -0.1286 0.6579 0.0128
-7.500 -0.1334 0.01173 0.00536 -0.1278 0.6522 0.0134
-7.250 -0.1106 0.01147 0.00504 -0.1267 0.6465 0.0146
-7.000 -0.0870 0.01122 0.00474 -0.1258 0.6410 0.0160
-6.750 -0.0634 0.01097 0.00445 -0.1249 0.6347 0.0183
-6.500 -0.0412 0.01070 0.00417 -0.1238 0.6279 0.0238
-6.250 -0.0175 0.01044 0.00394 -0.1229 0.6215 0.0345
-6.000 0.0060 0.01030 0.00379 -0.1220 0.6146 0.0393
-5.750 0.0303 0.01021 0.00366 -0.1212 0.6079 0.0422
-5.500 0.0537 0.01008 0.00352 -0.1202 0.5998 0.0460
-5.250 0.0775 0.01000 0.00339 -0.1193 0.5930 0.0481
-5.000 0.1016 0.00994 0.00328 -0.1184 0.5857 0.0498
-4.750 0.1249 0.00988 0.00316 -0.1174 0.5788 0.0514
-4.500 0.1486 0.00977 0.00304 -0.1165 0.5716 0.0545
-4.250 0.1712 0.00972 0.00294 -0.1154 0.5643 0.0567
-4.000 0.1953 0.00965 0.00284 -0.1145 0.5582 0.0593
-3.750 0.2184 0.00960 0.00275 -0.1135 0.5516 0.0619
-3.500 0.2412 0.00952 0.00267 -0.1124 0.5459 0.0676
-3.250 0.2643 0.00946 0.00259 -0.1113 0.5398 0.0722
-3.000 0.2856 0.00940 0.00253 -0.1100 0.5341 0.0790
-2.750 0.3077 0.00935 0.00247 -0.1087 0.5294 0.0854
-2.500 0.3298 0.00929 0.00242 -0.1075 0.5240 0.0928
-2.250 0.3515 0.00929 0.00238 -0.1061 0.5188 0.0970
-2.000 0.3734 0.00925 0.00234 -0.1048 0.5143 0.1031
-1.750 0.3964 0.00922 0.00231 -0.1038 0.5099 0.1081
-1.500 0.4190 0.00922 0.00228 -0.1027 0.5052 0.1119
-1.250 0.4401 0.00922 0.00227 -0.1013 0.5007 0.1193
-1.000 0.4631 0.00920 0.00226 -0.1002 0.4972 0.1247
-0.750 0.4859 0.00919 0.00225 -0.0992 0.4931 0.1313
-0.500 0.5082 0.00920 0.00227 -0.0980 0.4889 0.1394
-0.250 0.5297 0.00923 0.00230 -0.0968 0.4848 0.1497
0.000 0.5526 0.00924 0.00234 -0.0958 0.4814 0.1608
0.250 0.5757 0.00926 0.00238 -0.0948 0.4774 0.1729
0.500 0.5979 0.00929 0.00243 -0.0937 0.4732 0.1821
0.750 0.6198 0.00936 0.00248 -0.0925 0.4693 0.1879
1.000 0.6421 0.00941 0.00254 -0.0914 0.4659 0.1952
1.250 0.6653 0.00945 0.00259 -0.0906 0.4624 0.2035
1.500 0.6879 0.00951 0.00264 -0.0896 0.4583 0.2088
1.750 0.7092 0.00958 0.00272 -0.0883 0.4540 0.2155
2.000 0.7310 0.00966 0.00279 -0.0872 0.4505 0.2208
2.250 0.7538 0.00972 0.00286 -0.0863 0.4469 0.2257
2.500 0.7759 0.00978 0.00294 -0.0852 0.4432 0.2330
2.750 0.7970 0.00988 0.00303 -0.0840 0.4385 0.2390
3.000 0.8181 0.00997 0.00313 -0.0827 0.4345 0.2473
3.250 0.8404 0.01004 0.00323 -0.0818 0.4311 0.2566
3.500 0.8616 0.01011 0.00334 -0.0806 0.4271 0.2713
3.750 0.8801 0.01024 0.00349 -0.0789 0.4208 0.2926
4.000 0.9009 0.01030 0.00362 -0.0777 0.4171 0.3219
4.250 0.9209 0.01038 0.00376 -0.0764 0.4108 0.3518
4.500 0.9375 0.01052 0.00395 -0.0744 0.4041 0.3943
4.750 0.9548 0.01044 0.00412 -0.0726 0.4005 0.4949
5.250 1.1229 0.01023 0.00496 -0.0987 0.3776 0.9881
5.500 1.1466 0.01052 0.00523 -0.0983 0.3713 0.9969
6.000 1.2030 0.01105 0.00570 -0.0996 0.3590 1.0000
6.250 1.2190 0.01126 0.00590 -0.0976 0.3541 1.0000
6.500 1.2353 0.01149 0.00612 -0.0956 0.3487 1.0000
6.750 1.2496 0.01181 0.00640 -0.0934 0.3422 1.0000
7.000 1.2668 0.01205 0.00665 -0.0918 0.3373 1.0000
7.250 1.2832 0.01235 0.00694 -0.0900 0.3318 1.0000
7.500 1.2988 0.01269 0.00726 -0.0882 0.3268 1.0000
7.750 1.3146 0.01304 0.00760 -0.0864 0.3187 1.0000
8.000 1.3285 0.01350 0.00803 -0.0844 0.3111 1.0000
8.250 1.3432 0.01394 0.00845 -0.0826 0.3019 1.0000
8.500 1.3568 0.01445 0.00893 -0.0806 0.2940 1.0000
8.750 1.3690 0.01504 0.00948 -0.0786 0.2833 1.0000
9.000 1.3816 0.01565 0.01006 -0.0766 0.2730 1.0000
9.250 1.3917 0.01640 0.01076 -0.0744 0.2614 1.0000
9.500 1.4015 0.01719 0.01151 -0.0722 0.2505 1.0000
9.750 1.4130 0.01793 0.01223 -0.0704 0.2411 1.0000
10.000 1.4211 0.01889 0.01315 -0.0682 0.2292 1.0000
10.250 1.4262 0.02006 0.01426 -0.0658 0.2148 1.0000
10.500 1.4274 0.02152 0.01563 -0.0631 0.1979 1.0000
10.750 1.4299 0.02299 0.01704 -0.0607 0.1841 1.0000
11.000 1.4341 0.02444 0.01845 -0.0586 0.1730 1.0000
11.250 1.4339 0.02624 0.02020 -0.0563 0.1593 1.0000
11.500 1.4314 0.02830 0.02219 -0.0540 0.1442 1.0000
11.750 1.4302 0.03037 0.02422 -0.0520 0.1309 1.0000
12.000 1.4091 0.03408 0.02776 -0.0488 0.1008 1.0000
12.250 1.3841 0.03838 0.03194 -0.0457 0.0692 1.0000
12.500 1.3683 0.04207 0.03559 -0.0435 0.0483 1.0000
12.750 1.3452 0.04666 0.04008 -0.0413 0.0202 1.0000
13.000 1.3442 0.04927 0.04272 -0.0403 0.0152 1.0000
13.250 1.3468 0.05156 0.04506 -0.0396 0.0136 1.0000
13.500 1.3503 0.05380 0.04734 -0.0390 0.0122 1.0000
13.750 1.3542 0.05606 0.04966 -0.0385 0.0116 1.0000
14.000 1.3566 0.05851 0.05216 -0.0381 0.0109 1.0000
14.250 1.3592 0.06093 0.05464 -0.0376 0.0103 1.0000
14.500 1.3604 0.06354 0.05731 -0.0373 0.0095 1.0000
14.750 1.3629 0.06605 0.05987 -0.0370 0.0091 1.0000
15.000 1.3653 0.06859 0.06247 -0.0367 0.0088 1.0000
15.250 1.3659 0.07138 0.06531 -0.0365 0.0083 1.0000
15.500 1.3663 0.07420 0.06819 -0.0364 0.0080 1.0000
15.750 1.3653 0.07719 0.07124 -0.0362 0.0076 1.0000
16.000 1.3644 0.08023 0.07433 -0.0362 0.0074 1.0000
16.250 1.3660 0.08297 0.07715 -0.0362 0.0071 1.0000
16.500 1.3651 0.08608 0.08032 -0.0363 0.0069 1.0000
16.750 1.3654 0.08904 0.08333 -0.0364 0.0065 1.0000
17.000 1.3632 0.09232 0.08669 -0.0366 0.0064 1.0000
17.250 1.3620 0.09550 0.08993 -0.0368 0.0062 1.0000
17.500 1.3601 0.09880 0.09328 -0.0372 0.0059 1.0000
17.750 1.3560 0.10244 0.09698 -0.0376 0.0056 1.0000
18.000 1.3536 0.10588 0.10049 -0.0380 0.0055 1.0000
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