GOE 440 AIRFOIL (goe440-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 440 AIRFOIL (goe440-il) Reynolds number: 200,000 Max Cl/Cd: 71.11 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe440-il-200000.txt Download as CSV file: xf-goe440-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 440 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.3033 0.09894 0.09595 -0.1196 0.8475 0.0122
-10.250 0.3095 0.09640 0.09339 -0.1198 0.8390 0.0125
-10.000 0.2313 0.11600 0.11297 -0.1182 0.8806 0.0106
-9.750 0.2411 0.11179 0.10873 -0.1175 0.8714 0.0110
-9.500 0.2494 0.10882 0.10570 -0.1176 0.8629 0.0114
-9.250 0.2574 0.10620 0.10307 -0.1180 0.8526 0.0118
-9.000 0.2655 0.10365 0.10049 -0.1185 0.8422 0.0122
-8.750 0.2739 0.10114 0.09795 -0.1191 0.8326 0.0126
-8.500 0.2827 0.09864 0.09539 -0.1198 0.8235 0.0130
-8.250 0.2913 0.09620 0.09294 -0.1206 0.8127 0.0135
-8.000 0.3003 0.09376 0.09045 -0.1215 0.8028 0.0140
-7.750 0.3096 0.09130 0.08793 -0.1224 0.7939 0.0145
-7.500 0.3188 0.08892 0.08551 -0.1233 0.7834 0.0151
-7.250 0.3282 0.08655 0.08311 -0.1244 0.7733 0.0157
-7.000 0.3380 0.08419 0.08067 -0.1254 0.7641 0.0163
-6.750 0.3479 0.08188 0.07832 -0.1266 0.7542 0.0170
-6.500 0.3579 0.07967 0.07608 -0.1279 0.7443 0.0177
-6.250 0.3684 0.07761 0.07395 -0.1295 0.7352 0.0184
-6.000 0.3774 0.07599 0.07229 -0.1312 0.7255 0.0189
-5.750 0.3881 0.07449 0.07077 -0.1340 0.7156 0.0192
-5.500 0.4053 0.07248 0.06869 -0.1385 0.7066 0.0195
-5.250 0.4247 0.07013 0.06631 -0.1432 0.6968 0.0196
-5.000 0.4459 0.06753 0.06366 -0.1481 0.6867 0.0197
-4.750 0.4684 0.06436 0.06044 -0.1531 0.6778 0.0198
-4.500 0.4642 0.06054 0.05659 -0.1474 0.6687 0.0212
-4.250 0.4798 0.05799 0.05399 -0.1489 0.6587 0.0226
-4.000 0.5026 0.05522 0.05112 -0.1532 0.6491 0.0243
-3.750 0.5305 0.05218 0.04801 -0.1591 0.6384 0.0264
-3.500 0.5828 0.04817 0.04387 -0.1726 0.6268 0.0292
-3.250 0.6521 0.04345 0.03871 -0.1895 0.6153 0.0298
-3.000 0.6561 0.04018 0.03555 -0.1867 0.6058 0.0319
-2.750 0.6975 0.03681 0.03196 -0.1936 0.5941 0.0360
-2.500 0.7561 0.03235 0.02705 -0.2043 0.5822 0.0417
-2.000 0.8461 0.02725 0.02105 -0.2157 0.5597 0.0673
-1.750 0.8831 0.02526 0.01878 -0.2194 0.5494 0.0969
-1.250 0.9660 0.02181 0.01423 -0.2234 0.5310 0.0621
-1.000 1.0031 0.02032 0.01219 -0.2234 0.5225 0.0289
-0.750 1.0375 0.01906 0.01067 -0.2246 0.5145 0.0253
-0.500 1.0705 0.01837 0.00981 -0.2255 0.5068 0.0259
-0.250 1.1047 0.01798 0.00921 -0.2271 0.4996 0.0378
0.000 1.1426 0.01700 0.00939 -0.2300 0.4924 0.5545
0.250 1.1690 0.01722 0.00949 -0.2300 0.4861 0.6148
0.500 1.1940 0.01735 0.00962 -0.2298 0.4795 0.6751
0.750 1.2169 0.01746 0.00965 -0.2289 0.4743 0.7772
1.000 1.2323 0.01736 0.00969 -0.2265 0.4688 1.0000
1.250 1.2588 0.01771 0.00987 -0.2268 0.4632 1.0000
1.500 1.2764 0.01795 0.00989 -0.2254 0.4472 1.0000
1.750 1.2993 0.01829 0.01013 -0.2250 0.4393 1.0000
2.000 1.3090 0.01860 0.01022 -0.2222 0.4164 1.0000
2.250 1.3235 0.01901 0.01050 -0.2203 0.4006 1.0000
2.500 1.3286 0.01953 0.01085 -0.2168 0.3725 1.0000
2.750 1.3390 0.02015 0.01132 -0.2144 0.3506 1.0000
3.000 1.3403 0.02135 0.01214 -0.2108 0.3057 1.0000
3.250 1.3487 0.02243 0.01298 -0.2084 0.2782 1.0000
3.500 1.3518 0.02393 0.01421 -0.2054 0.2413 1.0000
3.750 1.3293 0.02736 0.01703 -0.1994 0.1616 1.0000
4.000 1.3067 0.03109 0.02040 -0.1940 0.0798 1.0000
4.250 1.3157 0.03250 0.02179 -0.1923 0.0377 1.0000
4.500 1.3303 0.03347 0.02277 -0.1913 0.0420 1.0000
4.750 1.4664 0.02538 0.01617 -0.2036 0.2771 1.0000
5.000 1.4670 0.02713 0.01767 -0.2006 0.2456 1.0000
5.250 1.4552 0.02992 0.02009 -0.1964 0.1992 1.0000
5.500 1.4291 0.03407 0.02382 -0.1911 0.1375 1.0000
5.750 1.4039 0.03849 0.02804 -0.1866 0.0754 1.0000
6.000 1.4073 0.04060 0.03019 -0.1848 0.0445 1.0000
6.250 1.4166 0.04220 0.03189 -0.1836 0.0423 1.0000
6.500 1.4228 0.04415 0.03399 -0.1822 0.0403 1.0000
6.750 1.4256 0.04650 0.03653 -0.1807 0.0381 1.0000
7.000 1.4230 0.04951 0.03981 -0.1790 0.0359 1.0000
7.250 1.4221 0.05249 0.04300 -0.1777 0.0330 1.0000
7.500 1.4163 0.05613 0.04687 -0.1763 0.0295 1.0000
7.750 1.4111 0.05980 0.05076 -0.1751 0.0256 1.0000
8.000 1.3976 0.06468 0.05590 -0.1739 0.0240 1.0000
8.250 1.3786 0.07048 0.06197 -0.1730 0.0234 1.0000
8.500 1.3575 0.07681 0.06854 -0.1724 0.0231 1.0000
8.750 1.3353 0.08360 0.07555 -0.1722 0.0229 1.0000
9.000 1.3665 0.08255 0.07446 -0.1717 0.0192 1.0000
9.250 1.3510 0.08849 0.08059 -0.1716 0.0187 1.0000
9.500 1.3343 0.09477 0.08705 -0.1718 0.0184 1.0000
9.750 1.3165 0.10135 0.09380 -0.1721 0.0182 1.0000
10.000 1.2989 0.10807 0.10069 -0.1727 0.0181 1.0000
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Polar data table (+)
Polar graphs
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