GOE 627 AIRFOIL (goe627-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 627 AIRFOIL (goe627-il) Reynolds number: 500,000 Max Cl/Cd: 71.89 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe627-il-500000-n5.txt Download as CSV file: xf-goe627-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 627 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.7671 0.05779 0.05444 -0.0875 0.9974 0.0177
-14.750 -0.7756 0.05130 0.04777 -0.0943 0.9955 0.0178
-14.500 -0.7846 0.04569 0.04197 -0.0998 0.9935 0.0179
-14.250 -0.7862 0.04222 0.03836 -0.1024 0.9910 0.0181
-14.000 -0.7826 0.03955 0.03556 -0.1043 0.9884 0.0182
-13.750 -0.7794 0.03695 0.03280 -0.1057 0.9860 0.0184
-13.500 -0.7707 0.03486 0.03056 -0.1069 0.9841 0.0187
-13.250 -0.7650 0.03302 0.02855 -0.1067 0.9814 0.0190
-13.000 -0.7610 0.03137 0.02673 -0.1054 0.9773 0.0193
-12.750 -0.7521 0.02966 0.02478 -0.1048 0.9744 0.0198
-12.500 -0.7381 0.02814 0.02302 -0.1045 0.9724 0.0202
-12.250 -0.7188 0.02696 0.02172 -0.1045 0.9710 0.0205
-12.000 -0.7146 0.02638 0.02110 -0.1009 0.9648 0.0206
-11.750 -0.6950 0.02577 0.02046 -0.1002 0.9620 0.0209
-11.500 -0.6710 0.02513 0.01978 -0.1002 0.9602 0.0212
-11.250 -0.6442 0.02433 0.01890 -0.1009 0.9588 0.0215
-11.000 -0.6141 0.02346 0.01794 -0.1021 0.9576 0.0220
-10.750 -0.6048 0.02287 0.01725 -0.0989 0.9502 0.0224
-10.500 -0.5794 0.02202 0.01627 -0.0990 0.9475 0.0228
-10.250 -0.5515 0.02119 0.01530 -0.0995 0.9456 0.0234
-10.000 -0.5226 0.02055 0.01451 -0.1001 0.9440 0.0239
-9.750 -0.4935 0.01969 0.01363 -0.1009 0.9426 0.0243
-9.500 -0.4839 0.01928 0.01320 -0.0974 0.9358 0.0246
-9.250 -0.4597 0.01875 0.01263 -0.0970 0.9323 0.0249
-9.000 -0.4318 0.01818 0.01202 -0.0972 0.9297 0.0253
-8.750 -0.4022 0.01763 0.01141 -0.0978 0.9275 0.0259
-8.500 -0.3828 0.01721 0.01093 -0.0961 0.9225 0.0264
-8.250 -0.3630 0.01676 0.01042 -0.0945 0.9171 0.0268
-8.000 -0.3359 0.01626 0.00986 -0.0944 0.9133 0.0273
-7.750 -0.3050 0.01576 0.00928 -0.0951 0.9104 0.0277
-7.500 -0.2903 0.01532 0.00881 -0.0924 0.9025 0.0280
-7.250 -0.2651 0.01473 0.00821 -0.0919 0.8967 0.0285
-7.000 -0.2417 0.01431 0.00777 -0.0910 0.8887 0.0290
-6.750 -0.2153 0.01391 0.00734 -0.0906 0.8800 0.0296
-6.500 -0.1924 0.01354 0.00694 -0.0895 0.8703 0.0301
-6.250 -0.1643 0.01314 0.00648 -0.0895 0.8611 0.0306
-6.000 -0.1413 0.01283 0.00611 -0.0884 0.8486 0.0311
-5.750 -0.1164 0.01253 0.00575 -0.0876 0.8354 0.0316
-5.500 -0.0912 0.01227 0.00541 -0.0869 0.8217 0.0321
-5.250 -0.0677 0.01199 0.00505 -0.0859 0.8066 0.0326
-5.000 -0.0451 0.01173 0.00473 -0.0847 0.7899 0.0333
-4.750 -0.0230 0.01154 0.00446 -0.0834 0.7711 0.0340
-4.500 -0.0014 0.01141 0.00423 -0.0819 0.7511 0.0346
-4.250 0.0190 0.01132 0.00402 -0.0802 0.7285 0.0353
-4.000 0.0383 0.01126 0.00384 -0.0782 0.7046 0.0360
-3.750 0.0575 0.01123 0.00368 -0.0762 0.6807 0.0367
-3.500 0.0772 0.01118 0.00353 -0.0743 0.6610 0.0375
-3.250 0.0968 0.01111 0.00338 -0.0725 0.6430 0.0389
-3.000 0.1171 0.01106 0.00327 -0.0708 0.6268 0.0406
-2.750 0.1370 0.01105 0.00317 -0.0690 0.6086 0.0425
-2.500 0.1570 0.01100 0.00307 -0.0672 0.5924 0.0460
-2.250 0.1768 0.01095 0.00299 -0.0654 0.5762 0.0534
-2.000 0.1960 0.01087 0.00291 -0.0635 0.5602 0.0735
-1.750 0.2123 0.01062 0.00281 -0.0612 0.5441 0.1316
-1.500 0.2303 0.01052 0.00276 -0.0591 0.5265 0.1678
-1.250 0.2456 0.01033 0.00272 -0.0566 0.5068 0.2321
-1.000 0.2618 0.01021 0.00271 -0.0542 0.4881 0.2923
-0.750 0.2778 0.01012 0.00269 -0.0517 0.4697 0.3405
-0.500 0.2931 0.01004 0.00269 -0.0491 0.4529 0.3870
-0.250 0.3058 0.00984 0.00269 -0.0460 0.4386 0.4666
0.000 0.3160 0.00958 0.00270 -0.0423 0.4252 0.5674
0.250 0.3266 0.00935 0.00275 -0.0386 0.4131 0.6594
0.500 0.3391 0.00924 0.00284 -0.0352 0.4017 0.7322
0.750 0.3543 0.00920 0.00298 -0.0323 0.3897 0.8011
1.000 0.3781 0.00925 0.00314 -0.0312 0.3778 0.8549
1.250 0.4160 0.00945 0.00336 -0.0333 0.3644 0.8999
1.500 0.4578 0.00972 0.00356 -0.0363 0.3509 0.9218
1.750 0.5006 0.01002 0.00376 -0.0397 0.3375 0.9328
2.000 0.5452 0.01030 0.00397 -0.0433 0.3265 0.9445
2.250 0.5822 0.01058 0.00417 -0.0453 0.3172 0.9559
2.500 0.6204 0.01084 0.00436 -0.0476 0.3078 0.9606
2.750 0.6507 0.01109 0.00454 -0.0482 0.3005 0.9681
3.000 0.6850 0.01133 0.00473 -0.0497 0.2924 0.9730
3.250 0.7188 0.01161 0.00492 -0.0512 0.2851 0.9780
3.500 0.7495 0.01182 0.00510 -0.0519 0.2786 0.9831
3.750 0.7827 0.01205 0.00526 -0.0533 0.2718 0.9858
4.000 0.8142 0.01226 0.00543 -0.0543 0.2669 0.9890
4.250 0.8447 0.01246 0.00561 -0.0552 0.2619 0.9923
4.500 0.8757 0.01268 0.00579 -0.0562 0.2570 0.9952
4.750 0.9073 0.01293 0.00599 -0.0573 0.2525 0.9979
5.000 0.9401 0.01312 0.00617 -0.0587 0.2485 0.9998
5.250 0.9529 0.01326 0.00630 -0.0559 0.2454 1.0000
5.500 0.9640 0.01341 0.00644 -0.0527 0.2423 1.0000
5.750 0.9756 0.01360 0.00662 -0.0497 0.2394 1.0000
6.000 0.9880 0.01383 0.00681 -0.0468 0.2364 1.0000
6.250 1.0033 0.01400 0.00700 -0.0445 0.2339 1.0000
6.500 1.0189 0.01419 0.00720 -0.0424 0.2311 1.0000
6.750 1.0346 0.01441 0.00742 -0.0402 0.2286 1.0000
7.000 1.0500 0.01466 0.00766 -0.0381 0.2255 1.0000
7.250 1.0650 0.01496 0.00794 -0.0359 0.2224 1.0000
7.500 1.0805 0.01526 0.00823 -0.0339 0.2195 1.0000
7.750 1.0986 0.01549 0.00849 -0.0323 0.2174 1.0000
8.000 1.1161 0.01575 0.00878 -0.0307 0.2155 1.0000
8.250 1.1333 0.01604 0.00909 -0.0291 0.2132 1.0000
8.500 1.1503 0.01636 0.00941 -0.0275 0.2107 1.0000
8.750 1.1664 0.01674 0.00978 -0.0258 0.2077 1.0000
9.000 1.1816 0.01716 0.01020 -0.0240 0.2043 1.0000
9.250 1.2000 0.01747 0.01055 -0.0227 0.2026 1.0000
9.500 1.2182 0.01780 0.01092 -0.0215 0.2005 1.0000
9.750 1.2355 0.01817 0.01133 -0.0201 0.1982 1.0000
10.000 1.2523 0.01859 0.01177 -0.0187 0.1959 1.0000
10.250 1.2687 0.01903 0.01223 -0.0173 0.1938 1.0000
10.500 1.2841 0.01954 0.01276 -0.0159 0.1915 1.0000
10.750 1.2993 0.02007 0.01331 -0.0144 0.1893 1.0000
11.000 1.3168 0.02050 0.01380 -0.0133 0.1877 1.0000
11.250 1.3338 0.02097 0.01433 -0.0122 0.1854 1.0000
11.500 1.3501 0.02149 0.01489 -0.0110 0.1830 1.0000
11.750 1.3652 0.02208 0.01551 -0.0098 0.1804 1.0000
12.000 1.3792 0.02274 0.01620 -0.0085 0.1776 1.0000
12.250 1.3923 0.02347 0.01696 -0.0072 0.1750 1.0000
12.500 1.4087 0.02404 0.01760 -0.0062 0.1711 1.0000
12.750 1.4219 0.02481 0.01839 -0.0050 0.1658 1.0000
13.000 1.4328 0.02574 0.01932 -0.0037 0.1615 1.0000
13.250 1.4464 0.02654 0.02017 -0.0027 0.1564 1.0000
13.500 1.4565 0.02758 0.02122 -0.0015 0.1507 1.0000
13.750 1.4662 0.02869 0.02235 -0.0003 0.1445 1.0000
14.000 1.4745 0.02995 0.02362 0.0009 0.1387 1.0000
14.250 1.4815 0.03133 0.02503 0.0020 0.1323 1.0000
14.500 1.4861 0.03296 0.02666 0.0032 0.1256 1.0000
14.750 1.4908 0.03464 0.02837 0.0042 0.1195 1.0000
15.000 1.4913 0.03675 0.03049 0.0052 0.1129 1.0000
15.250 1.4939 0.03876 0.03253 0.0060 0.1074 1.0000
15.500 1.4949 0.04096 0.03478 0.0067 0.1037 1.0000
15.750 1.4958 0.04326 0.03713 0.0073 0.1003 1.0000
16.000 1.4956 0.04575 0.03968 0.0077 0.0968 1.0000
16.250 1.4919 0.04866 0.04265 0.0080 0.0935 1.0000
16.500 1.4892 0.05156 0.04561 0.0081 0.0913 1.0000
16.750 1.4870 0.05448 0.04861 0.0081 0.0886 1.0000
17.000 1.4841 0.05755 0.05177 0.0079 0.0869 1.0000
17.250 1.4758 0.06134 0.05564 0.0075 0.0845 1.0000
17.500 1.4685 0.06508 0.05948 0.0070 0.0832 1.0000
17.750 1.4574 0.06940 0.06388 0.0062 0.0806 1.0000
18.000 1.4517 0.07311 0.06770 0.0055 0.0794 1.0000
18.250 1.4439 0.07715 0.07184 0.0046 0.0782 1.0000
18.500 1.4299 0.08207 0.07685 0.0034 0.0760 1.0000
18.750 1.4180 0.08680 0.08169 0.0021 0.0749 1.0000
19.000 1.4018 0.09219 0.08717 0.0005 0.0735 1.0000
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