GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 371 AIRFOIL (goe371-il) Reynolds number: 500,000 Max Cl/Cd: 108.58 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe371-il-500000.txt Download as CSV file: xf-goe371-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 371 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2556 0.08632 0.08423 -0.0306 1.0000 0.0168
-8.500 -0.2537 0.08352 0.08146 -0.0301 1.0000 0.0170
-8.250 -0.3397 0.09319 0.09101 -0.0301 1.0000 0.0164
-8.000 -0.3317 0.09002 0.08786 -0.0280 1.0000 0.0167
-7.750 -0.3336 0.08794 0.08582 -0.0270 1.0000 0.0168
-7.500 -0.3390 0.08623 0.08416 -0.0249 1.0000 0.0170
-7.250 -0.3518 0.08512 0.08310 -0.0215 1.0000 0.0171
-7.000 -0.3324 0.08117 0.07916 -0.0266 0.9971 0.0175
-6.750 -0.3052 0.07668 0.07466 -0.0341 0.9927 0.0181
-6.500 -0.2767 0.07197 0.06992 -0.0421 0.9874 0.0189
-6.250 -0.2271 0.06511 0.06297 -0.0593 0.9816 0.0209
-6.000 -0.1897 0.05940 0.05718 -0.0690 0.9751 0.0211
-5.750 -0.1497 0.05334 0.05100 -0.0782 0.9714 0.0212
-5.500 -0.1291 0.04773 0.04535 -0.0827 0.9646 0.0219
-5.250 -0.1011 0.04538 0.04295 -0.0856 0.9587 0.0230
-2.750 0.1763 0.01730 0.01227 -0.0988 0.8472 0.0498
-2.500 0.2011 0.01607 0.01102 -0.0986 0.8385 0.0527
-2.250 0.2278 0.01575 0.01054 -0.0982 0.8297 0.0590
-2.000 0.2530 0.01457 0.00923 -0.0980 0.8216 0.0665
-1.750 0.2790 0.01405 0.00855 -0.0977 0.8134 0.0787
-1.500 0.3088 0.01124 0.00518 -0.0960 0.8059 0.0442
-1.250 0.3355 0.01047 0.00426 -0.0954 0.7979 0.0426
-1.000 0.3621 0.00995 0.00367 -0.0949 0.7896 0.0423
-0.750 0.3886 0.00959 0.00324 -0.0944 0.7821 0.0430
-0.500 0.4150 0.00920 0.00281 -0.0939 0.7735 0.0427
-0.250 0.4414 0.00892 0.00248 -0.0934 0.7654 0.0430
0.000 0.4676 0.00871 0.00222 -0.0928 0.7556 0.0438
0.250 0.4939 0.00854 0.00202 -0.0923 0.7440 0.0449
0.500 0.5200 0.00843 0.00186 -0.0918 0.7310 0.0459
0.750 0.5462 0.00836 0.00173 -0.0912 0.7172 0.0471
1.000 0.5723 0.00831 0.00162 -0.0907 0.7020 0.0493
1.250 0.5984 0.00827 0.00154 -0.0901 0.6851 0.0541
1.500 0.6236 0.00809 0.00154 -0.0895 0.6653 0.1416
1.750 0.6642 0.00634 0.00166 -0.0929 0.6327 1.0000
2.000 0.6874 0.00657 0.00165 -0.0917 0.5873 1.0000
2.250 0.7103 0.00688 0.00173 -0.0907 0.5502 1.0000
2.500 0.7347 0.00713 0.00183 -0.0899 0.5276 1.0000
2.750 0.7596 0.00736 0.00195 -0.0893 0.5112 1.0000
3.000 0.7848 0.00757 0.00208 -0.0887 0.4975 1.0000
3.250 0.8101 0.00776 0.00223 -0.0882 0.4850 1.0000
3.500 0.8355 0.00796 0.00237 -0.0877 0.4738 1.0000
3.750 0.8608 0.00816 0.00252 -0.0871 0.4635 1.0000
4.000 0.8863 0.00834 0.00267 -0.0866 0.4510 1.0000
4.250 0.9117 0.00851 0.00284 -0.0861 0.4389 1.0000
4.500 0.9371 0.00869 0.00300 -0.0856 0.4269 1.0000
4.750 0.9622 0.00888 0.00317 -0.0851 0.4119 1.0000
5.000 0.9870 0.00909 0.00334 -0.0845 0.3950 1.0000
5.250 1.0115 0.00932 0.00354 -0.0839 0.3755 1.0000
5.500 1.0350 0.00962 0.00373 -0.0831 0.3384 1.0000
5.750 1.0560 0.01017 0.00401 -0.0820 0.2820 1.0000
6.000 1.0762 0.01083 0.00442 -0.0808 0.2369 1.0000
6.250 1.0978 0.01138 0.00484 -0.0799 0.2095 1.0000
6.500 1.1201 0.01184 0.00523 -0.0790 0.1915 1.0000
6.750 1.1428 0.01226 0.00560 -0.0782 0.1745 1.0000
7.000 1.1655 0.01267 0.00598 -0.0774 0.1579 1.0000
7.250 1.1871 0.01317 0.00638 -0.0765 0.1363 1.0000
7.500 1.2077 0.01377 0.00684 -0.0754 0.1030 1.0000
7.750 1.2233 0.01485 0.00761 -0.0736 0.0591 1.0000
8.000 1.2378 0.01604 0.00855 -0.0716 0.0260 1.0000
8.250 1.2563 0.01680 0.00933 -0.0701 0.0203 1.0000
8.500 1.2740 0.01762 0.01020 -0.0685 0.0177 1.0000
8.750 1.2891 0.01865 0.01136 -0.0664 0.0162 1.0000
9.000 1.3061 0.01940 0.01222 -0.0648 0.0155 1.0000
9.250 1.3211 0.02029 0.01321 -0.0628 0.0149 1.0000
9.500 1.3341 0.02127 0.01429 -0.0606 0.0141 1.0000
9.750 1.3450 0.02227 0.01537 -0.0581 0.0135 1.0000
10.000 1.3519 0.02336 0.01654 -0.0549 0.0129 1.0000
10.250 1.3538 0.02480 0.01807 -0.0513 0.0122 1.0000
10.500 1.3497 0.02686 0.02027 -0.0472 0.0117 1.0000
10.750 1.3515 0.02872 0.02224 -0.0441 0.0115 1.0000
11.000 1.3604 0.02990 0.02355 -0.0421 0.0113 1.0000
11.250 1.3672 0.03138 0.02514 -0.0399 0.0112 1.0000
11.500 1.3731 0.03299 0.02688 -0.0379 0.0109 1.0000
11.750 1.3784 0.03475 0.02877 -0.0360 0.0106 1.0000
12.000 1.3824 0.03679 0.03095 -0.0342 0.0105 1.0000
12.250 1.3856 0.03896 0.03326 -0.0326 0.0102 1.0000
12.500 1.3880 0.04126 0.03573 -0.0311 0.0100 1.0000
12.750 1.3890 0.04385 0.03848 -0.0297 0.0100 1.0000
13.000 1.3882 0.04665 0.04145 -0.0285 0.0098 1.0000
13.250 1.3859 0.04973 0.04471 -0.0276 0.0097 1.0000
13.500 1.3828 0.05284 0.04796 -0.0271 0.0095 1.0000
13.750 1.3802 0.05587 0.05111 -0.0269 0.0093 1.0000
14.000 1.3711 0.06013 0.05559 -0.0269 0.0093 1.0000
14.250 1.3670 0.06358 0.05913 -0.0274 0.0091 1.0000
14.500 1.3587 0.06786 0.06356 -0.0283 0.0090 1.0000
14.750 1.3464 0.07306 0.06896 -0.0297 0.0090 1.0000
15.000 1.3399 0.07739 0.07337 -0.0314 0.0087 1.0000
15.250 1.3252 0.08360 0.07978 -0.0340 0.0087 1.0000
15.500 1.3074 0.09079 0.08722 -0.0373 0.0089 1.0000
15.750 1.2975 0.09650 0.09302 -0.0403 0.0087 1.0000
16.000 1.2812 0.10397 0.10068 -0.0444 0.0088 1.0000
16.250 1.2553 0.11409 0.11106 -0.0503 0.0090 1.0000
16.500 1.2426 0.12141 0.11851 -0.0547 0.0090 1.0000
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Polar data table (+)
Polar graphs
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