GOE 438 AIRFOIL (goe438-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 438 AIRFOIL (goe438-il) Reynolds number: 200,000 Max Cl/Cd: 68.39 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe438-il-200000.txt Download as CSV file: xf-goe438-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 438 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3625 0.09920 0.09554 -0.0394 1.0000 0.0654
-9.250 -0.3830 0.09629 0.09272 -0.0427 1.0000 0.0658
-9.000 -0.4074 0.09351 0.09004 -0.0439 1.0000 0.0659
-8.750 -0.3656 0.08898 0.08545 -0.0376 1.0000 0.0678
-8.500 -0.3614 0.08694 0.08343 -0.0358 1.0000 0.0690
-8.250 -0.3654 0.08492 0.08147 -0.0342 1.0000 0.0702
-8.000 -0.3769 0.08309 0.07972 -0.0322 1.0000 0.0716
-7.750 -0.3986 0.08174 0.07846 -0.0290 1.0000 0.0724
-7.500 -0.4216 0.08019 0.07699 -0.0264 1.0000 0.0732
-7.250 -0.4412 0.07778 0.07462 -0.0259 1.0000 0.0749
-7.000 -0.4341 0.06707 0.06366 -0.0430 0.9926 0.0793
-6.750 -0.4097 0.06514 0.06177 -0.0427 0.9888 0.0809
-6.500 -0.3816 0.06219 0.05879 -0.0460 0.9844 0.0840
-6.250 -0.3587 0.05412 0.05021 -0.0571 0.9746 0.0932
-6.000 -0.3279 0.05178 0.04795 -0.0589 0.9713 0.0952
-5.750 -0.3017 0.04949 0.04560 -0.0607 0.9648 0.0991
-5.500 -0.2716 0.04470 0.04038 -0.0662 0.9581 0.1089
-5.250 -0.2393 0.04254 0.03825 -0.0684 0.9538 0.1121
-5.000 -0.2120 0.03959 0.03484 -0.0710 0.9449 0.1237
-4.750 -0.1743 0.03734 0.03268 -0.0739 0.9418 0.1276
-4.500 -0.1467 0.03519 0.03017 -0.0753 0.9325 0.1399
-4.250 -0.1080 0.03297 0.02799 -0.0781 0.9284 0.1448
-4.000 -0.0668 0.03077 0.02559 -0.0817 0.9252 0.1585
-3.750 -0.0384 0.02488 0.01848 -0.0806 0.9145 0.1093
-3.500 0.0026 0.02181 0.01467 -0.0819 0.9102 0.0928
-3.250 0.0316 0.02057 0.01325 -0.0817 0.8999 0.0928
-3.000 0.0698 0.01915 0.01166 -0.0833 0.8941 0.0930
-2.750 0.0981 0.01820 0.01056 -0.0829 0.8825 0.0928
-2.500 0.1297 0.01716 0.00941 -0.0832 0.8726 0.0931
-2.250 0.1622 0.01621 0.00837 -0.0836 0.8628 0.0937
-2.000 0.1899 0.01550 0.00762 -0.0831 0.8497 0.0950
-1.750 0.2180 0.01497 0.00707 -0.0828 0.8366 0.0975
-1.500 0.2462 0.01450 0.00656 -0.0824 0.8234 0.0997
-1.250 0.2739 0.01406 0.00606 -0.0819 0.8102 0.1016
-1.000 0.3011 0.01369 0.00562 -0.0813 0.7966 0.1036
-0.750 0.3265 0.01341 0.00529 -0.0804 0.7816 0.1058
-0.500 0.3507 0.01297 0.00488 -0.0794 0.7664 0.1093
-0.250 0.3755 0.01273 0.00464 -0.0785 0.7512 0.1149
0.000 0.4006 0.01255 0.00442 -0.0776 0.7357 0.1212
0.250 0.4252 0.01230 0.00418 -0.0766 0.7202 0.1312
0.500 0.4497 0.01204 0.00397 -0.0756 0.7044 0.1579
0.750 0.5464 0.00979 0.00393 -0.0894 0.6851 1.0000
1.000 0.5686 0.00991 0.00388 -0.0880 0.6679 1.0000
1.250 0.5909 0.01007 0.00387 -0.0867 0.6512 1.0000
1.500 0.6132 0.01024 0.00390 -0.0854 0.6347 1.0000
1.750 0.6355 0.01044 0.00395 -0.0841 0.6183 1.0000
2.000 0.6576 0.01065 0.00403 -0.0828 0.6014 1.0000
2.250 0.6796 0.01085 0.00413 -0.0815 0.5846 1.0000
2.500 0.7017 0.01105 0.00423 -0.0801 0.5680 1.0000
2.750 0.7237 0.01125 0.00433 -0.0788 0.5513 1.0000
3.000 0.7456 0.01146 0.00445 -0.0775 0.5346 1.0000
3.250 0.7674 0.01167 0.00457 -0.0762 0.5181 1.0000
3.500 0.7893 0.01189 0.00471 -0.0749 0.5024 1.0000
3.750 0.8115 0.01215 0.00487 -0.0737 0.4881 1.0000
4.000 0.8338 0.01243 0.00504 -0.0725 0.4746 1.0000
4.250 0.8561 0.01270 0.00525 -0.0713 0.4613 1.0000
4.500 0.8786 0.01298 0.00548 -0.0702 0.4486 1.0000
4.750 0.9011 0.01329 0.00574 -0.0692 0.4366 1.0000
5.000 0.9236 0.01362 0.00598 -0.0681 0.4249 1.0000
5.500 0.9671 0.01419 0.00647 -0.0657 0.3997 1.0000
5.750 0.9893 0.01449 0.00675 -0.0646 0.3887 1.0000
6.000 1.0119 0.01485 0.00703 -0.0636 0.3792 1.0000
6.250 1.0341 0.01512 0.00736 -0.0626 0.3697 1.0000
6.500 1.0567 0.01548 0.00769 -0.0617 0.3612 1.0000
6.750 1.0789 0.01578 0.00802 -0.0606 0.3526 1.0000
7.000 1.1014 0.01614 0.00839 -0.0597 0.3448 1.0000
7.250 1.1232 0.01646 0.00873 -0.0586 0.3365 1.0000
7.500 1.1446 0.01679 0.00910 -0.0575 0.3277 1.0000
7.750 1.1657 0.01712 0.00943 -0.0563 0.3194 1.0000
8.000 1.1863 0.01744 0.00984 -0.0551 0.3108 1.0000
8.250 1.2067 0.01781 0.01019 -0.0538 0.3026 1.0000
8.500 1.2263 0.01809 0.01061 -0.0524 0.2937 1.0000
8.750 1.2456 0.01848 0.01098 -0.0510 0.2855 1.0000
9.000 1.2640 0.01877 0.01142 -0.0494 0.2762 1.0000
9.250 1.2812 0.01912 0.01182 -0.0477 0.2665 1.0000
9.500 1.2967 0.01950 0.01221 -0.0457 0.2562 1.0000
9.750 1.3119 0.01983 0.01266 -0.0436 0.2441 1.0000
10.000 1.3237 0.02021 0.01311 -0.0410 0.2304 1.0000
10.250 1.3325 0.02070 0.01361 -0.0379 0.2140 1.0000
10.500 1.3396 0.02135 0.01424 -0.0348 0.1910 1.0000
10.750 1.3419 0.02236 0.01512 -0.0314 0.1611 1.0000
11.000 1.3398 0.02379 0.01636 -0.0277 0.1334 1.0000
11.250 1.3367 0.02544 0.01787 -0.0243 0.1155 1.0000
11.500 1.3362 0.02705 0.01944 -0.0215 0.1035 1.0000
11.750 1.3394 0.02853 0.02095 -0.0192 0.0944 1.0000
12.000 1.3404 0.03022 0.02267 -0.0170 0.0880 1.0000
12.250 1.3424 0.03194 0.02443 -0.0152 0.0823 1.0000
12.500 1.3411 0.03401 0.02651 -0.0134 0.0784 1.0000
12.750 1.3431 0.03594 0.02854 -0.0120 0.0745 1.0000
13.000 1.3401 0.03839 0.03102 -0.0108 0.0710 1.0000
13.250 1.3350 0.04117 0.03384 -0.0097 0.0680 1.0000
13.500 1.3343 0.04370 0.03650 -0.0090 0.0649 1.0000
13.750 1.3297 0.04670 0.03955 -0.0085 0.0619 1.0000
14.000 1.3217 0.05007 0.04285 -0.0077 0.0588 1.0000
14.250 1.3202 0.05303 0.04601 -0.0076 0.0559 1.0000
14.500 1.3164 0.05624 0.04928 -0.0075 0.0529 1.0000
14.750 1.3160 0.05888 0.05179 -0.0063 0.0495 1.0000
15.000 1.3130 0.06227 0.05540 -0.0068 0.0474 1.0000
15.250 1.3120 0.06540 0.05864 -0.0071 0.0451 1.0000
15.500 1.3139 0.06810 0.06133 -0.0070 0.0429 1.0000
15.750 1.3180 0.07058 0.06382 -0.0065 0.0407 1.0000
16.000 1.3138 0.07438 0.06782 -0.0075 0.0391 1.0000
16.250 1.3136 0.07766 0.07123 -0.0081 0.0377 1.0000
16.500 1.3148 0.08076 0.07440 -0.0087 0.0365 1.0000
16.750 1.3195 0.08325 0.07687 -0.0088 0.0352 1.0000
17.000 1.3210 0.08639 0.08010 -0.0090 0.0341 1.0000
17.250 1.3133 0.09107 0.08501 -0.0109 0.0333 1.0000
17.500 1.3082 0.09546 0.08960 -0.0124 0.0326 1.0000
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Polar data table (+)
Polar graphs
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