GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 431 AIRFOIL (goe431-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.1 at α=0° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe431-il-1000000.txt Download as CSV file: xf-goe431-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 431 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3359 0.07529 0.07319 -0.1111 0.9713 0.0104
-12.500 -0.3397 0.06888 0.06668 -0.1173 0.9623 0.0106
-12.250 -0.3298 0.06286 0.06056 -0.1258 0.9568 0.0108
-12.000 -0.3163 0.05645 0.05401 -0.1363 0.9475 0.0109
-11.750 -0.2972 0.05007 0.04745 -0.1484 0.9352 0.0111
-11.500 -0.2809 0.04540 0.04261 -0.1568 0.9160 0.0116
-11.250 -0.2880 0.04206 0.03910 -0.1591 0.8917 0.0115
-11.000 -0.2945 0.03874 0.03563 -0.1617 0.8749 0.0115
-10.750 -0.2942 0.03510 0.03185 -0.1658 0.8636 0.0116
-10.500 -0.2872 0.03117 0.02777 -0.1713 0.8549 0.0117
-10.250 -0.2721 0.02713 0.02357 -0.1778 0.8486 0.0118
-10.000 -0.2498 0.02344 0.01971 -0.1840 0.8435 0.0120
-9.750 -0.2225 0.01995 0.01600 -0.1901 0.8392 0.0122
-9.500 -0.1946 0.01712 0.01293 -0.1949 0.8357 0.0126
-9.250 -0.1677 0.01551 0.01117 -0.1971 0.8326 0.0131
-9.000 -0.1404 0.01460 0.01017 -0.1982 0.8294 0.0135
-8.750 -0.1129 0.01389 0.00935 -0.1989 0.8258 0.0141
-8.500 -0.0850 0.01328 0.00860 -0.1996 0.8220 0.0147
-8.250 -0.0574 0.01271 0.00796 -0.2000 0.8192 0.0152
-8.000 -0.0296 0.01221 0.00737 -0.2004 0.8161 0.0157
-7.750 -0.0019 0.01139 0.00643 -0.2011 0.8128 0.0169
-7.500 0.0262 0.01099 0.00595 -0.2013 0.8100 0.0180
-7.250 0.0547 0.01065 0.00552 -0.2016 0.8070 0.0190
-7.000 0.0829 0.01017 0.00495 -0.2019 0.8044 0.0206
-6.750 0.1111 0.00979 0.00453 -0.2021 0.8016 0.0228
-6.500 0.1393 0.00943 0.00412 -0.2023 0.7986 0.0260
-6.250 0.1676 0.00908 0.00375 -0.2024 0.7956 0.0325
-6.000 0.1960 0.00877 0.00343 -0.2026 0.7928 0.0429
-5.750 0.2246 0.00850 0.00313 -0.2028 0.7900 0.0531
-5.500 0.2528 0.00813 0.00279 -0.2030 0.7875 0.0695
-5.250 0.2809 0.00780 0.00267 -0.2032 0.7847 0.1224
-5.000 0.3094 0.00784 0.00271 -0.2031 0.7817 0.1306
-4.750 0.3380 0.00795 0.00278 -0.2030 0.7788 0.1361
-4.500 0.3668 0.00809 0.00285 -0.2030 0.7755 0.1383
-4.250 0.3950 0.00797 0.00273 -0.2030 0.7730 0.1425
-4.000 0.4235 0.00803 0.00280 -0.2029 0.7702 0.1463
-3.750 0.4519 0.00810 0.00287 -0.2029 0.7674 0.1497
-3.500 0.4802 0.00809 0.00281 -0.2028 0.7642 0.1512
-3.250 0.5086 0.00811 0.00278 -0.2027 0.7610 0.1523
-3.000 0.5369 0.00811 0.00275 -0.2027 0.7580 0.1529
-2.750 0.5649 0.00795 0.00259 -0.2026 0.7547 0.1545
-2.500 0.5928 0.00777 0.00240 -0.2026 0.7508 0.1569
-2.250 0.6207 0.00771 0.00231 -0.2025 0.7467 0.1587
-2.000 0.6486 0.00766 0.00224 -0.2024 0.7427 0.1597
-1.750 0.6765 0.00757 0.00216 -0.2023 0.7379 0.1603
-1.500 0.7040 0.00751 0.00208 -0.2021 0.7324 0.1611
-1.250 0.7315 0.00747 0.00202 -0.2019 0.7267 0.1618
-1.000 0.7590 0.00742 0.00196 -0.2016 0.7194 0.1627
-0.750 0.7859 0.00740 0.00191 -0.2013 0.7117 0.1635
-0.500 0.8126 0.00738 0.00187 -0.2010 0.7011 0.1645
-0.250 0.8386 0.00739 0.00184 -0.2004 0.6864 0.1655
0.000 0.8621 0.00749 0.00183 -0.1994 0.6568 0.1664
0.250 0.8621 0.00872 0.00229 -0.1938 0.5046 0.1670
0.500 0.8804 0.00919 0.00253 -0.1919 0.4594 0.1677
0.750 0.9019 0.00949 0.00269 -0.1906 0.4318 0.1685
1.000 0.9246 0.00970 0.00281 -0.1896 0.4115 0.1696
1.250 0.9480 0.00986 0.00290 -0.1886 0.3964 0.1722
1.500 0.9715 0.01002 0.00301 -0.1878 0.3845 0.1749
1.750 0.9951 0.01017 0.00313 -0.1869 0.3750 0.1774
2.000 1.0192 0.01030 0.00325 -0.1861 0.3679 0.1800
2.250 1.0429 0.01045 0.00337 -0.1853 0.3616 0.1828
2.500 1.0660 0.01061 0.00351 -0.1843 0.3557 0.1862
2.750 1.0904 0.01069 0.00364 -0.1836 0.3518 0.1941
3.000 1.1138 0.01081 0.00378 -0.1827 0.3472 0.2047
3.250 1.1351 0.01095 0.00396 -0.1814 0.3420 0.2310
3.500 1.1575 0.01101 0.00413 -0.1803 0.3385 0.2732
3.750 1.1800 0.01108 0.00429 -0.1793 0.3354 0.3088
4.000 1.2018 0.01118 0.00448 -0.1781 0.3321 0.3432
4.250 1.2229 0.01131 0.00470 -0.1768 0.3292 0.3891
4.500 1.2429 0.01150 0.00498 -0.1753 0.3255 0.4418
4.750 1.2651 0.01163 0.00522 -0.1742 0.3234 0.4838
5.000 1.2876 0.01175 0.00543 -0.1732 0.3213 0.5135
5.250 1.3095 0.01191 0.00565 -0.1721 0.3192 0.5357
5.500 1.3309 0.01209 0.00588 -0.1709 0.3171 0.5545
5.750 1.3519 0.01229 0.00613 -0.1696 0.3149 0.5714
6.000 1.3713 0.01255 0.00642 -0.1681 0.3114 0.5884
6.250 1.3913 0.01277 0.00671 -0.1667 0.3080 0.6104
6.500 1.4140 0.01269 0.00696 -0.1659 0.3049 0.7459
6.750 1.4357 0.01256 0.00717 -0.1648 0.3005 1.0000
7.000 1.4552 0.01286 0.00747 -0.1633 0.2965 1.0000
7.250 1.4747 0.01317 0.00778 -0.1619 0.2923 1.0000
7.500 1.4975 0.01334 0.00798 -0.1611 0.2873 1.0000
7.750 1.5167 0.01367 0.00829 -0.1597 0.2806 1.0000
8.000 1.5369 0.01396 0.00860 -0.1584 0.2752 1.0000
8.250 1.5567 0.01427 0.00891 -0.1572 0.2672 1.0000
8.500 1.5750 0.01468 0.00928 -0.1557 0.2537 1.0000
8.750 1.5889 0.01533 0.00980 -0.1536 0.2280 1.0000
9.000 1.5857 0.01709 0.01111 -0.1491 0.1652 1.0000
9.250 1.5936 0.01825 0.01212 -0.1463 0.1396 1.0000
9.500 1.6032 0.01935 0.01308 -0.1439 0.1153 1.0000
10.000 1.5975 0.02348 0.01658 -0.1361 0.0267 1.0000
10.250 1.6076 0.02461 0.01770 -0.1340 0.0205 1.0000
10.500 1.6186 0.02570 0.01880 -0.1320 0.0176 1.0000
10.750 1.6312 0.02667 0.01982 -0.1303 0.0164 1.0000
11.000 1.6417 0.02782 0.02100 -0.1284 0.0151 1.0000
11.250 1.6506 0.02911 0.02235 -0.1264 0.0139 1.0000
11.500 1.6623 0.03020 0.02350 -0.1248 0.0134 1.0000
11.750 1.6725 0.03142 0.02477 -0.1231 0.0128 1.0000
12.000 1.6819 0.03275 0.02614 -0.1214 0.0122 1.0000
12.250 1.6885 0.03432 0.02778 -0.1195 0.0116 1.0000
12.500 1.6895 0.03646 0.03002 -0.1173 0.0109 1.0000
12.750 1.6991 0.03786 0.03148 -0.1158 0.0107 1.0000
13.000 1.7067 0.03947 0.03315 -0.1143 0.0103 1.0000
13.250 1.7131 0.04124 0.03499 -0.1128 0.0100 1.0000
13.500 1.7184 0.04317 0.03699 -0.1114 0.0097 1.0000
13.750 1.7222 0.04529 0.03919 -0.1099 0.0094 1.0000
14.000 1.7254 0.04755 0.04152 -0.1086 0.0091 1.0000
14.250 1.7253 0.05024 0.04430 -0.1072 0.0089 1.0000
14.500 1.7215 0.05346 0.04762 -0.1059 0.0086 1.0000
14.750 1.7111 0.05765 0.05194 -0.1047 0.0084 1.0000
15.000 1.7044 0.06156 0.05597 -0.1039 0.0082 1.0000
15.250 1.7039 0.06482 0.05933 -0.1034 0.0081 1.0000
15.500 1.7029 0.06828 0.06289 -0.1032 0.0080 1.0000
15.750 1.6994 0.07223 0.06694 -0.1032 0.0079 1.0000
16.000 1.6952 0.07645 0.07127 -0.1035 0.0077 1.0000
16.250 1.6901 0.08098 0.07591 -0.1041 0.0076 1.0000
16.500 1.6839 0.08587 0.08091 -0.1051 0.0074 1.0000
16.750 1.6770 0.09103 0.08618 -0.1064 0.0073 1.0000
17.000 1.6699 0.09630 0.09157 -0.1078 0.0072 1.0000
17.250 1.6625 0.10171 0.09708 -0.1095 0.0071 1.0000
17.500 1.6546 0.10719 0.10267 -0.1113 0.0070 1.0000
17.750 1.6463 0.11279 0.10837 -0.1133 0.0069 1.0000
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