GOE 496 AIRFOIL (goe496-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 496 AIRFOIL (goe496-il) Reynolds number: 500,000 Max Cl/Cd: 124.31 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe496-il-500000.txt Download as CSV file: xf-goe496-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 496 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3551 0.10580 0.10347 -0.0395 1.0000 0.0315
-10.000 -0.3495 0.10433 0.10202 -0.0380 1.0000 0.0320
-9.750 -0.3462 0.10266 0.10038 -0.0366 1.0000 0.0324
-9.500 -0.3448 0.10108 0.09882 -0.0352 1.0000 0.0330
-9.250 -0.3478 0.09918 0.09695 -0.0339 1.0000 0.0335
-9.000 -0.3371 0.09574 0.09352 -0.0372 0.9987 0.0356
-8.500 -0.3877 0.02814 0.02452 -0.1243 0.9719 0.0316
-8.250 -0.3576 0.02609 0.02238 -0.1271 0.9685 0.0326
-8.000 -0.3275 0.02521 0.02147 -0.1285 0.9639 0.0336
-7.750 -0.2929 0.02312 0.01912 -0.1318 0.9612 0.0346
-7.500 -0.2562 0.02125 0.01694 -0.1350 0.9593 0.0358
-7.250 -0.2182 0.02000 0.01542 -0.1379 0.9579 0.0371
-7.000 -0.1868 0.01914 0.01433 -0.1390 0.9535 0.0377
-6.750 -0.1578 0.01667 0.01156 -0.1405 0.9484 0.0386
-6.500 -0.1244 0.01538 0.01019 -0.1422 0.9452 0.0399
-6.250 -0.0896 0.01458 0.00932 -0.1439 0.9424 0.0410
-6.000 -0.0633 0.01388 0.00852 -0.1436 0.9343 0.0419
-5.750 -0.0311 0.01315 0.00769 -0.1445 0.9293 0.0430
-5.500 -0.0021 0.01256 0.00700 -0.1447 0.9221 0.0439
-5.250 0.0281 0.01209 0.00644 -0.1451 0.9150 0.0451
-5.000 0.0573 0.01173 0.00599 -0.1452 0.9070 0.0459
-4.750 0.0862 0.01087 0.00502 -0.1455 0.8990 0.0472
-4.500 0.1138 0.01031 0.00442 -0.1454 0.8896 0.0488
-4.250 0.1434 0.00992 0.00396 -0.1456 0.8815 0.0507
-4.000 0.1708 0.00963 0.00361 -0.1454 0.8714 0.0527
-3.750 0.1992 0.00940 0.00330 -0.1454 0.8624 0.0550
-3.500 0.2275 0.00910 0.00292 -0.1453 0.8530 0.0583
-3.250 0.2551 0.00885 0.00265 -0.1451 0.8434 0.0638
-3.000 0.2834 0.00862 0.00245 -0.1451 0.8347 0.0788
-2.750 0.3108 0.00851 0.00241 -0.1448 0.8248 0.1109
-2.500 0.3386 0.00847 0.00234 -0.1446 0.8159 0.1253
-2.250 0.3663 0.00846 0.00228 -0.1444 0.8068 0.1348
-2.000 0.3938 0.00837 0.00219 -0.1442 0.7975 0.1433
-1.500 0.4488 0.00827 0.00205 -0.1438 0.7793 0.1600
-1.250 0.4764 0.00822 0.00199 -0.1436 0.7705 0.1719
-1.000 0.5037 0.00813 0.00195 -0.1433 0.7611 0.1950
-0.750 0.5309 0.00798 0.00196 -0.1432 0.7520 0.2504
-0.500 0.5581 0.00792 0.00198 -0.1430 0.7426 0.3030
-0.250 0.5850 0.00786 0.00200 -0.1426 0.7312 0.3422
0.000 0.6119 0.00784 0.00202 -0.1423 0.7201 0.3734
0.250 0.6387 0.00785 0.00205 -0.1419 0.7091 0.4017
0.500 0.6654 0.00785 0.00208 -0.1415 0.6974 0.4302
0.750 0.6922 0.00785 0.00212 -0.1412 0.6860 0.4591
1.000 0.7188 0.00787 0.00217 -0.1408 0.6746 0.4890
1.250 0.7451 0.00787 0.00221 -0.1403 0.6625 0.5240
1.500 0.7710 0.00780 0.00230 -0.1398 0.6498 0.5849
1.750 0.7960 0.00765 0.00241 -0.1391 0.6378 0.6989
2.000 0.8209 0.00718 0.00245 -0.1381 0.6270 1.0000
2.250 0.8475 0.00732 0.00251 -0.1377 0.6161 1.0000
2.500 0.8741 0.00745 0.00259 -0.1373 0.6049 1.0000
2.750 0.9009 0.00758 0.00268 -0.1370 0.5946 1.0000
3.000 0.9272 0.00774 0.00278 -0.1366 0.5844 1.0000
3.250 0.9535 0.00789 0.00289 -0.1362 0.5731 1.0000
3.500 0.9798 0.00804 0.00301 -0.1357 0.5619 1.0000
3.750 1.0059 0.00820 0.00314 -0.1353 0.5515 1.0000
4.000 1.0317 0.00839 0.00327 -0.1348 0.5407 1.0000
4.250 1.0578 0.00854 0.00343 -0.1343 0.5292 1.0000
4.500 1.0833 0.00872 0.00358 -0.1338 0.5169 1.0000
4.750 1.1086 0.00892 0.00375 -0.1332 0.5044 1.0000
5.000 1.1337 0.00912 0.00394 -0.1326 0.4913 1.0000
5.250 1.1583 0.00934 0.00413 -0.1319 0.4752 1.0000
5.500 1.1817 0.00961 0.00433 -0.1310 0.4508 1.0000
5.750 1.2033 0.00999 0.00457 -0.1298 0.4178 1.0000
6.000 1.2225 0.01054 0.00490 -0.1282 0.3707 1.0000
6.250 1.2394 0.01130 0.00534 -0.1264 0.3144 1.0000
6.500 1.2576 0.01199 0.00581 -0.1248 0.2757 1.0000
6.750 1.2774 0.01256 0.00625 -0.1234 0.2513 1.0000
7.250 1.3186 0.01354 0.00709 -0.1210 0.2190 1.0000
7.750 1.3595 0.01446 0.00794 -0.1185 0.1895 1.0000
8.000 1.3795 0.01492 0.00836 -0.1172 0.1729 1.0000
8.250 1.3975 0.01550 0.00884 -0.1156 0.1490 1.0000
8.500 1.4088 0.01646 0.00953 -0.1130 0.1078 1.0000
8.750 1.4125 0.01774 0.01052 -0.1091 0.0688 1.0000
9.000 1.4190 0.01885 0.01149 -0.1057 0.0483 1.0000
9.250 1.4284 0.01980 0.01241 -0.1028 0.0378 1.0000
9.500 1.4370 0.02081 0.01340 -0.0999 0.0318 1.0000
9.750 1.4487 0.02164 0.01428 -0.0975 0.0287 1.0000
10.000 1.4551 0.02284 0.01550 -0.0945 0.0260 1.0000
10.250 1.4675 0.02365 0.01638 -0.0924 0.0245 1.0000
10.500 1.4775 0.02465 0.01744 -0.0902 0.0230 1.0000
10.750 1.4835 0.02595 0.01880 -0.0876 0.0218 1.0000
11.000 1.4858 0.02759 0.02052 -0.0848 0.0208 1.0000
11.250 1.4940 0.02885 0.02187 -0.0828 0.0202 1.0000
11.500 1.5010 0.03026 0.02336 -0.0808 0.0195 1.0000
11.750 1.5069 0.03182 0.02500 -0.0789 0.0189 1.0000
12.000 1.5118 0.03352 0.02678 -0.0771 0.0182 1.0000
12.250 1.5148 0.03546 0.02879 -0.0754 0.0177 1.0000
12.500 1.5117 0.03809 0.03149 -0.0735 0.0172 1.0000
12.750 1.5079 0.04092 0.03444 -0.0719 0.0167 1.0000
13.000 1.5133 0.04293 0.03655 -0.0708 0.0164 1.0000
13.250 1.5174 0.04514 0.03886 -0.0699 0.0160 1.0000
13.500 1.5195 0.04763 0.04146 -0.0690 0.0156 1.0000
13.750 1.5211 0.05026 0.04419 -0.0683 0.0152 1.0000
14.000 1.5224 0.05304 0.04707 -0.0678 0.0149 1.0000
14.250 1.5229 0.05596 0.05009 -0.0674 0.0146 1.0000
14.500 1.5233 0.05901 0.05322 -0.0672 0.0143 1.0000
14.750 1.5229 0.06225 0.05654 -0.0672 0.0141 1.0000
15.000 1.5214 0.06570 0.06007 -0.0672 0.0138 1.0000
15.250 1.5182 0.06945 0.06390 -0.0671 0.0135 1.0000
15.500 1.5154 0.07326 0.06783 -0.0669 0.0133 1.0000
15.750 1.5154 0.07683 0.07153 -0.0674 0.0131 1.0000
16.000 1.5144 0.08060 0.07545 -0.0682 0.0130 1.0000
16.250 1.5127 0.08458 0.07958 -0.0691 0.0128 1.0000
16.500 1.5103 0.08875 0.08389 -0.0702 0.0126 1.0000
16.750 1.5073 0.09312 0.08841 -0.0715 0.0124 1.0000
17.000 1.5035 0.09768 0.09311 -0.0730 0.0122 1.0000
17.250 1.4993 0.10238 0.09795 -0.0748 0.0120 1.0000
17.500 1.4947 0.10725 0.10294 -0.0767 0.0118 1.0000
17.750 1.4899 0.11224 0.10806 -0.0788 0.0117 1.0000
18.000 1.4841 0.11749 0.11345 -0.0812 0.0116 1.0000
18.250 1.4774 0.12298 0.11908 -0.0839 0.0114 1.0000
18.500 1.4704 0.12864 0.12488 -0.0869 0.0113 1.0000
18.750 1.4630 0.13448 0.13086 -0.0901 0.0113 1.0000
19.000 1.4551 0.14052 0.13703 -0.0936 0.0112 1.0000
19.250 1.4469 0.14675 0.14339 -0.0974 0.0111 1.0000
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