GOE 633 AIRFOIL (goe633-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 633 AIRFOIL (goe633-il) Reynolds number: 100,000 Max Cl/Cd: 48.88 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe633-il-100000-n5.txt Download as CSV file: xf-goe633-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 633 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3583 0.09316 0.08806 -0.0380 1.0000 0.0525
-10.000 -0.3606 0.08879 0.08376 -0.0400 1.0000 0.0523
-9.750 -0.3652 0.08418 0.07922 -0.0423 1.0000 0.0519
-9.500 -0.3704 0.07751 0.07258 -0.0479 0.9412 0.0514
-9.250 -0.4848 0.04930 0.04368 -0.0717 0.8802 0.0490
-9.000 -0.5060 0.04343 0.03717 -0.0716 0.8588 0.0489
-8.750 -0.5071 0.04009 0.03335 -0.0701 0.8443 0.0490
-8.500 -0.5010 0.03752 0.03035 -0.0685 0.8330 0.0493
-8.250 -0.4908 0.03539 0.02786 -0.0670 0.8222 0.0496
-8.000 -0.4769 0.03363 0.02575 -0.0655 0.8134 0.0502
-7.750 -0.4612 0.03206 0.02386 -0.0641 0.8042 0.0510
-7.500 -0.4435 0.03064 0.02209 -0.0628 0.7966 0.0519
-7.250 -0.4244 0.02934 0.02048 -0.0616 0.7884 0.0527
-7.000 -0.4036 0.02821 0.01907 -0.0604 0.7819 0.0532
-6.750 -0.3817 0.02713 0.01793 -0.0596 0.7741 0.0538
-6.500 -0.3593 0.02622 0.01692 -0.0587 0.7673 0.0544
-6.250 -0.3366 0.02541 0.01602 -0.0578 0.7609 0.0552
-6.000 -0.3137 0.02467 0.01520 -0.0570 0.7540 0.0561
-5.750 -0.2905 0.02399 0.01438 -0.0560 0.7482 0.0572
-5.500 -0.2673 0.02337 0.01366 -0.0551 0.7417 0.0584
-5.250 -0.2437 0.02281 0.01298 -0.0542 0.7352 0.0601
-5.000 -0.2203 0.02225 0.01236 -0.0533 0.7300 0.0622
-4.750 -0.1966 0.02178 0.01186 -0.0525 0.7239 0.0647
-4.500 -0.1725 0.02133 0.01133 -0.0517 0.7176 0.0675
-4.250 -0.1480 0.02088 0.01082 -0.0509 0.7125 0.0705
-4.000 -0.1233 0.02048 0.01042 -0.0502 0.7066 0.0753
-3.750 -0.0984 0.02007 0.01005 -0.0495 0.7004 0.0839
-3.500 -0.0728 0.01966 0.00965 -0.0489 0.6952 0.1028
-3.250 -0.0476 0.01932 0.00943 -0.0483 0.6896 0.1313
-3.000 -0.0222 0.01921 0.00943 -0.0477 0.6829 0.1591
-2.750 0.0041 0.01918 0.00933 -0.0470 0.6766 0.1827
-2.500 0.0295 0.01917 0.00926 -0.0464 0.6682 0.1999
-2.250 0.0552 0.01910 0.00913 -0.0456 0.6604 0.2151
-2.000 0.0808 0.01905 0.00902 -0.0449 0.6532 0.2307
-1.750 0.1058 0.01903 0.00900 -0.0442 0.6456 0.2479
-1.500 0.1321 0.01894 0.00884 -0.0436 0.6401 0.2634
-1.250 0.1578 0.01885 0.00875 -0.0431 0.6330 0.2752
-1.000 0.1843 0.01868 0.00857 -0.0426 0.6263 0.2839
-0.750 0.2119 0.01850 0.00830 -0.0422 0.6210 0.2936
-0.500 0.2382 0.01840 0.00828 -0.0418 0.6129 0.3034
-0.250 0.2662 0.01827 0.00811 -0.0415 0.6066 0.3154
0.000 0.2942 0.01814 0.00801 -0.0414 0.5999 0.3295
0.250 0.3220 0.01801 0.00796 -0.0412 0.5922 0.3482
0.500 0.3505 0.01778 0.00777 -0.0411 0.5863 0.3721
0.750 0.3760 0.01764 0.00782 -0.0406 0.5776 0.4044
1.000 0.4011 0.01724 0.00770 -0.0399 0.5710 0.4741
1.250 0.5163 0.01658 0.00815 -0.0559 0.5588 0.9643
1.500 0.5845 0.01656 0.00795 -0.0638 0.5489 0.9942
1.750 0.6214 0.01660 0.00790 -0.0656 0.5391 1.0000
2.000 0.6451 0.01671 0.00790 -0.0646 0.5313 1.0000
2.250 0.6683 0.01685 0.00798 -0.0637 0.5223 1.0000
2.500 0.6917 0.01697 0.00802 -0.0627 0.5140 1.0000
2.750 0.7145 0.01712 0.00812 -0.0616 0.5044 1.0000
3.000 0.7373 0.01728 0.00821 -0.0606 0.4954 1.0000
3.250 0.7599 0.01745 0.00832 -0.0595 0.4862 1.0000
3.500 0.7823 0.01765 0.00849 -0.0584 0.4771 1.0000
3.750 0.8047 0.01784 0.00861 -0.0573 0.4687 1.0000
4.000 0.8266 0.01809 0.00884 -0.0562 0.4597 1.0000
4.250 0.8485 0.01831 0.00899 -0.0550 0.4515 1.0000
4.500 0.8698 0.01859 0.00926 -0.0538 0.4427 1.0000
4.750 0.8913 0.01883 0.00943 -0.0526 0.4347 1.0000
5.000 0.9120 0.01914 0.00974 -0.0513 0.4259 1.0000
5.250 0.9329 0.01940 0.00993 -0.0500 0.4180 1.0000
5.500 0.9526 0.01973 0.01027 -0.0486 0.4089 1.0000
5.750 0.9727 0.02000 0.01046 -0.0471 0.4007 1.0000
6.000 0.9914 0.02037 0.01086 -0.0456 0.3917 1.0000
6.250 1.0109 0.02068 0.01109 -0.0441 0.3841 1.0000
6.500 1.0287 0.02108 0.01153 -0.0425 0.3757 1.0000
6.750 1.0471 0.02143 0.01182 -0.0408 0.3681 1.0000
7.000 1.0642 0.02186 0.01229 -0.0391 0.3603 1.0000
7.250 1.0815 0.02226 0.01267 -0.0374 0.3533 1.0000
7.500 1.0992 0.02269 0.01309 -0.0357 0.3475 1.0000
7.750 1.1154 0.02317 0.01364 -0.0339 0.3414 1.0000
8.000 1.1322 0.02361 0.01408 -0.0322 0.3358 1.0000
8.250 1.1481 0.02409 0.01459 -0.0304 0.3300 1.0000
8.500 1.1618 0.02461 0.01519 -0.0283 0.3236 1.0000
8.750 1.1772 0.02509 0.01563 -0.0263 0.3178 1.0000
9.000 1.1891 0.02566 0.01630 -0.0241 0.3115 1.0000
9.250 1.2000 0.02623 0.01693 -0.0216 0.3050 1.0000
9.500 1.2134 0.02675 0.01739 -0.0195 0.2993 1.0000
9.750 1.2188 0.02746 0.01826 -0.0165 0.2927 1.0000
10.000 1.2241 0.02809 0.01893 -0.0133 0.2866 1.0000
10.250 1.2308 0.02875 0.01961 -0.0105 0.2810 1.0000
10.500 1.2325 0.02966 0.02065 -0.0075 0.2741 1.0000
10.750 1.2383 0.03049 0.02149 -0.0051 0.2680 1.0000
11.000 1.2411 0.03160 0.02271 -0.0028 0.2611 1.0000
11.250 1.2440 0.03279 0.02396 -0.0008 0.2541 1.0000
11.500 1.2476 0.03405 0.02528 0.0010 0.2472 1.0000
11.750 1.2489 0.03557 0.02690 0.0026 0.2395 1.0000
12.000 1.2523 0.03700 0.02835 0.0040 0.2329 1.0000
12.250 1.2524 0.03883 0.03028 0.0053 0.2252 1.0000
12.500 1.2556 0.04040 0.03182 0.0065 0.2189 1.0000
12.750 1.2548 0.04251 0.03405 0.0075 0.2118 1.0000
13.000 1.2571 0.04430 0.03584 0.0084 0.2061 1.0000
13.250 1.2581 0.04637 0.03799 0.0092 0.2005 1.0000
13.500 1.2589 0.04850 0.04019 0.0099 0.1953 1.0000
13.750 1.2640 0.05019 0.04186 0.0106 0.1914 1.0000
14.000 1.2660 0.05234 0.04409 0.0112 0.1874 1.0000
14.250 1.2666 0.05470 0.04655 0.0116 0.1834 1.0000
14.500 1.2696 0.05678 0.04869 0.0120 0.1799 1.0000
14.750 1.2790 0.05813 0.05001 0.0127 0.1768 1.0000
15.000 1.2766 0.06100 0.05301 0.0127 0.1734 1.0000
15.250 1.2730 0.06408 0.05623 0.0126 0.1698 1.0000
15.500 1.2740 0.06659 0.05880 0.0126 0.1664 1.0000
15.750 1.2856 0.06772 0.05987 0.0131 0.1629 1.0000
16.000 1.2739 0.07205 0.06439 0.0122 0.1596 1.0000
16.250 1.2642 0.07625 0.06876 0.0113 0.1564 1.0000
16.500 1.2620 0.07943 0.07202 0.0108 0.1531 1.0000
16.750 1.2768 0.08007 0.07258 0.0113 0.1494 1.0000
17.000 1.2581 0.08583 0.07855 0.0095 0.1465 1.0000
17.250 1.2365 0.09230 0.08523 0.0072 0.1437 1.0000
17.500 1.2233 0.09754 0.09060 0.0053 0.1405 1.0000
17.750 1.2503 0.09605 0.08896 0.0066 0.1358 1.0000
18.000 1.2215 0.10404 0.09718 0.0033 0.1334 1.0000
18.250 1.1446 0.12125 0.11474 -0.0046 0.1318 1.0000
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