GOE 490 AIRFOIL (goe490-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 490 AIRFOIL (goe490-il) Reynolds number: 100,000 Max Cl/Cd: 54.15 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe490-il-100000-n5.txt Download as CSV file: xf-goe490-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 490 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3694 0.09241 0.08755 -0.0317 1.0000 0.0345
-8.250 -0.3741 0.08927 0.08449 -0.0318 1.0000 0.0342
-8.000 -0.3819 0.08628 0.08160 -0.0316 1.0000 0.0343
-7.750 -0.3935 0.08357 0.07898 -0.0309 1.0000 0.0345
-7.500 -0.4024 0.08048 0.07598 -0.0309 1.0000 0.0347
-7.250 -0.4106 0.07687 0.07244 -0.0316 1.0000 0.0354
-7.000 -0.4166 0.07330 0.06892 -0.0321 1.0000 0.0354
-6.750 -0.4226 0.06890 0.06452 -0.0333 1.0000 0.0361
-6.500 -0.4255 0.06437 0.05997 -0.0344 1.0000 0.0364
-6.250 -0.4263 0.05925 0.05476 -0.0355 1.0000 0.0367
-6.000 -0.4026 0.04760 0.04263 -0.0448 0.9935 0.0374
-5.750 -0.3763 0.04375 0.03856 -0.0485 0.9876 0.0402
-5.500 -0.3487 0.04041 0.03495 -0.0512 0.9815 0.0426
-5.250 -0.3214 0.03393 0.02771 -0.0546 0.9759 0.0452
-5.000 -0.2961 0.02961 0.02248 -0.0557 0.9689 0.0489
-4.750 -0.2648 0.02666 0.01890 -0.0572 0.9645 0.0507
-4.500 -0.2376 0.02551 0.01761 -0.0577 0.9571 0.0535
-4.250 -0.2036 0.02427 0.01606 -0.0592 0.9525 0.0572
-4.000 -0.1749 0.02280 0.01423 -0.0593 0.9451 0.0592
-3.750 -0.1394 0.02151 0.01259 -0.0607 0.9396 0.0614
-3.500 -0.1074 0.02044 0.01134 -0.0615 0.9313 0.0636
-3.250 -0.0690 0.01963 0.01048 -0.0635 0.9244 0.0681
-3.000 -0.0358 0.01895 0.00966 -0.0643 0.9145 0.0743
-2.750 0.0037 0.01814 0.00881 -0.0663 0.9086 0.0804
-2.500 0.0334 0.01757 0.00818 -0.0664 0.8991 0.0897
-2.250 0.0713 0.01701 0.00768 -0.0682 0.8937 0.1077
-2.000 0.1004 0.01668 0.00731 -0.0683 0.8835 0.1308
-1.750 0.1344 0.01633 0.00695 -0.0693 0.8759 0.1515
-1.500 0.1663 0.01604 0.00674 -0.0700 0.8666 0.1796
-1.250 0.1967 0.01586 0.00667 -0.0704 0.8561 0.2120
-1.000 0.2301 0.01563 0.00644 -0.0712 0.8467 0.2362
-0.750 0.2627 0.01537 0.00618 -0.0719 0.8362 0.2591
-0.500 0.2932 0.01514 0.00594 -0.0721 0.8239 0.2844
-0.250 0.3246 0.01486 0.00569 -0.0726 0.8117 0.3166
0.000 0.3549 0.01449 0.00544 -0.0729 0.7989 0.3601
0.250 0.4564 0.01280 0.00526 -0.0878 0.7900 1.0000
0.500 0.4839 0.01284 0.00513 -0.0874 0.7736 1.0000
0.750 0.5109 0.01288 0.00503 -0.0869 0.7565 1.0000
1.000 0.5375 0.01294 0.00496 -0.0863 0.7387 1.0000
1.250 0.5639 0.01302 0.00488 -0.0857 0.7196 1.0000
1.500 0.5889 0.01312 0.00484 -0.0847 0.6984 1.0000
1.750 0.6132 0.01325 0.00483 -0.0836 0.6756 1.0000
2.000 0.6369 0.01340 0.00485 -0.0825 0.6532 1.0000
2.250 0.6603 0.01358 0.00490 -0.0813 0.6314 1.0000
2.500 0.6836 0.01377 0.00499 -0.0802 0.6110 1.0000
2.750 0.7063 0.01398 0.00511 -0.0790 0.5902 1.0000
3.000 0.7290 0.01421 0.00524 -0.0777 0.5701 1.0000
3.250 0.7514 0.01445 0.00541 -0.0765 0.5505 1.0000
3.500 0.7735 0.01471 0.00559 -0.0752 0.5306 1.0000
3.750 0.7952 0.01499 0.00577 -0.0739 0.5107 1.0000
4.000 0.8164 0.01530 0.00599 -0.0724 0.4896 1.0000
4.250 0.8375 0.01562 0.00624 -0.0710 0.4696 1.0000
4.500 0.8583 0.01598 0.00649 -0.0696 0.4508 1.0000
4.750 0.8795 0.01633 0.00680 -0.0682 0.4341 1.0000
5.000 0.9007 0.01669 0.00716 -0.0669 0.4181 1.0000
5.250 0.9219 0.01705 0.00752 -0.0656 0.4029 1.0000
5.500 0.9429 0.01742 0.00790 -0.0643 0.3876 1.0000
5.750 0.9638 0.01780 0.00831 -0.0630 0.3724 1.0000
6.000 0.9844 0.01818 0.00876 -0.0616 0.3572 1.0000
6.250 1.0048 0.01857 0.00921 -0.0602 0.3416 1.0000
6.500 1.0243 0.01898 0.00965 -0.0587 0.3241 1.0000
6.750 1.0409 0.01945 0.01005 -0.0568 0.2976 1.0000
7.000 1.0563 0.02001 0.01048 -0.0547 0.2686 1.0000
7.250 1.0733 0.02058 0.01105 -0.0529 0.2488 1.0000
7.500 1.0898 0.02119 0.01163 -0.0511 0.2308 1.0000
7.750 1.1060 0.02184 0.01226 -0.0493 0.2131 1.0000
8.000 1.1226 0.02247 0.01293 -0.0475 0.1962 1.0000
8.250 1.1370 0.02321 0.01362 -0.0455 0.1724 1.0000
8.500 1.1513 0.02399 0.01437 -0.0435 0.1476 1.0000
8.750 1.1630 0.02496 0.01523 -0.0411 0.1195 1.0000
9.000 1.1614 0.02687 0.01662 -0.0373 0.0512 1.0000
9.250 1.1628 0.02849 0.01813 -0.0336 0.0314 1.0000
9.500 1.1676 0.02987 0.01953 -0.0305 0.0264 1.0000
9.750 1.1730 0.03125 0.02101 -0.0277 0.0238 1.0000
10.000 1.1768 0.03275 0.02264 -0.0248 0.0221 1.0000
10.250 1.1800 0.03431 0.02436 -0.0222 0.0213 1.0000
10.500 1.1804 0.03611 0.02635 -0.0196 0.0206 1.0000
11.000 1.1767 0.04027 0.03087 -0.0151 0.0198 1.0000
11.250 1.1738 0.04262 0.03343 -0.0134 0.0194 1.0000
11.500 1.1701 0.04520 0.03620 -0.0121 0.0191 1.0000
11.750 1.1647 0.04815 0.03933 -0.0112 0.0187 1.0000
12.000 1.1588 0.05136 0.04272 -0.0107 0.0184 1.0000
12.250 1.1526 0.05482 0.04635 -0.0107 0.0179 1.0000
12.500 1.1452 0.05863 0.05039 -0.0110 0.0174 1.0000
12.750 1.1389 0.06248 0.05438 -0.0115 0.0172 1.0000
13.000 1.1326 0.06647 0.05852 -0.0123 0.0169 1.0000
13.250 1.1273 0.07043 0.06262 -0.0130 0.0167 1.0000
13.500 1.1227 0.07437 0.06669 -0.0138 0.0164 1.0000
13.750 1.1200 0.07804 0.07049 -0.0144 0.0162 1.0000
14.000 1.1187 0.08159 0.07415 -0.0149 0.0161 1.0000
14.250 1.1182 0.08506 0.07774 -0.0154 0.0159 1.0000
14.500 1.1183 0.08850 0.08132 -0.0158 0.0157 1.0000
14.750 1.1179 0.09214 0.08509 -0.0165 0.0155 1.0000
15.000 1.1168 0.09602 0.08913 -0.0174 0.0155 1.0000
15.250 1.1141 0.10031 0.09357 -0.0186 0.0153 1.0000
15.500 1.1101 0.10495 0.09838 -0.0203 0.0153 1.0000
15.750 1.1044 0.11005 0.10365 -0.0224 0.0153 1.0000
16.000 1.0971 0.11562 0.10941 -0.0251 0.0153 1.0000
16.250 1.0884 0.12169 0.11566 -0.0282 0.0153 1.0000
16.500 1.0779 0.12835 0.12250 -0.0318 0.0153 1.0000
16.750 1.0665 0.13549 0.12981 -0.0359 0.0153 1.0000
17.000 1.0540 0.14328 0.13778 -0.0406 0.0154 1.0000
17.250 1.0405 0.15179 0.14645 -0.0457 0.0157 1.0000
17.500 1.0234 0.16191 0.15673 -0.0519 0.0160 1.0000
17.750 1.0010 0.17466 0.16961 -0.0594 0.0164 1.0000
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