GOE 386 AIRFOIL (goe386-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 386 AIRFOIL (goe386-il) Reynolds number: 100,000 Max Cl/Cd: 40.82 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe386-il-100000-n5.txt Download as CSV file: xf-goe386-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 386 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3515 0.05744 0.05099 -0.1182 0.9175 0.0762
-10.750 -0.4095 0.05038 0.04343 -0.1208 0.8966 0.0763
-10.500 -0.4361 0.04647 0.03903 -0.1194 0.8801 0.0767
-10.250 -0.4319 0.04393 0.03621 -0.1188 0.8683 0.0772
-10.000 -0.4212 0.04235 0.03455 -0.1175 0.8533 0.0778
-9.750 -0.4068 0.04073 0.03280 -0.1167 0.8406 0.0785
-9.500 -0.3923 0.03914 0.03104 -0.1159 0.8274 0.0794
-9.250 -0.3804 0.03762 0.02930 -0.1145 0.8121 0.0804
-9.000 -0.3668 0.03600 0.02738 -0.1134 0.7981 0.0816
-8.750 -0.3516 0.03441 0.02539 -0.1123 0.7848 0.0828
-8.500 -0.3338 0.03314 0.02388 -0.1112 0.7699 0.0837
-8.250 -0.3107 0.03208 0.02275 -0.1107 0.7570 0.0846
-8.000 -0.2873 0.03107 0.02162 -0.1102 0.7449 0.0857
-7.750 -0.2653 0.03017 0.02058 -0.1095 0.7328 0.0870
-7.500 -0.2416 0.02925 0.01942 -0.1090 0.7233 0.0885
-7.250 -0.2196 0.02844 0.01837 -0.1083 0.7130 0.0899
-7.000 -0.1944 0.02765 0.01753 -0.1079 0.7046 0.0912
-6.750 -0.1699 0.02700 0.01685 -0.1075 0.6966 0.0924
-6.500 -0.1456 0.02639 0.01616 -0.1070 0.6887 0.0938
-6.250 -0.1199 0.02580 0.01541 -0.1066 0.6822 0.0956
-5.750 -0.0713 0.02479 0.01432 -0.1055 0.6684 0.0991
-5.500 -0.0457 0.02435 0.01382 -0.1052 0.6630 0.1010
-5.250 -0.0197 0.02396 0.01334 -0.1049 0.6583 0.1030
-4.750 0.0297 0.02330 0.01267 -0.1039 0.6480 0.1078
-4.500 0.0556 0.02302 0.01236 -0.1036 0.6436 0.1108
-4.250 0.0826 0.02275 0.01201 -0.1034 0.6396 0.1141
-4.000 0.1080 0.02255 0.01183 -0.1030 0.6352 0.1177
-3.500 0.1587 0.02223 0.01156 -0.1021 0.6261 0.1291
-3.250 0.1852 0.02209 0.01144 -0.1019 0.6223 0.1380
-3.000 0.2127 0.02196 0.01128 -0.1017 0.6185 0.1506
-2.750 0.2391 0.02189 0.01120 -0.1014 0.6139 0.1666
-2.500 0.2631 0.02186 0.01121 -0.1007 0.6079 0.1835
-2.250 0.2889 0.02181 0.01115 -0.1002 0.6021 0.2000
-2.000 0.3164 0.02174 0.01104 -0.1000 0.5968 0.2150
-1.750 0.3420 0.02173 0.01103 -0.0996 0.5913 0.2291
-1.500 0.3655 0.02174 0.01110 -0.0988 0.5849 0.2437
-1.250 0.3914 0.02174 0.01107 -0.0983 0.5795 0.2570
-1.000 0.4186 0.02171 0.01103 -0.0981 0.5753 0.2695
-0.750 0.4469 0.02172 0.01099 -0.0981 0.5716 0.2840
-0.500 0.4692 0.02179 0.01118 -0.0972 0.5667 0.2979
-0.250 0.4932 0.02183 0.01130 -0.0965 0.5617 0.3129
0.000 0.5188 0.02182 0.01134 -0.0960 0.5570 0.3318
0.250 0.5461 0.02176 0.01131 -0.0958 0.5527 0.3561
0.500 0.5723 0.02174 0.01137 -0.0955 0.5486 0.3867
0.750 0.5933 0.02177 0.01163 -0.0944 0.5431 0.4261
1.000 0.6160 0.02168 0.01180 -0.0935 0.5380 0.4881
1.500 0.6622 0.02108 0.01201 -0.0905 0.5293 0.7342
1.750 0.6931 0.02118 0.01245 -0.0904 0.5231 0.8686
2.000 0.7380 0.02138 0.01265 -0.0935 0.5162 0.9491
2.250 0.7870 0.02150 0.01262 -0.0977 0.5105 0.9910
2.500 0.8157 0.02169 0.01271 -0.0981 0.5052 1.0000
2.750 0.8282 0.02198 0.01300 -0.0955 0.4987 1.0000
3.000 0.8466 0.02214 0.01307 -0.0938 0.4928 1.0000
3.250 0.8702 0.02221 0.01298 -0.0930 0.4879 1.0000
3.500 0.8812 0.02258 0.01339 -0.0902 0.4804 1.0000
3.750 0.8984 0.02279 0.01354 -0.0884 0.4735 1.0000
4.000 0.9219 0.02287 0.01347 -0.0875 0.4682 1.0000
4.250 0.9318 0.02332 0.01398 -0.0847 0.4599 1.0000
4.500 0.9496 0.02355 0.01414 -0.0830 0.4532 1.0000
4.750 0.9679 0.02381 0.01432 -0.0815 0.4468 1.0000
5.000 0.9795 0.02425 0.01478 -0.0790 0.4387 1.0000
5.250 0.9976 0.02444 0.01487 -0.0774 0.4325 1.0000
5.500 1.0063 0.02498 0.01542 -0.0745 0.4245 1.0000
5.750 1.0205 0.02537 0.01575 -0.0725 0.4174 1.0000
6.000 1.0356 0.02580 0.01612 -0.0707 0.4108 1.0000
6.250 1.0470 0.02644 0.01676 -0.0686 0.4035 1.0000
6.500 1.0648 0.02684 0.01706 -0.0673 0.3981 1.0000
6.750 1.0777 0.02755 0.01776 -0.0656 0.3920 1.0000
7.000 1.0910 0.02826 0.01845 -0.0639 0.3862 1.0000
7.250 1.1092 0.02874 0.01883 -0.0628 0.3814 1.0000
7.500 1.1233 0.02950 0.01957 -0.0614 0.3762 1.0000
7.750 1.1348 0.03042 0.02050 -0.0599 0.3708 1.0000
8.000 1.1511 0.03109 0.02111 -0.0587 0.3663 1.0000
8.250 1.1738 0.03147 0.02137 -0.0582 0.3627 1.0000
8.500 1.1828 0.03266 0.02262 -0.0567 0.3583 1.0000
8.750 1.1945 0.03373 0.02372 -0.0554 0.3542 1.0000
9.000 1.2099 0.03459 0.02456 -0.0544 0.3505 1.0000
9.250 1.2310 0.03512 0.02502 -0.0539 0.3473 1.0000
9.500 1.2515 0.03575 0.02559 -0.0534 0.3441 1.0000
9.750 1.2552 0.03739 0.02734 -0.0517 0.3402 1.0000
10.000 1.2641 0.03876 0.02876 -0.0505 0.3366 1.0000
10.250 1.2786 0.03979 0.02980 -0.0497 0.3335 1.0000
10.500 1.2979 0.04052 0.03050 -0.0492 0.3308 1.0000
10.750 1.3257 0.04073 0.03063 -0.0492 0.3283 1.0000
11.000 1.3291 0.04255 0.03255 -0.0478 0.3252 1.0000
11.250 1.3232 0.04509 0.03525 -0.0461 0.3216 1.0000
11.500 1.3257 0.04713 0.03738 -0.0450 0.3183 1.0000
11.750 1.3368 0.04853 0.03882 -0.0443 0.3155 1.0000
12.000 1.3568 0.04922 0.03948 -0.0439 0.3129 1.0000
12.250 1.3886 0.04900 0.03916 -0.0440 0.3104 1.0000
12.500 1.3624 0.05343 0.04384 -0.0421 0.3066 1.0000
12.750 1.3209 0.05979 0.05047 -0.0406 0.3014 1.0000
13.000 1.3233 0.06208 0.05281 -0.0401 0.2975 1.0000
13.250 1.3593 0.06088 0.05150 -0.0399 0.2945 1.0000
13.500 1.3855 0.06077 0.05131 -0.0396 0.2913 1.0000
13.750 1.2051 0.08464 0.07589 -0.0403 0.2784 1.0000
14.000 1.2486 0.08189 0.07306 -0.0395 0.2772 1.0000
14.250 1.2894 0.07964 0.07075 -0.0389 0.2761 1.0000
14.500 1.3317 0.07736 0.06838 -0.0383 0.2749 1.0000
17.000 1.0145 0.16053 0.15271 -0.0617 0.1919 1.0000
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Polar data table (+)
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