GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 431 AIRFOIL (goe431-il) Reynolds number: 100,000 Max Cl/Cd: 62.74 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe431-il-100000.txt Download as CSV file: xf-goe431-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 -0.4058 0.11662 0.11275 -0.0083 1.0000 0.1230
-6.250 -0.4293 0.11619 0.11240 -0.0074 1.0000 0.1240
-6.000 -0.4459 0.11465 0.11094 -0.0158 1.0000 0.1249
-5.750 -0.4374 0.11001 0.10629 -0.0088 1.0000 0.1259
-5.500 -0.4308 0.10684 0.10312 -0.0059 1.0000 0.1272
-5.250 -0.3012 0.03827 0.03253 -0.1085 1.0000 0.0672
-5.000 -0.2672 0.03599 0.02998 -0.1120 1.0000 0.0716
-4.750 -0.2267 0.03313 0.02648 -0.1169 1.0000 0.0784
-4.500 -0.1979 0.03223 0.02555 -0.1180 1.0000 0.0856
-4.250 -0.1720 0.03208 0.02544 -0.1183 1.0000 0.0967
-4.000 -0.1477 0.03244 0.02575 -0.1180 1.0000 0.1126
-3.750 -0.1319 0.03405 0.02756 -0.1156 1.0000 0.1273
-3.500 -0.1172 0.03574 0.02944 -0.1129 1.0000 0.1438
-3.250 -0.0989 0.03704 0.03070 -0.1113 1.0000 0.1670
-3.000 -0.0822 0.03818 0.03190 -0.1096 1.0000 0.1864
-2.750 0.0696 0.04424 0.03805 -0.1263 0.9289 0.2376
-2.500 0.0964 0.04359 0.03721 -0.1272 0.9199 0.2516
-2.250 0.1387 0.04371 0.03720 -0.1298 0.9119 0.2675
-2.000 0.1712 0.04340 0.03670 -0.1314 0.9031 0.2819
-1.750 0.1981 0.04366 0.03710 -0.1304 0.8949 0.2906
-1.500 0.2469 0.04210 0.03519 -0.1358 0.8870 0.2907
-1.250 0.2947 0.04065 0.03337 -0.1407 0.8795 0.2878
-1.000 0.3396 0.03956 0.03196 -0.1445 0.8717 0.2869
-0.750 0.3779 0.03892 0.03113 -0.1467 0.8631 0.2887
-0.500 0.4250 0.03804 0.03002 -0.1501 0.8554 0.2897
-0.250 0.4588 0.03747 0.02928 -0.1512 0.8456 0.2904
0.000 0.5096 0.03658 0.02819 -0.1548 0.8392 0.2921
0.250 0.5396 0.03613 0.02761 -0.1551 0.8284 0.2940
0.500 0.5934 0.03514 0.02642 -0.1588 0.8230 0.2972
0.750 0.6215 0.03461 0.02596 -0.1585 0.8112 0.3010
1.000 0.6779 0.03332 0.02464 -0.1622 0.8067 0.3081
1.250 0.7077 0.03268 0.02394 -0.1618 0.7941 0.3134
1.500 0.7667 0.03093 0.02229 -0.1656 0.7904 0.3219
1.750 0.7974 0.03006 0.02141 -0.1651 0.7774 0.3302
2.000 0.8319 0.02895 0.02043 -0.1651 0.7653 0.3411
2.250 0.8928 0.02676 0.01836 -0.1688 0.7609 0.3640
2.500 0.9294 0.02539 0.01716 -0.1689 0.7470 0.3945
2.750 0.9693 0.02382 0.01586 -0.1692 0.7319 0.4497
3.000 1.0119 0.02213 0.01445 -0.1700 0.7142 0.5467
3.250 1.0330 0.02101 0.01354 -0.1674 0.6841 0.6279
3.500 1.0514 0.01963 0.01264 -0.1643 0.6471 1.0000
3.750 1.0991 0.01879 0.01137 -0.1667 0.6106 1.0000
4.000 1.1441 0.01857 0.01071 -0.1690 0.5804 1.0000
4.250 1.1803 0.01886 0.01064 -0.1703 0.5591 1.0000
4.500 1.2145 0.01936 0.01086 -0.1713 0.5438 1.0000
4.750 1.2504 0.01993 0.01119 -0.1728 0.5321 1.0000
5.000 1.2794 0.02055 0.01174 -0.1732 0.5218 1.0000
5.250 1.3121 0.02121 0.01227 -0.1742 0.5133 1.0000
5.500 1.3411 0.02187 0.01292 -0.1745 0.5056 1.0000
5.750 1.3750 0.02259 0.01354 -0.1758 0.4997 1.0000
6.000 1.3993 0.02327 0.01432 -0.1753 0.4933 1.0000
6.250 1.4296 0.02399 0.01501 -0.1759 0.4866 1.0000
6.500 1.4538 0.02474 0.01584 -0.1755 0.4799 1.0000
6.750 1.4784 0.02546 0.01660 -0.1750 0.4726 1.0000
7.000 1.5059 0.02625 0.01742 -0.1751 0.4663 1.0000
7.250 1.5258 0.02699 0.01834 -0.1739 0.4601 1.0000
7.500 1.5542 0.02776 0.01911 -0.1741 0.4538 1.0000
7.750 1.5737 0.02858 0.02010 -0.1729 0.4476 1.0000
8.000 1.5953 0.02937 0.02106 -0.1720 0.4416 1.0000
8.250 1.6265 0.03023 0.02191 -0.1727 0.4360 1.0000
8.500 1.6385 0.03107 0.02306 -0.1701 0.4294 1.0000
8.750 1.6656 0.03167 0.02363 -0.1700 0.4195 1.0000
9.000 1.6745 0.03219 0.02434 -0.1667 0.4080 1.0000
9.250 1.6852 0.03258 0.02480 -0.1637 0.3944 1.0000
9.500 1.6963 0.03294 0.02521 -0.1607 0.3815 1.0000
9.750 1.7094 0.03325 0.02554 -0.1581 0.3692 1.0000
10.000 1.7206 0.03349 0.02578 -0.1552 0.3566 1.0000
10.250 1.7164 0.03405 0.02662 -0.1499 0.3461 1.0000
10.500 1.7151 0.03445 0.02712 -0.1451 0.3349 1.0000
10.750 1.7121 0.03484 0.02755 -0.1401 0.3228 1.0000
11.000 1.7023 0.03553 0.02837 -0.1345 0.3103 1.0000
11.250 1.6906 0.03656 0.02961 -0.1291 0.2971 1.0000
11.500 1.6792 0.03781 0.03104 -0.1242 0.2813 1.0000
11.750 1.6657 0.03946 0.03287 -0.1196 0.2586 1.0000
12.000 1.6478 0.04182 0.03521 -0.1152 0.2102 1.0000
12.250 1.6216 0.04565 0.03856 -0.1110 0.1675 1.0000
12.500 1.5955 0.05040 0.04304 -0.1076 0.1344 1.0000
12.750 1.5718 0.05543 0.04794 -0.1050 0.1051 1.0000
13.000 1.5501 0.06063 0.05306 -0.1031 0.0881 1.0000
13.250 1.5306 0.06594 0.05838 -0.1019 0.0788 1.0000
13.500 1.5108 0.07167 0.06414 -0.1014 0.0738 1.0000
13.750 1.4950 0.07725 0.06988 -0.1014 0.0694 1.0000
14.000 1.4789 0.08319 0.07592 -0.1020 0.0664 1.0000
14.250 1.4627 0.08935 0.08214 -0.1029 0.0640 1.0000
14.500 1.4551 0.09425 0.08714 -0.1035 0.0610 1.0000
14.750 1.4511 0.09854 0.09151 -0.1039 0.0579 1.0000
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Polar data table (+)
Polar graphs
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