GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 371 AIRFOIL (goe371-il) Reynolds number: 500,000 Max Cl/Cd: 103.93 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe371-il-500000-n5.txt Download as CSV file: xf-goe371-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3218 0.09734 0.09509 -0.0283 1.0000 0.0068
-8.500 -0.3211 0.09438 0.09217 -0.0285 1.0000 0.0069
-8.250 -0.3220 0.09157 0.08939 -0.0285 1.0000 0.0071
-8.000 -0.3187 0.08706 0.08491 -0.0314 0.9979 0.0076
-7.500 -0.2905 0.07863 0.07649 -0.0409 0.9799 0.0076
-7.250 -0.2696 0.07435 0.07221 -0.0474 0.9713 0.0079
-7.000 -0.2433 0.06871 0.06655 -0.0565 0.9635 0.0079
-6.750 -0.2146 0.06401 0.06180 -0.0647 0.9534 0.0081
-6.500 -0.1849 0.05969 0.05743 -0.0723 0.9409 0.0085
-6.250 -0.1556 0.05447 0.05212 -0.0804 0.9251 0.0088
-6.000 -0.1294 0.04915 0.04667 -0.0873 0.9062 0.0094
-5.750 -0.1038 0.03954 0.03677 -0.0963 0.8858 0.0107
-5.500 -0.0797 0.03657 0.03361 -0.0986 0.8702 0.0112
-5.250 -0.0553 0.03363 0.03048 -0.1004 0.8558 0.0117
-5.000 -0.0346 0.01952 0.01525 -0.1038 0.8426 0.0150
-4.750 -0.0085 0.01995 0.01564 -0.1036 0.8303 0.0155
-4.500 0.0171 0.01960 0.01515 -0.1034 0.8193 0.0162
-4.000 0.0678 0.01577 0.01042 -0.1026 0.8007 0.0204
-3.750 0.0926 0.01445 0.00886 -0.1023 0.7924 0.0214
-3.500 0.1186 0.01404 0.00833 -0.1020 0.7831 0.0222
-3.250 0.1450 0.01376 0.00796 -0.1018 0.7744 0.0234
-3.000 0.1713 0.01319 0.00721 -0.1014 0.7662 0.0246
-2.750 0.1978 0.01251 0.00634 -0.1011 0.7585 0.0254
-2.500 0.2245 0.01205 0.00572 -0.1007 0.7519 0.0265
-2.250 0.2515 0.01169 0.00525 -0.1004 0.7454 0.0274
-2.000 0.2783 0.01132 0.00476 -0.1001 0.7381 0.0279
-1.750 0.3052 0.01104 0.00439 -0.0998 0.7311 0.0282
-1.500 0.3320 0.01070 0.00397 -0.0995 0.7239 0.0286
-1.250 0.3584 0.01014 0.00333 -0.0991 0.7172 0.0290
-1.000 0.3847 0.00970 0.00284 -0.0987 0.7096 0.0296
-0.750 0.4111 0.00939 0.00249 -0.0984 0.7019 0.0305
-0.500 0.4376 0.00919 0.00225 -0.0980 0.6928 0.0306
-0.250 0.4642 0.00901 0.00204 -0.0977 0.6823 0.0307
0.000 0.4906 0.00887 0.00186 -0.0973 0.6695 0.0309
0.250 0.5168 0.00877 0.00170 -0.0968 0.6518 0.0312
0.500 0.5423 0.00873 0.00156 -0.0962 0.6238 0.0319
0.750 0.5660 0.00885 0.00146 -0.0953 0.5761 0.0328
1.000 0.5895 0.00905 0.00144 -0.0944 0.5349 0.0340
1.250 0.6145 0.00919 0.00145 -0.0938 0.5112 0.0354
1.500 0.6402 0.00930 0.00148 -0.0934 0.4947 0.0370
1.750 0.6660 0.00941 0.00152 -0.0929 0.4798 0.0384
2.000 0.6918 0.00953 0.00158 -0.0925 0.4655 0.0414
2.250 0.7175 0.00952 0.00169 -0.0921 0.4535 0.1065
2.750 0.7803 0.00803 0.00208 -0.0944 0.4334 1.0000
3.000 0.8062 0.00818 0.00219 -0.0940 0.4254 1.0000
3.250 0.8320 0.00834 0.00230 -0.0936 0.4158 1.0000
3.500 0.8579 0.00848 0.00242 -0.0932 0.4072 1.0000
3.750 0.8835 0.00865 0.00256 -0.0927 0.3979 1.0000
4.000 0.9089 0.00884 0.00271 -0.0923 0.3840 1.0000
4.250 0.9341 0.00903 0.00286 -0.0918 0.3687 1.0000
4.500 0.9593 0.00923 0.00302 -0.0913 0.3526 1.0000
4.750 0.9836 0.00950 0.00322 -0.0907 0.3264 1.0000
5.000 1.0055 0.01000 0.00348 -0.0897 0.2774 1.0000
5.250 1.0268 0.01057 0.00384 -0.0887 0.2353 1.0000
5.500 1.0489 0.01107 0.00420 -0.0878 0.2072 1.0000
5.750 1.0712 0.01154 0.00457 -0.0870 0.1841 1.0000
6.000 1.0942 0.01195 0.00490 -0.0862 0.1675 1.0000
6.250 1.1173 0.01233 0.00524 -0.0855 0.1523 1.0000
6.500 1.1395 0.01279 0.00560 -0.0847 0.1290 1.0000
6.750 1.1607 0.01334 0.00603 -0.0837 0.1011 1.0000
7.000 1.1790 0.01417 0.00662 -0.0823 0.0652 1.0000
7.250 1.1987 0.01483 0.00719 -0.0811 0.0461 1.0000
7.500 1.2154 0.01578 0.00795 -0.0795 0.0185 1.0000
7.750 1.2361 0.01632 0.00854 -0.0783 0.0135 1.0000
8.000 1.2559 0.01692 0.00922 -0.0771 0.0114 1.0000
8.250 1.2743 0.01765 0.01003 -0.0756 0.0095 1.0000
8.500 1.2940 0.01820 0.01066 -0.0744 0.0089 1.0000
8.750 1.3126 0.01882 0.01137 -0.0730 0.0082 1.0000
9.000 1.3301 0.01951 0.01214 -0.0714 0.0076 1.0000
9.250 1.3460 0.02028 0.01298 -0.0697 0.0070 1.0000
9.500 1.3574 0.02135 0.01418 -0.0673 0.0064 1.0000
9.750 1.3711 0.02205 0.01496 -0.0652 0.0061 1.0000
10.000 1.3829 0.02282 0.01582 -0.0628 0.0057 1.0000
10.250 1.3922 0.02374 0.01684 -0.0602 0.0055 1.0000
10.500 1.4005 0.02476 0.01796 -0.0576 0.0052 1.0000
10.750 1.4088 0.02580 0.01909 -0.0551 0.0050 1.0000
11.000 1.4147 0.02705 0.02044 -0.0526 0.0049 1.0000
11.250 1.4204 0.02835 0.02183 -0.0503 0.0047 1.0000
11.500 1.4242 0.02987 0.02344 -0.0480 0.0045 1.0000
11.750 1.4214 0.03202 0.02573 -0.0454 0.0043 1.0000
12.000 1.4213 0.03409 0.02792 -0.0434 0.0043 1.0000
12.250 1.4208 0.03632 0.03029 -0.0417 0.0042 1.0000
12.500 1.4208 0.03864 0.03275 -0.0403 0.0041 1.0000
12.750 1.4253 0.04061 0.03486 -0.0393 0.0039 1.0000
13.000 1.4223 0.04346 0.03785 -0.0383 0.0039 1.0000
13.250 1.4226 0.04608 0.04061 -0.0377 0.0037 1.0000
13.500 1.4208 0.04903 0.04371 -0.0373 0.0036 1.0000
13.750 1.4156 0.05256 0.04738 -0.0371 0.0036 1.0000
14.000 1.4124 0.05598 0.05095 -0.0373 0.0035 1.0000
14.250 1.4068 0.05989 0.05500 -0.0379 0.0034 1.0000
14.500 1.4024 0.06385 0.05910 -0.0388 0.0033 1.0000
14.750 1.3955 0.06840 0.06379 -0.0400 0.0032 1.0000
15.000 1.3867 0.07345 0.06899 -0.0416 0.0032 1.0000
15.250 1.3812 0.07817 0.07385 -0.0435 0.0031 1.0000
15.500 1.3695 0.08407 0.07991 -0.0457 0.0031 1.0000
15.750 1.3595 0.08985 0.08583 -0.0482 0.0031 1.0000
16.000 1.3495 0.09582 0.09195 -0.0509 0.0031 1.0000
16.250 1.3387 0.10210 0.09837 -0.0539 0.0030 1.0000
16.500 1.3257 0.10894 0.10537 -0.0572 0.0030 1.0000
16.750 1.3155 0.11547 0.11202 -0.0605 0.0030 1.0000
17.000 1.3015 0.12298 0.11969 -0.0644 0.0030 1.0000
17.250 1.2915 0.12992 0.12674 -0.0683 0.0030 1.0000
17.500 1.2778 0.13781 0.13479 -0.0727 0.0030 1.0000
17.750 1.2651 0.14578 0.14289 -0.0772 0.0030 1.0000
18.000 1.2535 0.15368 0.15092 -0.0819 0.0030 1.0000
18.250 1.2401 0.16230 0.15968 -0.0870 0.0030 1.0000
18.500 1.2276 0.17094 0.16843 -0.0923 0.0030 1.0000
18.750 1.2133 0.18039 0.17800 -0.0980 0.0030 1.0000
19.000 1.1960 0.19140 0.18916 -0.1046 0.0031 1.0000
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Polar data table (+)
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