GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 408 AIRFOIL (goe408-il) Reynolds number: 100,000 Max Cl/Cd: 59.16 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe408-il-100000-n5.txt Download as CSV file: xf-goe408-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 408 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3857 0.10426 0.09943 -0.0259 1.0000 0.0382
-8.000 -0.3908 0.10177 0.09700 -0.0260 1.0000 0.0382
-7.750 -0.3943 0.09909 0.09439 -0.0263 1.0000 0.0383
-7.500 -0.3939 0.09578 0.09113 -0.0273 1.0000 0.0383
-7.250 -0.3829 0.09151 0.08689 -0.0218 1.0000 0.0402
-7.000 -0.3836 0.08857 0.08400 -0.0218 1.0000 0.0405
-6.750 -0.3834 0.08555 0.08104 -0.0221 1.0000 0.0406
-6.500 -0.3830 0.08229 0.07783 -0.0230 1.0000 0.0402
-6.000 -0.3790 0.07549 0.07106 -0.0233 1.0000 0.0354
-5.750 -0.3763 0.07207 0.06764 -0.0236 1.0000 0.0340
-5.500 -0.3727 0.06791 0.06344 -0.0246 1.0000 0.0322
-5.250 -0.3560 0.06491 0.06040 -0.0265 0.9975 0.0344
-5.000 -0.3207 0.05948 0.05473 -0.0336 0.9904 0.0369
-4.750 -0.2901 0.05449 0.04952 -0.0382 0.9831 0.0368
-4.500 -0.2572 0.04868 0.04327 -0.0424 0.9745 0.0380
-4.250 -0.2317 0.04706 0.04166 -0.0441 0.9673 0.0426
-4.000 -0.2030 0.04303 0.03729 -0.0460 0.9577 0.0445
-3.750 -0.1758 0.03854 0.03217 -0.0464 0.9465 0.0482
-3.500 -0.1528 0.03727 0.03098 -0.0470 0.9358 0.0525
-3.250 -0.1260 0.03428 0.02759 -0.0471 0.9255 0.0544
-3.000 -0.0937 0.03135 0.02389 -0.0474 0.9176 0.0600
-2.750 -0.0684 0.02924 0.02162 -0.0473 0.9067 0.0615
-2.500 -0.0391 0.02739 0.01949 -0.0475 0.8975 0.0629
-2.250 -0.0066 0.02602 0.01786 -0.0483 0.8893 0.0674
-2.000 0.0231 0.02442 0.01588 -0.0482 0.8788 0.0679
-1.750 0.0588 0.02288 0.01397 -0.0493 0.8714 0.0681
-1.500 0.0915 0.02166 0.01245 -0.0498 0.8607 0.0687
-1.250 0.1265 0.02058 0.01108 -0.0509 0.8506 0.0698
-1.000 0.1675 0.01965 0.00987 -0.0532 0.8423 0.0733
-0.750 0.2037 0.01878 0.00891 -0.0548 0.8303 0.0746
-0.500 0.2432 0.01801 0.00803 -0.0570 0.8186 0.0755
-0.250 0.2851 0.01734 0.00728 -0.0598 0.8068 0.0768
0.000 0.3269 0.01676 0.00664 -0.0626 0.7945 0.0788
0.250 0.3670 0.01629 0.00612 -0.0650 0.7814 0.0812
0.500 0.4041 0.01600 0.00573 -0.0668 0.7675 0.0850
0.750 0.4415 0.01575 0.00547 -0.0688 0.7531 0.0914
1.000 0.4799 0.01561 0.00522 -0.0709 0.7387 0.0969
1.250 0.5168 0.01548 0.00504 -0.0728 0.7244 0.1041
1.500 0.5521 0.01540 0.00492 -0.0743 0.7099 0.1188
2.000 0.7293 0.01394 0.00517 -0.1019 0.6750 1.0000
2.250 0.7547 0.01414 0.00529 -0.1013 0.6599 1.0000
2.500 0.7792 0.01435 0.00542 -0.1004 0.6448 1.0000
2.750 0.8032 0.01456 0.00557 -0.0995 0.6296 1.0000
3.000 0.8264 0.01477 0.00576 -0.0984 0.6136 1.0000
3.250 0.8481 0.01499 0.00592 -0.0969 0.5947 1.0000
3.500 0.8691 0.01521 0.00606 -0.0953 0.5734 1.0000
3.750 0.8892 0.01544 0.00622 -0.0935 0.5508 1.0000
4.000 0.9099 0.01569 0.00642 -0.0919 0.5302 1.0000
4.250 0.9315 0.01596 0.00666 -0.0905 0.5136 1.0000
4.500 0.9531 0.01624 0.00693 -0.0891 0.4976 1.0000
4.750 0.9745 0.01654 0.00722 -0.0877 0.4821 1.0000
5.000 0.9956 0.01685 0.00757 -0.0863 0.4667 1.0000
5.250 1.0163 0.01718 0.00791 -0.0848 0.4507 1.0000
5.500 1.0367 0.01753 0.00829 -0.0832 0.4345 1.0000
5.750 1.0566 0.01790 0.00870 -0.0816 0.4177 1.0000
6.000 1.0756 0.01829 0.00915 -0.0798 0.3987 1.0000
6.250 1.0937 0.01870 0.00958 -0.0778 0.3784 1.0000
6.500 1.1108 0.01914 0.01004 -0.0757 0.3552 1.0000
6.750 1.1273 0.01962 0.01052 -0.0735 0.3320 1.0000
7.000 1.1441 0.02012 0.01109 -0.0714 0.3087 1.0000
7.250 1.1599 0.02068 0.01166 -0.0692 0.2876 1.0000
7.500 1.1758 0.02127 0.01229 -0.0670 0.2664 1.0000
7.750 1.1889 0.02198 0.01296 -0.0644 0.2427 1.0000
8.000 1.2017 0.02275 0.01369 -0.0618 0.2180 1.0000
8.250 1.2126 0.02362 0.01450 -0.0589 0.1923 1.0000
8.500 1.2214 0.02462 0.01539 -0.0559 0.1638 1.0000
8.750 1.2298 0.02567 0.01640 -0.0528 0.1356 1.0000
9.000 1.2367 0.02674 0.01740 -0.0495 0.1052 1.0000
9.250 1.2378 0.02815 0.01856 -0.0454 0.0690 1.0000
9.500 1.2344 0.02991 0.02014 -0.0408 0.0537 1.0000
9.750 1.2340 0.03152 0.02185 -0.0366 0.0452 1.0000
10.000 1.2315 0.03333 0.02374 -0.0326 0.0394 1.0000
10.250 1.2318 0.03500 0.02557 -0.0290 0.0352 1.0000
10.500 1.2320 0.03674 0.02742 -0.0259 0.0314 1.0000
10.750 1.2287 0.03880 0.02957 -0.0229 0.0296 1.0000
11.000 1.2293 0.04072 0.03170 -0.0204 0.0274 1.0000
11.250 1.2284 0.04286 0.03400 -0.0182 0.0258 1.0000
11.500 1.2266 0.04521 0.03650 -0.0163 0.0249 1.0000
11.750 1.2237 0.04783 0.03928 -0.0148 0.0237 1.0000
12.000 1.2197 0.05068 0.04224 -0.0136 0.0227 1.0000
12.250 1.2150 0.05378 0.04539 -0.0124 0.0220 1.0000
12.500 1.2153 0.05655 0.04839 -0.0114 0.0210 1.0000
12.750 1.2149 0.05942 0.05148 -0.0108 0.0200 1.0000
13.000 1.2133 0.06255 0.05479 -0.0103 0.0192 1.0000
13.250 1.2119 0.06574 0.05817 -0.0098 0.0188 1.0000
13.500 1.2097 0.06914 0.06174 -0.0095 0.0184 1.0000
13.750 1.2054 0.07294 0.06574 -0.0094 0.0180 1.0000
14.000 1.1987 0.07710 0.07010 -0.0098 0.0175 1.0000
14.250 1.1918 0.08141 0.07461 -0.0104 0.0173 1.0000
14.500 1.1829 0.08616 0.07957 -0.0115 0.0171 1.0000
14.750 1.1722 0.09136 0.08498 -0.0130 0.0171 1.0000
15.000 1.1598 0.09706 0.09089 -0.0151 0.0171 1.0000
15.250 1.1454 0.10332 0.09734 -0.0178 0.0168 1.0000
15.500 1.1308 0.10995 0.10418 -0.0209 0.0169 1.0000
15.750 1.1129 0.11772 0.11216 -0.0248 0.0172 1.0000
16.000 1.0941 0.12609 0.12072 -0.0295 0.0173 1.0000
16.250 1.0711 0.13612 0.13091 -0.0353 0.0173 1.0000
16.500 1.0459 0.14767 0.14263 -0.0420 0.0179 1.0000
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Polar data table (+)
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