GOE 796 AIRFOIL (goe796-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 796 AIRFOIL (goe796-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.19 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe796-il-1000000-n5.txt Download as CSV file: xf-goe796-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7184 0.09505 0.09285 -0.0435 1.0000 0.0126
-14.250 -0.7933 0.07833 0.07598 -0.0538 1.0000 0.0125
-14.000 -0.9955 0.03555 0.03243 -0.0901 1.0000 0.0118
-13.750 -1.0103 0.03312 0.02988 -0.0876 0.9999 0.0118
-13.500 -0.9952 0.03086 0.02748 -0.0893 0.9950 0.0120
-13.250 -0.9776 0.02911 0.02561 -0.0903 0.9899 0.0121
-13.000 -0.9582 0.02761 0.02400 -0.0910 0.9853 0.0122
-12.750 -0.9381 0.02629 0.02257 -0.0915 0.9810 0.0123
-12.500 -0.9188 0.02509 0.02127 -0.0914 0.9755 0.0124
-12.000 -0.8789 0.02298 0.01894 -0.0909 0.9651 0.0127
-11.750 -0.8587 0.02205 0.01790 -0.0904 0.9598 0.0128
-11.500 -0.8380 0.02120 0.01694 -0.0899 0.9547 0.0129
-11.250 -0.8166 0.02044 0.01609 -0.0893 0.9491 0.0131
-11.000 -0.7947 0.01974 0.01529 -0.0887 0.9440 0.0133
-10.750 -0.7721 0.01905 0.01451 -0.0882 0.9390 0.0134
-10.500 -0.7492 0.01841 0.01377 -0.0878 0.9332 0.0136
-10.250 -0.7259 0.01782 0.01309 -0.0872 0.9279 0.0138
-10.000 -0.7018 0.01723 0.01241 -0.0869 0.9227 0.0139
-9.750 -0.6775 0.01670 0.01180 -0.0865 0.9166 0.0141
-9.500 -0.6529 0.01622 0.01123 -0.0861 0.9109 0.0142
-9.250 -0.6282 0.01566 0.01058 -0.0858 0.9043 0.0143
-9.000 -0.6034 0.01514 0.00997 -0.0854 0.8977 0.0143
-8.750 -0.5780 0.01465 0.00940 -0.0851 0.8909 0.0144
-8.500 -0.5526 0.01419 0.00885 -0.0848 0.8830 0.0144
-8.250 -0.5268 0.01375 0.00833 -0.0845 0.8749 0.0144
-8.000 -0.5009 0.01335 0.00783 -0.0842 0.8664 0.0145
-7.750 -0.4746 0.01295 0.00736 -0.0840 0.8571 0.0145
-7.500 -0.4483 0.01259 0.00692 -0.0838 0.8471 0.0145
-7.250 -0.4223 0.01217 0.00640 -0.0835 0.8357 0.0146
-7.000 -0.3959 0.01178 0.00592 -0.0833 0.8236 0.0147
-6.750 -0.3692 0.01144 0.00549 -0.0831 0.8118 0.0148
-6.500 -0.3423 0.01114 0.00510 -0.0829 0.7998 0.0149
-6.250 -0.3154 0.01087 0.00474 -0.0828 0.7876 0.0150
-6.000 -0.2882 0.01062 0.00441 -0.0826 0.7757 0.0151
-5.750 -0.2607 0.01039 0.00411 -0.0825 0.7654 0.0153
-5.500 -0.2332 0.01018 0.00383 -0.0825 0.7565 0.0154
-5.250 -0.2055 0.00997 0.00357 -0.0824 0.7476 0.0156
-5.000 -0.1777 0.00979 0.00333 -0.0824 0.7395 0.0159
-4.750 -0.1499 0.00963 0.00312 -0.0824 0.7308 0.0162
-4.500 -0.1219 0.00948 0.00292 -0.0824 0.7226 0.0164
-4.250 -0.0940 0.00936 0.00274 -0.0823 0.7136 0.0166
-4.000 -0.0658 0.00923 0.00257 -0.0824 0.7061 0.0169
-3.750 -0.0377 0.00912 0.00241 -0.0824 0.6992 0.0174
-3.500 -0.0093 0.00901 0.00228 -0.0824 0.6933 0.0178
-3.250 0.0190 0.00890 0.00214 -0.0825 0.6860 0.0192
-3.000 0.0467 0.00869 0.00198 -0.0825 0.6794 0.0313
-2.750 0.0750 0.00854 0.00187 -0.0826 0.6736 0.0427
-2.500 0.1033 0.00846 0.00178 -0.0826 0.6672 0.0481
-2.250 0.1318 0.00838 0.00170 -0.0827 0.6613 0.0529
-2.000 0.1601 0.00830 0.00163 -0.0828 0.6542 0.0580
-1.750 0.1883 0.00822 0.00156 -0.0829 0.6468 0.0684
-1.500 0.2165 0.00811 0.00153 -0.0829 0.6383 0.0873
-1.250 0.2449 0.00809 0.00150 -0.0830 0.6311 0.0948
-1.000 0.2736 0.00806 0.00146 -0.0832 0.6248 0.0989
-0.500 0.3306 0.00799 0.00141 -0.0834 0.6132 0.1106
-0.250 0.3590 0.00795 0.00139 -0.0835 0.6063 0.1202
0.000 0.3872 0.00794 0.00138 -0.0835 0.5963 0.1273
0.250 0.4151 0.00794 0.00137 -0.0836 0.5828 0.1391
0.500 0.4428 0.00791 0.00138 -0.0836 0.5701 0.1624
0.750 0.4706 0.00786 0.00139 -0.0836 0.5590 0.1962
1.000 0.4985 0.00782 0.00141 -0.0837 0.5481 0.2299
1.250 0.5260 0.00778 0.00145 -0.0837 0.5355 0.2714
1.750 0.5788 0.00755 0.00157 -0.0834 0.4970 0.4509
2.000 0.6045 0.00750 0.00167 -0.0832 0.4719 0.5421
2.250 0.6288 0.00739 0.00179 -0.0827 0.4441 0.6663
2.500 0.6521 0.00734 0.00194 -0.0818 0.4149 0.7780
2.750 0.6711 0.00719 0.00213 -0.0797 0.3927 0.9270
3.000 0.7055 0.00741 0.00229 -0.0811 0.3718 0.9783
3.250 0.7464 0.00765 0.00244 -0.0841 0.3551 0.9956
3.750 0.8076 0.00797 0.00267 -0.0856 0.3354 1.0000
4.250 0.8568 0.00829 0.00291 -0.0843 0.3178 1.0000
4.500 0.8816 0.00847 0.00304 -0.0838 0.3105 1.0000
4.750 0.9067 0.00862 0.00317 -0.0833 0.3014 1.0000
5.000 0.9310 0.00886 0.00333 -0.0826 0.2858 1.0000
5.250 0.9548 0.00913 0.00351 -0.0820 0.2673 1.0000
5.500 0.9781 0.00945 0.00371 -0.0812 0.2422 1.0000
5.750 0.9971 0.01009 0.00406 -0.0798 0.1915 1.0000
6.250 1.0416 0.01088 0.00465 -0.0780 0.1550 1.0000
6.500 1.0656 0.01115 0.00490 -0.0774 0.1477 1.0000
6.750 1.0900 0.01138 0.00512 -0.0769 0.1422 1.0000
7.000 1.1135 0.01167 0.00537 -0.0762 0.1350 1.0000
7.250 1.1374 0.01192 0.00561 -0.0756 0.1278 1.0000
7.500 1.1600 0.01226 0.00590 -0.0748 0.1180 1.0000
7.750 1.1817 0.01264 0.00621 -0.0739 0.1048 1.0000
8.000 1.2018 0.01313 0.00659 -0.0727 0.0880 1.0000
8.250 1.2218 0.01359 0.00699 -0.0716 0.0761 1.0000
8.500 1.2422 0.01401 0.00738 -0.0704 0.0685 1.0000
8.750 1.2625 0.01440 0.00775 -0.0693 0.0626 1.0000
9.000 1.2818 0.01482 0.00815 -0.0680 0.0568 1.0000
9.250 1.2992 0.01525 0.00856 -0.0663 0.0515 1.0000
9.500 1.3167 0.01567 0.00899 -0.0647 0.0476 1.0000
9.750 1.3326 0.01620 0.00949 -0.0629 0.0414 1.0000
10.000 1.3472 0.01682 0.01007 -0.0609 0.0335 1.0000
10.250 1.3592 0.01761 0.01080 -0.0587 0.0236 1.0000
10.500 1.3730 0.01833 0.01150 -0.0568 0.0193 1.0000
10.750 1.3881 0.01898 0.01217 -0.0552 0.0171 1.0000
11.000 1.4035 0.01962 0.01284 -0.0536 0.0158 1.0000
11.250 1.4179 0.02034 0.01359 -0.0520 0.0146 1.0000
11.500 1.4330 0.02104 0.01432 -0.0506 0.0138 1.0000
11.750 1.4479 0.02175 0.01507 -0.0492 0.0129 1.0000
12.000 1.4615 0.02257 0.01593 -0.0477 0.0119 1.0000
12.250 1.4742 0.02348 0.01687 -0.0462 0.0109 1.0000
12.500 1.4872 0.02438 0.01781 -0.0448 0.0099 1.0000
12.750 1.4988 0.02541 0.01887 -0.0434 0.0088 1.0000
13.000 1.5096 0.02654 0.02002 -0.0420 0.0083 1.0000
13.250 1.5198 0.02773 0.02125 -0.0406 0.0079 1.0000
13.500 1.5295 0.02899 0.02256 -0.0393 0.0077 1.0000
13.750 1.5386 0.03036 0.02398 -0.0380 0.0074 1.0000
14.000 1.5468 0.03182 0.02550 -0.0368 0.0071 1.0000
14.250 1.5543 0.03338 0.02713 -0.0357 0.0069 1.0000
14.500 1.5611 0.03505 0.02886 -0.0346 0.0067 1.0000
14.750 1.5686 0.03671 0.03059 -0.0337 0.0066 1.0000
15.000 1.5750 0.03848 0.03244 -0.0328 0.0065 1.0000
15.250 1.5805 0.04039 0.03442 -0.0320 0.0063 1.0000
15.500 1.5852 0.04244 0.03656 -0.0312 0.0062 1.0000
15.750 1.5889 0.04465 0.03885 -0.0306 0.0060 1.0000
16.000 1.5915 0.04701 0.04129 -0.0300 0.0058 1.0000
16.250 1.5931 0.04954 0.04391 -0.0296 0.0057 1.0000
16.500 1.5934 0.05229 0.04674 -0.0292 0.0055 1.0000
16.750 1.5924 0.05527 0.04981 -0.0290 0.0054 1.0000
17.000 1.5899 0.05847 0.05310 -0.0289 0.0052 1.0000
17.250 1.5853 0.06202 0.05674 -0.0290 0.0051 1.0000
17.500 1.5790 0.06593 0.06075 -0.0293 0.0050 1.0000
17.750 1.5765 0.06941 0.06433 -0.0297 0.0049 1.0000
18.000 1.5732 0.07306 0.06808 -0.0302 0.0048 1.0000
18.250 1.5679 0.07706 0.07219 -0.0309 0.0048 1.0000
18.500 1.5617 0.08128 0.07650 -0.0318 0.0047 1.0000
18.750 1.5542 0.08577 0.08111 -0.0329 0.0046 1.0000
19.000 1.5451 0.09058 0.08603 -0.0342 0.0045 1.0000
19.250 1.5352 0.09557 0.09112 -0.0356 0.0044 1.0000
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Polar data table (+)
Polar graphs
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