GOE 436 AIRFOIL (goe436-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 436 AIRFOIL (goe436-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.34 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe436-il-1000000.txt Download as CSV file: xf-goe436-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 436 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
------ -------- --------- --------- -------- -------- --------
-15.250 -1.0513 0.04006 0.03768 -0.0916 1.0000 0.0176
-15.000 -1.0968 0.03482 0.03220 -0.0896 1.0000 0.0176
-14.750 -1.1110 0.03203 0.02922 -0.0865 1.0000 0.0177
-14.500 -1.1196 0.02965 0.02668 -0.0835 1.0000 0.0181
-14.250 -1.1196 0.02794 0.02486 -0.0807 1.0000 0.0185
-14.000 -1.1120 0.02681 0.02368 -0.0783 1.0000 0.0190
-13.750 -1.1016 0.02591 0.02271 -0.0761 1.0000 0.0195
-13.500 -1.0908 0.02501 0.02173 -0.0739 1.0000 0.0200
-13.250 -1.0790 0.02416 0.02079 -0.0718 1.0000 0.0205
-13.000 -1.0664 0.02335 0.01987 -0.0696 1.0000 0.0209
-12.750 -1.0528 0.02261 0.01901 -0.0676 1.0000 0.0213
-12.500 -1.0265 0.02148 0.01781 -0.0685 0.9987 0.0222
-12.250 -0.9938 0.02117 0.01751 -0.0698 0.9973 0.0230
-12.000 -0.9607 0.02079 0.01709 -0.0712 0.9958 0.0238
-11.750 -0.9275 0.02024 0.01645 -0.0728 0.9945 0.0245
-11.500 -0.8954 0.01974 0.01584 -0.0740 0.9930 0.0251
-11.250 -0.8689 0.01864 0.01463 -0.0746 0.9904 0.0259
-11.000 -0.8367 0.01837 0.01437 -0.0757 0.9884 0.0267
-10.750 -0.8026 0.01833 0.01435 -0.0770 0.9868 0.0274
-10.500 -0.7689 0.01807 0.01404 -0.0784 0.9853 0.0282
-10.250 -0.7352 0.01765 0.01354 -0.0798 0.9841 0.0289
-10.000 -0.7009 0.01726 0.01306 -0.0813 0.9831 0.0295
-9.750 -0.6759 0.01624 0.01190 -0.0813 0.9790 0.0303
-9.500 -0.6443 0.01588 0.01154 -0.0822 0.9764 0.0311
-9.250 -0.6099 0.01578 0.01145 -0.0836 0.9745 0.0318
-9.000 -0.5752 0.01560 0.01125 -0.0850 0.9730 0.0325
-8.750 -0.5404 0.01533 0.01093 -0.0865 0.9717 0.0334
-8.500 -0.5063 0.01494 0.01047 -0.0879 0.9702 0.0341
-8.250 -0.4791 0.01464 0.01010 -0.0878 0.9639 0.0346
-8.000 -0.4495 0.01359 0.00889 -0.0885 0.9586 0.0356
-7.750 -0.4193 0.01315 0.00843 -0.0890 0.9523 0.0364
-7.500 -0.3905 0.01296 0.00823 -0.0891 0.9443 0.0371
-7.250 -0.3618 0.01274 0.00797 -0.0892 0.9363 0.0378
-7.000 -0.3337 0.01246 0.00762 -0.0891 0.9268 0.0386
-6.750 -0.3073 0.01213 0.00722 -0.0887 0.9164 0.0394
-6.500 -0.2803 0.01185 0.00685 -0.0884 0.9056 0.0400
-6.000 -0.2281 0.01117 0.00597 -0.0874 0.8824 0.0413
-5.750 -0.2036 0.01055 0.00527 -0.0867 0.8719 0.0424
-5.500 -0.1775 0.01033 0.00500 -0.0862 0.8611 0.0432
-5.250 -0.1514 0.01016 0.00478 -0.0857 0.8500 0.0440
-5.000 -0.1251 0.01002 0.00459 -0.0852 0.8398 0.0449
-4.750 -0.0987 0.00987 0.00438 -0.0847 0.8308 0.0459
-4.500 -0.0723 0.00969 0.00415 -0.0843 0.8221 0.0468
-4.250 -0.0459 0.00956 0.00395 -0.0838 0.8130 0.0475
-4.000 -0.0192 0.00945 0.00380 -0.0834 0.8031 0.0479
-3.750 0.0048 0.00889 0.00318 -0.0825 0.7938 0.0497
-3.500 0.0309 0.00871 0.00298 -0.0820 0.7836 0.0509
-3.250 0.0575 0.00861 0.00286 -0.0816 0.7729 0.0523
-3.000 0.0838 0.00852 0.00273 -0.0811 0.7604 0.0536
-2.750 0.1098 0.00842 0.00257 -0.0805 0.7453 0.0548
-2.500 0.1357 0.00835 0.00244 -0.0799 0.7267 0.0558
-2.250 0.1613 0.00835 0.00234 -0.0792 0.7040 0.0565
-2.000 0.1850 0.00810 0.00199 -0.0782 0.6810 0.0591
-1.750 0.2100 0.00808 0.00190 -0.0775 0.6586 0.0611
-1.250 0.2609 0.00811 0.00177 -0.0762 0.6211 0.0648
-1.000 0.2868 0.00814 0.00173 -0.0757 0.6035 0.0662
-0.750 0.3124 0.00808 0.00161 -0.0751 0.5862 0.0689
-0.500 0.3381 0.00806 0.00154 -0.0745 0.5673 0.0728
-0.250 0.3636 0.00811 0.00151 -0.0739 0.5439 0.0763
0.000 0.3888 0.00820 0.00150 -0.0732 0.5140 0.0786
0.250 0.4129 0.00827 0.00147 -0.0724 0.4812 0.0871
0.500 0.4375 0.00837 0.00148 -0.0717 0.4554 0.0983
0.750 0.4620 0.00835 0.00152 -0.0710 0.4364 0.1413
1.000 0.4843 0.00799 0.00157 -0.0700 0.4233 0.3135
1.250 0.5029 0.00738 0.00165 -0.0684 0.4128 0.5841
1.500 0.5174 0.00677 0.00175 -0.0655 0.4048 0.8244
1.750 0.5753 0.00672 0.00196 -0.0718 0.3941 0.9693
2.250 0.6905 0.00709 0.00215 -0.0847 0.3713 0.9999
2.500 0.7140 0.00721 0.00221 -0.0838 0.3642 1.0000
2.750 0.7374 0.00729 0.00227 -0.0828 0.3592 1.0000
3.000 0.7603 0.00740 0.00234 -0.0817 0.3532 1.0000
3.250 0.7835 0.00752 0.00242 -0.0807 0.3468 1.0000
3.500 0.8069 0.00762 0.00249 -0.0797 0.3398 1.0000
3.750 0.8298 0.00777 0.00259 -0.0786 0.3331 1.0000
4.000 0.8538 0.00785 0.00267 -0.0778 0.3279 1.0000
4.250 0.8771 0.00799 0.00277 -0.0768 0.3211 1.0000
4.500 0.9007 0.00811 0.00288 -0.0759 0.3159 1.0000
4.750 0.9247 0.00822 0.00298 -0.0750 0.3111 1.0000
5.000 0.9482 0.00836 0.00309 -0.0741 0.3060 1.0000
5.250 0.9718 0.00850 0.00322 -0.0732 0.3010 1.0000
5.500 0.9960 0.00861 0.00334 -0.0724 0.2960 1.0000
5.750 1.0194 0.00876 0.00347 -0.0715 0.2899 1.0000
6.000 1.0432 0.00890 0.00360 -0.0707 0.2838 1.0000
6.250 1.0669 0.00905 0.00375 -0.0698 0.2769 1.0000
6.500 1.0901 0.00923 0.00390 -0.0689 0.2695 1.0000
6.750 1.1131 0.00941 0.00406 -0.0679 0.2600 1.0000
7.000 1.1361 0.00960 0.00423 -0.0670 0.2505 1.0000
7.250 1.1579 0.00987 0.00443 -0.0659 0.2349 1.0000
7.500 1.1774 0.01027 0.00470 -0.0644 0.2099 1.0000
7.750 1.1937 0.01089 0.00511 -0.0624 0.1746 1.0000
8.000 1.2088 0.01159 0.00561 -0.0603 0.1424 1.0000
8.250 1.2246 0.01223 0.00610 -0.0583 0.1170 1.0000
8.500 1.2397 0.01291 0.00661 -0.0561 0.0895 1.0000
8.750 1.2524 0.01371 0.00723 -0.0537 0.0640 1.0000
9.000 1.2708 0.01412 0.00764 -0.0521 0.0589 1.0000
9.250 1.2891 0.01452 0.00805 -0.0505 0.0565 1.0000
9.500 1.3050 0.01495 0.00849 -0.0484 0.0542 1.0000
9.750 1.3195 0.01540 0.00896 -0.0461 0.0517 1.0000
10.000 1.3356 0.01576 0.00937 -0.0442 0.0503 1.0000
10.250 1.3529 0.01609 0.00973 -0.0424 0.0492 1.0000
10.500 1.3691 0.01647 0.01016 -0.0406 0.0476 1.0000
10.750 1.3842 0.01693 0.01064 -0.0387 0.0460 1.0000
11.000 1.3976 0.01749 0.01122 -0.0366 0.0438 1.0000
11.250 1.4118 0.01802 0.01179 -0.0347 0.0420 1.0000
11.500 1.4296 0.01837 0.01218 -0.0333 0.0405 1.0000
11.750 1.4446 0.01888 0.01270 -0.0317 0.0378 1.0000
12.000 1.4580 0.01949 0.01331 -0.0299 0.0343 1.0000
12.250 1.4702 0.02019 0.01398 -0.0280 0.0291 1.0000
12.500 1.4790 0.02112 0.01487 -0.0259 0.0229 1.0000
12.750 1.4863 0.02218 0.01593 -0.0237 0.0198 1.0000
13.000 1.4936 0.02331 0.01710 -0.0217 0.0180 1.0000
13.250 1.4984 0.02467 0.01849 -0.0197 0.0166 1.0000
13.500 1.5065 0.02586 0.01977 -0.0182 0.0159 1.0000
13.750 1.5123 0.02729 0.02126 -0.0166 0.0151 1.0000
14.000 1.5171 0.02888 0.02291 -0.0153 0.0147 1.0000
14.250 1.5177 0.03090 0.02500 -0.0138 0.0139 1.0000
14.500 1.5175 0.03313 0.02732 -0.0127 0.0135 1.0000
14.750 1.5217 0.03506 0.02934 -0.0119 0.0132 1.0000
15.000 1.5234 0.03731 0.03167 -0.0113 0.0128 1.0000
15.250 1.5238 0.03982 0.03427 -0.0109 0.0125 1.0000
15.500 1.5219 0.04273 0.03728 -0.0108 0.0123 1.0000
15.750 1.5181 0.04596 0.04061 -0.0109 0.0120 1.0000
16.000 1.5130 0.04949 0.04423 -0.0113 0.0118 1.0000
16.250 1.5066 0.05328 0.04812 -0.0118 0.0117 1.0000
16.500 1.4956 0.05777 0.05272 -0.0127 0.0115 1.0000
16.750 1.4815 0.06286 0.05793 -0.0139 0.0112 1.0000
17.000 1.4653 0.06837 0.06356 -0.0153 0.0111 1.0000
17.250 1.4497 0.07387 0.06917 -0.0169 0.0109 1.0000
17.500 1.4353 0.07930 0.07470 -0.0184 0.0108 1.0000
17.750 1.4248 0.08416 0.07967 -0.0198 0.0108 1.0000
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Polar data table (+)
Polar graphs
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