GOE 479 AIRFOIL (goe479-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 479 AIRFOIL (goe479-il) Reynolds number: 100,000 Max Cl/Cd: 55.32 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe479-il-100000-n5.txt Download as CSV file: xf-goe479-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 479 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3593 0.09245 0.08723 -0.0427 1.0000 0.0534
-9.000 -0.3671 0.08938 0.08423 -0.0424 1.0000 0.0530
-8.750 -0.3778 0.08645 0.08138 -0.0417 1.0000 0.0525
-8.500 -0.3930 0.08367 0.07869 -0.0405 1.0000 0.0521
-8.250 -0.4141 0.08117 0.07630 -0.0387 1.0000 0.0517
-8.000 -0.4332 0.07783 0.07304 -0.0387 0.9988 0.0513
-7.750 -0.4211 0.06910 0.06422 -0.0506 0.9884 0.0513
-7.500 -0.4109 0.05990 0.05479 -0.0612 0.9778 0.0523
-7.250 -0.4030 0.05040 0.04484 -0.0691 0.9673 0.0525
-7.000 -0.3877 0.04291 0.03671 -0.0742 0.9593 0.0528
-6.750 -0.3731 0.03798 0.03113 -0.0757 0.9493 0.0539
-6.500 -0.3485 0.03402 0.02641 -0.0777 0.9429 0.0555
-6.250 -0.3241 0.03226 0.02450 -0.0780 0.9346 0.0565
-6.000 -0.2919 0.03033 0.02228 -0.0798 0.9299 0.0575
-5.750 -0.2671 0.02881 0.02053 -0.0798 0.9214 0.0586
-5.500 -0.2351 0.02732 0.01876 -0.0810 0.9157 0.0604
-5.250 -0.2018 0.02590 0.01698 -0.0822 0.9105 0.0628
-5.000 -0.1749 0.02471 0.01543 -0.0820 0.9016 0.0644
-4.750 -0.1403 0.02346 0.01414 -0.0835 0.8969 0.0659
-4.500 -0.1141 0.02264 0.01327 -0.0832 0.8875 0.0677
-4.250 -0.0802 0.02181 0.01234 -0.0842 0.8814 0.0708
-4.000 -0.0520 0.02110 0.01147 -0.0841 0.8718 0.0741
-3.750 -0.0184 0.02021 0.01057 -0.0850 0.8644 0.0772
-3.500 0.0084 0.01959 0.00994 -0.0846 0.8530 0.0806
-3.250 0.0413 0.01895 0.00920 -0.0851 0.8448 0.0861
-3.000 0.0680 0.01842 0.00872 -0.0848 0.8339 0.0921
-2.750 0.0965 0.01796 0.00821 -0.0846 0.8244 0.0999
-2.500 0.1263 0.01747 0.00776 -0.0848 0.8156 0.1117
-2.250 0.1528 0.01708 0.00741 -0.0843 0.8051 0.1281
-2.000 0.1838 0.01659 0.00703 -0.0847 0.7973 0.1564
-1.750 0.2090 0.01627 0.00682 -0.0841 0.7861 0.1930
-1.500 0.2377 0.01590 0.00660 -0.0841 0.7771 0.2419
-1.250 0.2653 0.01554 0.00642 -0.0839 0.7674 0.3026
-1.000 0.2923 0.01504 0.00630 -0.0837 0.7576 0.4042
-0.750 0.3152 0.01415 0.00630 -0.0822 0.7490 0.6509
-0.500 0.4104 0.01354 0.00620 -0.0944 0.7402 0.9826
-0.250 0.4492 0.01356 0.00600 -0.0964 0.7310 1.0000
0.000 0.4718 0.01368 0.00598 -0.0953 0.7196 1.0000
0.250 0.4968 0.01377 0.00592 -0.0946 0.7098 1.0000
0.500 0.5213 0.01388 0.00589 -0.0937 0.6996 1.0000
0.750 0.5448 0.01403 0.00592 -0.0927 0.6890 1.0000
1.000 0.5707 0.01414 0.00589 -0.0921 0.6799 1.0000
1.250 0.5932 0.01431 0.00599 -0.0909 0.6686 1.0000
1.500 0.6176 0.01447 0.00605 -0.0901 0.6584 1.0000
1.750 0.6419 0.01463 0.00611 -0.0892 0.6481 1.0000
2.000 0.6650 0.01482 0.00625 -0.0881 0.6370 1.0000
2.250 0.6895 0.01498 0.00632 -0.0873 0.6264 1.0000
2.500 0.7126 0.01516 0.00642 -0.0862 0.6140 1.0000
2.750 0.7350 0.01534 0.00656 -0.0849 0.6005 1.0000
3.000 0.7577 0.01552 0.00668 -0.0837 0.5873 1.0000
3.250 0.7811 0.01571 0.00680 -0.0827 0.5753 1.0000
3.500 0.8041 0.01591 0.00697 -0.0816 0.5633 1.0000
3.750 0.8265 0.01613 0.00718 -0.0805 0.5510 1.0000
4.000 0.8495 0.01635 0.00738 -0.0794 0.5395 1.0000
4.250 0.8727 0.01657 0.00755 -0.0784 0.5282 1.0000
4.500 0.8949 0.01681 0.00781 -0.0772 0.5160 1.0000
4.750 0.9172 0.01707 0.00807 -0.0761 0.5041 1.0000
5.000 0.9397 0.01733 0.00831 -0.0750 0.4926 1.0000
5.250 0.9621 0.01760 0.00856 -0.0739 0.4812 1.0000
5.500 0.9837 0.01791 0.00889 -0.0727 0.4690 1.0000
5.750 1.0054 0.01823 0.00922 -0.0715 0.4572 1.0000
6.000 1.0266 0.01856 0.00952 -0.0702 0.4448 1.0000
6.250 1.0466 0.01892 0.00983 -0.0687 0.4301 1.0000
6.500 1.0650 0.01929 0.01018 -0.0670 0.4135 1.0000
6.750 1.0822 0.01969 0.01057 -0.0651 0.3952 1.0000
7.000 1.0987 0.02010 0.01098 -0.0631 0.3764 1.0000
7.250 1.1152 0.02053 0.01141 -0.0612 0.3589 1.0000
7.500 1.1312 0.02099 0.01189 -0.0592 0.3415 1.0000
7.750 1.1461 0.02148 0.01237 -0.0571 0.3236 1.0000
8.000 1.1600 0.02202 0.01288 -0.0549 0.3054 1.0000
8.250 1.1731 0.02260 0.01344 -0.0526 0.2887 1.0000
8.500 1.1837 0.02322 0.01405 -0.0499 0.2722 1.0000
8.750 1.1927 0.02393 0.01471 -0.0471 0.2555 1.0000
9.000 1.2011 0.02472 0.01547 -0.0443 0.2380 1.0000
9.250 1.2080 0.02564 0.01634 -0.0415 0.2180 1.0000
9.500 1.2145 0.02663 0.01730 -0.0388 0.1989 1.0000
9.750 1.2193 0.02779 0.01842 -0.0361 0.1781 1.0000
10.000 1.2231 0.02909 0.01966 -0.0335 0.1521 1.0000
10.250 1.2229 0.03073 0.02117 -0.0308 0.1240 1.0000
10.500 1.2205 0.03265 0.02294 -0.0282 0.1008 1.0000
10.750 1.2187 0.03467 0.02487 -0.0259 0.0877 1.0000
11.000 1.2185 0.03667 0.02687 -0.0240 0.0806 1.0000
11.250 1.2168 0.03891 0.02911 -0.0223 0.0758 1.0000
11.500 1.2174 0.04105 0.03135 -0.0210 0.0725 1.0000
11.750 1.2171 0.04337 0.03376 -0.0198 0.0698 1.0000
12.000 1.2152 0.04596 0.03641 -0.0189 0.0676 1.0000
12.250 1.2121 0.04874 0.03926 -0.0181 0.0660 1.0000
12.500 1.2115 0.05140 0.04201 -0.0176 0.0644 1.0000
12.750 1.2115 0.05405 0.04479 -0.0171 0.0630 1.0000
13.000 1.2117 0.05674 0.04760 -0.0167 0.0619 1.0000
13.250 1.2122 0.05946 0.05043 -0.0165 0.0608 1.0000
13.500 1.2127 0.06221 0.05327 -0.0163 0.0595 1.0000
13.750 1.2139 0.06492 0.05604 -0.0161 0.0584 1.0000
14.000 1.2164 0.06748 0.05862 -0.0159 0.0573 1.0000
14.250 1.2215 0.06971 0.06088 -0.0155 0.0561 1.0000
14.500 1.2269 0.07208 0.06340 -0.0153 0.0550 1.0000
14.750 1.2332 0.07434 0.06579 -0.0151 0.0540 1.0000
15.000 1.2398 0.07659 0.06815 -0.0149 0.0530 1.0000
15.250 1.2460 0.07893 0.07060 -0.0148 0.0519 1.0000
15.500 1.2523 0.08126 0.07300 -0.0147 0.0508 1.0000
15.750 1.2597 0.08343 0.07521 -0.0146 0.0496 1.0000
16.000 1.2740 0.08469 0.07643 -0.0138 0.0484 1.0000
16.250 1.2774 0.08763 0.07954 -0.0141 0.0477 1.0000
16.500 1.2754 0.09138 0.08351 -0.0150 0.0470 1.0000
16.750 1.2721 0.09537 0.08773 -0.0162 0.0463 1.0000
17.000 1.2681 0.09954 0.09211 -0.0176 0.0455 1.0000
17.250 1.2623 0.10407 0.09684 -0.0193 0.0448 1.0000
17.500 1.2560 0.10878 0.10174 -0.0213 0.0441 1.0000
17.750 1.2491 0.11369 0.10683 -0.0235 0.0434 1.0000
18.000 1.2417 0.11877 0.11207 -0.0260 0.0429 1.0000
18.250 1.2336 0.12406 0.11753 -0.0287 0.0424 1.0000
18.500 1.2283 0.12888 0.12246 -0.0311 0.0418 1.0000
18.750 1.2333 0.13164 0.12525 -0.0321 0.0409 1.0000
19.000 1.2140 0.13955 0.13336 -0.0370 0.0407 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 479 AIRFOIL (goe479-il)