GOE 515 AIRFOIL (goe515-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 515 AIRFOIL (goe515-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.03 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe515-il-1000000.txt Download as CSV file: xf-goe515-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 515 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6516 0.10962 0.10785 -0.0233 1.0000 0.0113
-13.500 -0.7848 0.07999 0.07802 -0.0402 1.0000 0.0106
-13.250 -0.8572 0.06496 0.06292 -0.0508 1.0000 0.0103
-13.000 -1.0298 0.03236 0.02965 -0.0707 1.0000 0.0091
-12.750 -1.0260 0.02984 0.02697 -0.0695 1.0000 0.0093
-12.500 -1.0206 0.02773 0.02469 -0.0677 1.0000 0.0095
-12.250 -1.0096 0.02636 0.02320 -0.0661 1.0000 0.0097
-12.000 -1.0004 0.02486 0.02155 -0.0640 1.0000 0.0100
-11.750 -0.9901 0.02356 0.02011 -0.0618 1.0000 0.0102
-11.500 -0.9782 0.02249 0.01891 -0.0597 1.0000 0.0105
-11.250 -0.9659 0.02151 0.01779 -0.0575 1.0000 0.0107
-11.000 -0.9524 0.02068 0.01683 -0.0553 1.0000 0.0109
-10.750 -0.9357 0.01898 0.01493 -0.0544 0.9992 0.0115
-10.500 -0.9060 0.01804 0.01391 -0.0556 0.9976 0.0122
-10.250 -0.8745 0.01746 0.01327 -0.0569 0.9961 0.0129
-10.000 -0.8427 0.01677 0.01248 -0.0582 0.9946 0.0135
-9.750 -0.8120 0.01622 0.01181 -0.0592 0.9928 0.0141
-9.500 -0.7840 0.01513 0.01059 -0.0599 0.9901 0.0151
-9.250 -0.7524 0.01459 0.01001 -0.0610 0.9880 0.0160
-9.000 -0.7189 0.01423 0.00961 -0.0624 0.9862 0.0171
-8.750 -0.6847 0.01383 0.00914 -0.0639 0.9847 0.0180
-8.500 -0.6512 0.01316 0.00838 -0.0655 0.9834 0.0194
-8.250 -0.6218 0.01281 0.00803 -0.0660 0.9799 0.0207
-8.000 -0.5901 0.01251 0.00770 -0.0669 0.9772 0.0220
-7.750 -0.5565 0.01225 0.00738 -0.0682 0.9751 0.0231
-7.500 -0.5244 0.01166 0.00669 -0.0693 0.9727 0.0243
-7.250 -0.4916 0.01112 0.00614 -0.0706 0.9705 0.0262
-7.000 -0.4635 0.01087 0.00585 -0.0707 0.9649 0.0276
-6.750 -0.4336 0.01058 0.00552 -0.0711 0.9599 0.0289
-6.500 -0.4016 0.01034 0.00522 -0.0720 0.9559 0.0298
-6.250 -0.3772 0.00983 0.00463 -0.0712 0.9475 0.0314
-6.000 -0.3492 0.00941 0.00416 -0.0712 0.9414 0.0333
-5.750 -0.3236 0.00915 0.00386 -0.0707 0.9328 0.0348
-5.250 -0.2700 0.00874 0.00334 -0.0700 0.9172 0.0376
-5.000 -0.2437 0.00845 0.00298 -0.0696 0.9098 0.0397
-4.750 -0.2180 0.00817 0.00267 -0.0690 0.9012 0.0429
-4.500 -0.1914 0.00798 0.00245 -0.0687 0.8938 0.0460
-4.250 -0.1654 0.00775 0.00222 -0.0682 0.8859 0.0535
-4.000 -0.1391 0.00755 0.00206 -0.0678 0.8788 0.0688
-3.750 -0.1123 0.00745 0.00200 -0.0674 0.8713 0.0811
-3.500 -0.0853 0.00737 0.00192 -0.0671 0.8647 0.0885
-3.250 -0.0581 0.00733 0.00186 -0.0669 0.8576 0.0935
-3.000 -0.0309 0.00732 0.00178 -0.0666 0.8503 0.0963
-2.750 -0.0047 0.00720 0.00166 -0.0661 0.8405 0.1021
-2.500 0.0217 0.00715 0.00158 -0.0657 0.8293 0.1060
-2.250 0.0485 0.00713 0.00149 -0.0652 0.8196 0.1086
-2.000 0.0754 0.00706 0.00140 -0.0649 0.8117 0.1111
-1.750 0.1020 0.00697 0.00131 -0.0646 0.8049 0.1170
-1.500 0.1291 0.00690 0.00124 -0.0643 0.7976 0.1216
-1.250 0.1561 0.00688 0.00118 -0.0640 0.7908 0.1252
-1.000 0.1829 0.00676 0.00112 -0.0637 0.7831 0.1341
-0.750 0.2096 0.00672 0.00106 -0.0633 0.7757 0.1418
-0.500 0.2364 0.00661 0.00102 -0.0630 0.7679 0.1573
-0.250 0.2626 0.00649 0.00100 -0.0626 0.7601 0.1928
0.000 0.2887 0.00638 0.00098 -0.0621 0.7499 0.2313
0.250 0.3146 0.00626 0.00097 -0.0616 0.7379 0.2723
0.500 0.3397 0.00609 0.00096 -0.0610 0.7260 0.3379
0.750 0.3621 0.00569 0.00097 -0.0600 0.7138 0.4977
1.000 0.3765 0.00454 0.00107 -0.0569 0.7011 0.9160
1.250 0.4424 0.00467 0.00119 -0.0653 0.6821 0.9712
1.500 0.4772 0.00483 0.00127 -0.0666 0.6626 0.9831
1.750 0.5212 0.00498 0.00133 -0.0702 0.6441 0.9893
2.000 0.5619 0.00512 0.00140 -0.0730 0.6253 0.9948
2.250 0.6126 0.00526 0.00144 -0.0781 0.6009 0.9999
2.500 0.6367 0.00538 0.00149 -0.0772 0.5790 1.0000
2.750 0.6594 0.00554 0.00154 -0.0761 0.5495 1.0000
3.000 0.6804 0.00582 0.00163 -0.0747 0.4995 1.0000
3.250 0.7005 0.00618 0.00176 -0.0731 0.4462 1.0000
3.500 0.7215 0.00650 0.00190 -0.0717 0.4058 1.0000
3.750 0.7437 0.00676 0.00204 -0.0706 0.3768 1.0000
4.000 0.7655 0.00704 0.00220 -0.0693 0.3460 1.0000
4.250 0.7870 0.00734 0.00237 -0.0681 0.3126 1.0000
4.500 0.8074 0.00773 0.00256 -0.0667 0.2692 1.0000
4.750 0.8249 0.00835 0.00285 -0.0648 0.1994 1.0000
5.000 0.8436 0.00887 0.00316 -0.0631 0.1561 1.0000
5.250 0.8647 0.00922 0.00341 -0.0618 0.1349 1.0000
5.500 0.8867 0.00950 0.00364 -0.0606 0.1211 1.0000
5.750 0.9087 0.00978 0.00387 -0.0594 0.1079 1.0000
6.000 0.9302 0.01010 0.00412 -0.0582 0.0913 1.0000
6.250 0.9498 0.01057 0.00443 -0.0567 0.0647 1.0000
6.500 0.9701 0.01098 0.00476 -0.0553 0.0498 1.0000
6.750 0.9905 0.01138 0.00511 -0.0539 0.0387 1.0000
7.000 1.0103 0.01184 0.00551 -0.0524 0.0284 1.0000
7.250 1.0304 0.01227 0.00591 -0.0509 0.0226 1.0000
7.500 1.0502 0.01274 0.00638 -0.0494 0.0193 1.0000
7.750 1.0711 0.01309 0.00675 -0.0481 0.0177 1.0000
8.000 1.0905 0.01358 0.00724 -0.0466 0.0160 1.0000
8.250 1.1088 0.01415 0.00788 -0.0448 0.0149 1.0000
8.500 1.1289 0.01454 0.00831 -0.0434 0.0142 1.0000
8.750 1.1482 0.01499 0.00880 -0.0419 0.0135 1.0000
9.000 1.1668 0.01548 0.00932 -0.0404 0.0128 1.0000
9.250 1.1830 0.01614 0.01002 -0.0384 0.0121 1.0000
9.500 1.1953 0.01705 0.01103 -0.0358 0.0114 1.0000
9.750 1.2142 0.01746 0.01147 -0.0343 0.0110 1.0000
10.000 1.2302 0.01804 0.01212 -0.0324 0.0107 1.0000
10.250 1.2452 0.01864 0.01277 -0.0303 0.0102 1.0000
10.500 1.2579 0.01922 0.01340 -0.0278 0.0099 1.0000
10.750 1.2693 0.01987 0.01410 -0.0252 0.0096 1.0000
11.000 1.2803 0.02059 0.01488 -0.0226 0.0093 1.0000
11.250 1.2890 0.02149 0.01585 -0.0199 0.0090 1.0000
11.500 1.2912 0.02292 0.01737 -0.0165 0.0088 1.0000
11.750 1.2925 0.02453 0.01912 -0.0132 0.0085 1.0000
12.000 1.3016 0.02559 0.02027 -0.0111 0.0084 1.0000
12.250 1.3122 0.02653 0.02130 -0.0093 0.0083 1.0000
12.500 1.3214 0.02762 0.02247 -0.0075 0.0081 1.0000
12.750 1.3283 0.02895 0.02391 -0.0056 0.0079 1.0000
13.000 1.3344 0.03038 0.02545 -0.0038 0.0077 1.0000
13.250 1.3388 0.03202 0.02719 -0.0021 0.0076 1.0000
13.500 1.3487 0.03315 0.02839 -0.0011 0.0074 1.0000
13.750 1.3519 0.03500 0.03034 0.0003 0.0072 1.0000
14.000 1.3547 0.03696 0.03240 0.0014 0.0071 1.0000
14.250 1.3571 0.03900 0.03454 0.0023 0.0070 1.0000
14.500 1.3587 0.04123 0.03685 0.0030 0.0068 1.0000
14.750 1.3569 0.04391 0.03966 0.0035 0.0068 1.0000
15.000 1.3533 0.04694 0.04280 0.0037 0.0067 1.0000
15.250 1.3513 0.04991 0.04585 0.0036 0.0066 1.0000
15.500 1.3391 0.05429 0.05036 0.0031 0.0064 1.0000
15.750 1.3277 0.05883 0.05504 0.0021 0.0063 1.0000
16.000 1.3207 0.06305 0.05940 0.0009 0.0064 1.0000
16.250 1.3034 0.06897 0.06547 -0.0011 0.0063 1.0000
16.500 1.2927 0.07427 0.07091 -0.0033 0.0063 1.0000
16.750 1.2639 0.08270 0.07954 -0.0070 0.0062 1.0000
17.000 1.2444 0.09006 0.08705 -0.0105 0.0062 1.0000
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Polar data table (+)
Polar graphs
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