GOE 442 AIRFOIL (goe442-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 442 AIRFOIL (goe442-il) Reynolds number: 100,000 Max Cl/Cd: 54.28 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe442-il-100000.txt Download as CSV file: xf-goe442-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 442 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3613 0.09889 0.09406 -0.0242 1.0000 0.0694
-7.750 -0.3750 0.09808 0.09338 -0.0254 1.0000 0.0700
-7.500 -0.3793 0.09637 0.09174 -0.0295 1.0000 0.0704
-7.250 -0.3792 0.09409 0.08951 -0.0340 1.0000 0.0707
-7.000 -0.3653 0.08743 0.08289 -0.0219 1.0000 0.0740
-6.750 -0.3626 0.08484 0.08034 -0.0210 1.0000 0.0770
-6.500 -0.3619 0.08229 0.07784 -0.0215 1.0000 0.0795
-6.250 -0.3605 0.07974 0.07533 -0.0248 1.0000 0.0827
-6.000 -0.3509 0.07710 0.07254 -0.0363 1.0000 0.0849
-5.750 -0.3507 0.07270 0.06832 -0.0299 1.0000 0.0863
-5.500 -0.3459 0.06998 0.06565 -0.0268 1.0000 0.0886
-5.250 -0.3381 0.06725 0.06293 -0.0266 1.0000 0.0924
-5.000 -0.3166 0.06308 0.05851 -0.0357 1.0000 0.1000
-4.750 -0.3129 0.06021 0.05578 -0.0316 1.0000 0.1023
-4.500 -0.3018 0.05773 0.05330 -0.0309 1.0000 0.1077
-4.250 -0.2833 0.05410 0.04954 -0.0341 1.0000 0.1165
-4.000 -0.2649 0.05135 0.04663 -0.0359 1.0000 0.1300
-3.750 -0.2481 0.04897 0.04415 -0.0365 1.0000 0.1444
-3.500 -0.2378 0.04671 0.04200 -0.0341 1.0000 0.1516
-3.250 -0.2198 0.04434 0.03955 -0.0345 1.0000 0.1676
-3.000 -0.2001 0.04209 0.03716 -0.0355 1.0000 0.1907
-2.750 -0.1855 0.04018 0.03530 -0.0342 1.0000 0.2093
-2.250 -0.0949 0.02919 0.02246 -0.0424 1.0000 0.1174
-2.000 -0.0557 0.02607 0.01827 -0.0433 0.9981 0.1000
-1.750 -0.0053 0.02387 0.01556 -0.0472 0.9895 0.1002
-1.500 0.0439 0.02239 0.01394 -0.0514 0.9797 0.1084
-1.250 0.0959 0.02113 0.01234 -0.0556 0.9701 0.1159
-1.000 0.1448 0.02011 0.01127 -0.0593 0.9580 0.1246
-0.750 0.1921 0.01916 0.01038 -0.0627 0.9448 0.1389
-0.500 0.2391 0.01824 0.00955 -0.0658 0.9311 0.1550
-0.250 0.2864 0.01726 0.00885 -0.0690 0.9169 0.1993
0.000 0.3569 0.01462 0.00816 -0.0764 0.9101 1.0000
0.250 0.4057 0.01423 0.00754 -0.0796 0.8924 1.0000
0.500 0.4523 0.01378 0.00692 -0.0822 0.8732 1.0000
0.750 0.4945 0.01338 0.00637 -0.0838 0.8498 1.0000
1.000 0.5347 0.01304 0.00588 -0.0851 0.8232 1.0000
1.250 0.5698 0.01289 0.00555 -0.0855 0.7919 1.0000
1.500 0.6014 0.01291 0.00537 -0.0854 0.7600 1.0000
1.750 0.6303 0.01308 0.00532 -0.0848 0.7301 1.0000
2.000 0.6574 0.01333 0.00538 -0.0841 0.7028 1.0000
2.250 0.6835 0.01363 0.00547 -0.0832 0.6776 1.0000
2.500 0.7078 0.01396 0.00564 -0.0821 0.6524 1.0000
2.750 0.7323 0.01428 0.00581 -0.0810 0.6292 1.0000
3.000 0.7562 0.01461 0.00598 -0.0799 0.6060 1.0000
3.250 0.7800 0.01497 0.00618 -0.0787 0.5842 1.0000
3.500 0.8036 0.01533 0.00643 -0.0776 0.5635 1.0000
3.750 0.8280 0.01574 0.00676 -0.0767 0.5459 1.0000
4.000 0.8526 0.01617 0.00712 -0.0759 0.5303 1.0000
4.250 0.8770 0.01661 0.00751 -0.0751 0.5148 1.0000
4.500 0.9011 0.01703 0.00790 -0.0742 0.4991 1.0000
4.750 0.9248 0.01744 0.00829 -0.0732 0.4830 1.0000
5.000 0.9478 0.01780 0.00867 -0.0721 0.4660 1.0000
5.250 0.9701 0.01813 0.00904 -0.0709 0.4476 1.0000
5.500 0.9922 0.01844 0.00939 -0.0696 0.4285 1.0000
5.750 1.0141 0.01875 0.00968 -0.0683 0.4083 1.0000
6.000 1.0341 0.01905 0.01004 -0.0666 0.3827 1.0000
6.250 1.0533 0.01945 0.01038 -0.0648 0.3531 1.0000
6.500 1.0717 0.02004 0.01082 -0.0630 0.3214 1.0000
6.750 1.0908 0.02078 0.01147 -0.0614 0.2935 1.0000
7.000 1.1116 0.02163 0.01219 -0.0601 0.2737 1.0000
7.250 1.1337 0.02251 0.01304 -0.0591 0.2589 1.0000
7.500 1.1567 0.02341 0.01391 -0.0583 0.2476 1.0000
7.750 1.1794 0.02431 0.01496 -0.0574 0.2376 1.0000
8.000 1.2027 0.02530 0.01598 -0.0567 0.2294 1.0000
8.250 1.2262 0.02631 0.01710 -0.0560 0.2222 1.0000
8.500 1.2498 0.02745 0.01833 -0.0553 0.2156 1.0000
8.750 1.2713 0.02835 0.01936 -0.0544 0.2072 1.0000
9.000 1.2892 0.02917 0.02035 -0.0529 0.1967 1.0000
9.250 1.3052 0.02978 0.02102 -0.0513 0.1842 1.0000
9.500 1.3203 0.03046 0.02176 -0.0497 0.1719 1.0000
9.750 1.3359 0.03129 0.02262 -0.0481 0.1604 1.0000
10.000 1.3497 0.03217 0.02355 -0.0464 0.1482 1.0000
10.250 1.3584 0.03304 0.02457 -0.0439 0.1344 1.0000
10.500 1.3592 0.03400 0.02581 -0.0403 0.1180 1.0000
10.750 1.3545 0.03520 0.02715 -0.0361 0.0989 1.0000
11.000 1.3485 0.03652 0.02852 -0.0317 0.0844 1.0000
11.250 1.3460 0.03818 0.03026 -0.0282 0.0739 1.0000
11.500 1.3451 0.04007 0.03221 -0.0253 0.0668 1.0000
11.750 1.3437 0.04188 0.03404 -0.0229 0.0613 1.0000
12.000 1.3442 0.04437 0.03666 -0.0208 0.0571 1.0000
12.250 1.3457 0.04690 0.03938 -0.0190 0.0539 1.0000
12.500 1.3471 0.04945 0.04196 -0.0175 0.0513 1.0000
12.750 1.3499 0.05280 0.04539 -0.0162 0.0491 1.0000
13.000 1.3453 0.05613 0.04905 -0.0151 0.0477 1.0000
13.250 1.3388 0.05978 0.05298 -0.0144 0.0465 1.0000
13.500 1.3297 0.06379 0.05724 -0.0143 0.0454 1.0000
13.750 1.3192 0.06815 0.06185 -0.0148 0.0446 1.0000
14.000 1.3077 0.07271 0.06660 -0.0158 0.0435 1.0000
14.250 1.2926 0.07823 0.07237 -0.0176 0.0434 1.0000
14.500 1.2718 0.08497 0.07938 -0.0206 0.0436 1.0000
14.750 1.2470 0.09276 0.08743 -0.0247 0.0439 1.0000
15.000 1.2105 0.10349 0.09847 -0.0313 0.0453 1.0000
15.250 1.1701 0.11611 0.11131 -0.0395 0.0475 1.0000
15.500 1.1390 0.12775 0.12302 -0.0467 0.0490 1.0000
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Polar data table (+)
Polar graphs
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