GOE 796 AIRFOIL (goe796-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 796 AIRFOIL (goe796-il) Reynolds number: 500,000 Max Cl/Cd: 90.49 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe796-il-500000-n5.txt Download as CSV file: xf-goe796-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 796 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7554 0.06086 0.05793 -0.0665 1.0000 0.0165
-12.500 -0.8514 0.03908 0.03562 -0.0854 1.0000 0.0159
-12.250 -0.8592 0.03624 0.03260 -0.0847 0.9968 0.0160
-12.000 -0.8443 0.03353 0.02968 -0.0870 0.9930 0.0162
-11.750 -0.8283 0.03126 0.02719 -0.0883 0.9883 0.0164
-11.500 -0.8086 0.02926 0.02500 -0.0895 0.9846 0.0165
-11.250 -0.7882 0.02750 0.02304 -0.0903 0.9807 0.0166
-11.000 -0.7678 0.02597 0.02133 -0.0906 0.9758 0.0167
-10.750 -0.7446 0.02457 0.01975 -0.0912 0.9722 0.0168
-10.500 -0.7226 0.02336 0.01839 -0.0913 0.9674 0.0169
-10.250 -0.7003 0.02227 0.01713 -0.0911 0.9621 0.0170
-10.000 -0.6761 0.02125 0.01596 -0.0912 0.9580 0.0171
-9.750 -0.6542 0.02036 0.01495 -0.0907 0.9522 0.0172
-9.500 -0.6310 0.01953 0.01400 -0.0903 0.9466 0.0173
-9.250 -0.6071 0.01875 0.01310 -0.0900 0.9416 0.0174
-9.000 -0.5841 0.01805 0.01229 -0.0894 0.9352 0.0175
-8.750 -0.5600 0.01738 0.01151 -0.0889 0.9296 0.0176
-8.500 -0.5359 0.01676 0.01079 -0.0885 0.9234 0.0177
-8.250 -0.5115 0.01618 0.01012 -0.0880 0.9166 0.0178
-8.000 -0.4866 0.01564 0.00947 -0.0875 0.9106 0.0179
-7.750 -0.4615 0.01513 0.00888 -0.0871 0.9032 0.0180
-7.500 -0.4361 0.01465 0.00831 -0.0867 0.8965 0.0181
-7.250 -0.4104 0.01421 0.00779 -0.0864 0.8881 0.0182
-7.000 -0.3845 0.01379 0.00728 -0.0860 0.8806 0.0182
-6.750 -0.3582 0.01341 0.00682 -0.0857 0.8718 0.0183
-6.500 -0.3320 0.01300 0.00633 -0.0854 0.8631 0.0186
-6.250 -0.3057 0.01262 0.00586 -0.0851 0.8532 0.0190
-6.000 -0.2790 0.01228 0.00544 -0.0849 0.8432 0.0194
-5.750 -0.2521 0.01198 0.00507 -0.0847 0.8335 0.0198
-5.500 -0.2251 0.01172 0.00472 -0.0845 0.8228 0.0201
-5.250 -0.1979 0.01148 0.00440 -0.0843 0.8121 0.0206
-5.000 -0.1707 0.01126 0.00411 -0.0841 0.8016 0.0211
-4.750 -0.1434 0.01106 0.00384 -0.0839 0.7916 0.0220
-4.500 -0.1159 0.01085 0.00358 -0.0838 0.7822 0.0239
-4.250 -0.0889 0.01058 0.00335 -0.0837 0.7733 0.0338
-4.000 -0.0613 0.01042 0.00317 -0.0836 0.7642 0.0426
-3.750 -0.0336 0.01030 0.00301 -0.0835 0.7557 0.0486
-3.500 -0.0059 0.01019 0.00285 -0.0834 0.7465 0.0522
-3.250 0.0218 0.01007 0.00271 -0.0834 0.7373 0.0568
-3.000 0.0494 0.00999 0.00257 -0.0833 0.7289 0.0615
-2.500 0.1051 0.00976 0.00241 -0.0833 0.7142 0.0843
-2.250 0.1332 0.00970 0.00234 -0.0833 0.7072 0.0934
-2.000 0.1613 0.00965 0.00226 -0.0833 0.6999 0.0987
-1.750 0.1893 0.00959 0.00220 -0.0833 0.6930 0.1062
-1.500 0.2175 0.00954 0.00214 -0.0833 0.6861 0.1136
-1.250 0.2453 0.00948 0.00209 -0.0833 0.6795 0.1237
-1.000 0.2735 0.00942 0.00204 -0.0834 0.6718 0.1309
-0.750 0.3013 0.00938 0.00199 -0.0833 0.6641 0.1387
-0.500 0.3294 0.00930 0.00196 -0.0834 0.6568 0.1531
-0.250 0.3571 0.00921 0.00193 -0.0834 0.6506 0.1781
0.000 0.3851 0.00910 0.00192 -0.0835 0.6446 0.2107
0.250 0.4129 0.00900 0.00192 -0.0835 0.6383 0.2489
0.500 0.4404 0.00886 0.00193 -0.0835 0.6323 0.3024
0.750 0.4672 0.00858 0.00195 -0.0835 0.6247 0.3993
1.000 0.4926 0.00821 0.00198 -0.0832 0.6155 0.5438
1.250 0.5172 0.00790 0.00203 -0.0826 0.6042 0.6704
1.500 0.5405 0.00759 0.00209 -0.0815 0.5933 0.7904
1.750 0.5667 0.00742 0.00223 -0.0805 0.5830 0.9249
2.000 0.6070 0.00752 0.00230 -0.0831 0.5711 0.9730
2.250 0.6462 0.00764 0.00236 -0.0857 0.5578 0.9911
2.500 0.6866 0.00779 0.00243 -0.0885 0.5402 1.0000
2.750 0.7106 0.00795 0.00250 -0.0877 0.5187 1.0000
3.000 0.7339 0.00817 0.00259 -0.0868 0.4951 1.0000
3.250 0.7573 0.00838 0.00269 -0.0860 0.4722 1.0000
3.500 0.7802 0.00864 0.00283 -0.0850 0.4477 1.0000
3.750 0.8029 0.00892 0.00299 -0.0841 0.4225 1.0000
4.000 0.8260 0.00921 0.00317 -0.0832 0.4010 1.0000
4.250 0.8495 0.00947 0.00334 -0.0824 0.3841 1.0000
4.500 0.8732 0.00973 0.00353 -0.0817 0.3687 1.0000
4.750 0.8970 0.00999 0.00373 -0.0810 0.3557 1.0000
5.000 0.9211 0.01023 0.00393 -0.0804 0.3445 1.0000
5.250 0.9456 0.01045 0.00412 -0.0798 0.3351 1.0000
5.500 0.9691 0.01074 0.00435 -0.0790 0.3216 1.0000
5.750 0.9924 0.01104 0.00459 -0.0783 0.3070 1.0000
6.000 1.0158 0.01134 0.00483 -0.0776 0.2941 1.0000
6.250 1.0396 0.01159 0.00506 -0.0769 0.2816 1.0000
6.500 1.0632 0.01187 0.00531 -0.0763 0.2679 1.0000
6.750 1.0854 0.01222 0.00558 -0.0754 0.2478 1.0000
7.000 1.1038 0.01283 0.00596 -0.0740 0.2055 1.0000
7.250 1.1210 0.01350 0.00644 -0.0723 0.1752 1.0000
7.500 1.1407 0.01400 0.00687 -0.0711 0.1614 1.0000
7.750 1.1610 0.01443 0.00728 -0.0699 0.1519 1.0000
8.000 1.1819 0.01481 0.00765 -0.0689 0.1438 1.0000
8.250 1.2015 0.01525 0.00806 -0.0676 0.1356 1.0000
8.500 1.2220 0.01560 0.00844 -0.0665 0.1288 1.0000
8.750 1.2394 0.01606 0.00887 -0.0648 0.1194 1.0000
9.000 1.2556 0.01657 0.00934 -0.0630 0.1069 1.0000
9.250 1.2704 0.01718 0.00987 -0.0611 0.0926 1.0000
9.500 1.2847 0.01784 0.01047 -0.0592 0.0816 1.0000
9.750 1.3006 0.01842 0.01107 -0.0575 0.0748 1.0000
10.000 1.3157 0.01907 0.01172 -0.0558 0.0686 1.0000
10.250 1.3309 0.01973 0.01238 -0.0542 0.0632 1.0000
10.500 1.3453 0.02044 0.01311 -0.0525 0.0585 1.0000
10.750 1.3602 0.02115 0.01384 -0.0510 0.0539 1.0000
11.000 1.3732 0.02199 0.01470 -0.0493 0.0490 1.0000
11.250 1.3867 0.02282 0.01555 -0.0477 0.0436 1.0000
11.500 1.3975 0.02386 0.01658 -0.0460 0.0366 1.0000
11.750 1.4060 0.02509 0.01777 -0.0441 0.0287 1.0000
12.000 1.4140 0.02639 0.01907 -0.0423 0.0237 1.0000
12.250 1.4229 0.02768 0.02039 -0.0407 0.0208 1.0000
12.500 1.4312 0.02905 0.02181 -0.0391 0.0187 1.0000
12.750 1.4399 0.03043 0.02325 -0.0378 0.0173 1.0000
13.000 1.4489 0.03183 0.02472 -0.0365 0.0162 1.0000
13.250 1.4561 0.03341 0.02636 -0.0352 0.0151 1.0000
13.500 1.4618 0.03517 0.02819 -0.0340 0.0142 1.0000
13.750 1.4697 0.03679 0.02989 -0.0330 0.0135 1.0000
14.000 1.4766 0.03853 0.03173 -0.0321 0.0128 1.0000
14.250 1.4820 0.04044 0.03373 -0.0312 0.0122 1.0000
14.500 1.4859 0.04255 0.03592 -0.0304 0.0116 1.0000
14.750 1.4884 0.04487 0.03831 -0.0296 0.0111 1.0000
15.000 1.4925 0.04708 0.04061 -0.0291 0.0106 1.0000
15.250 1.4955 0.04946 0.04309 -0.0286 0.0101 1.0000
15.500 1.4974 0.05202 0.04575 -0.0282 0.0097 1.0000
15.750 1.4981 0.05479 0.04860 -0.0280 0.0093 1.0000
16.000 1.4974 0.05779 0.05168 -0.0278 0.0089 1.0000
16.250 1.4953 0.06104 0.05502 -0.0279 0.0086 1.0000
16.500 1.4928 0.06443 0.05853 -0.0280 0.0084 1.0000
16.750 1.4893 0.06805 0.06226 -0.0284 0.0082 1.0000
17.000 1.4847 0.07189 0.06621 -0.0289 0.0080 1.0000
17.250 1.4786 0.07605 0.07047 -0.0296 0.0078 1.0000
17.500 1.4713 0.08049 0.07503 -0.0306 0.0076 1.0000
17.750 1.4630 0.08519 0.07984 -0.0318 0.0075 1.0000
18.000 1.4530 0.09024 0.08501 -0.0332 0.0074 1.0000
18.250 1.4423 0.09549 0.09037 -0.0348 0.0073 1.0000
18.500 1.4303 0.10107 0.09608 -0.0367 0.0072 1.0000
18.750 1.4175 0.10688 0.10201 -0.0388 0.0070 1.0000
19.000 1.4039 0.11290 0.10815 -0.0411 0.0070 1.0000
19.250 1.3895 0.11913 0.11450 -0.0437 0.0069 1.0000
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