GOE 13K AIRFOIL (goe13k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 13K AIRFOIL (goe13k-il) Reynolds number: 1,000,000 Max Cl/Cd: 129 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe13k-il-1000000.txt Download as CSV file: xf-goe13k-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 13K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.0399 0.12273 0.12051 -0.1570 0.9523 0.0305
-14.250 -0.0248 0.11881 0.11657 -0.1613 0.9537 0.0310
-13.750 -0.5047 0.03229 0.02908 -0.2065 0.9345 0.0385
-13.500 -0.4918 0.03103 0.02776 -0.2070 0.9329 0.0388
-13.250 -0.4679 0.03041 0.02712 -0.2082 0.9319 0.0390
-13.000 -0.4403 0.02994 0.02664 -0.2097 0.9311 0.0393
-12.750 -0.4326 0.02936 0.02601 -0.2077 0.9272 0.0395
-12.500 -0.4282 0.02855 0.02511 -0.2051 0.9230 0.0397
-12.250 -0.4049 0.02824 0.02479 -0.2054 0.9211 0.0400
-12.000 -0.3924 0.02674 0.02312 -0.2050 0.9188 0.0404
-11.750 -0.3691 0.02573 0.02198 -0.2061 0.9170 0.0409
-11.500 -0.3880 0.02504 0.02119 -0.1976 0.9103 0.0410
-11.250 -0.3747 0.02417 0.02018 -0.1960 0.9074 0.0416
-11.000 -0.3560 0.02278 0.01859 -0.1959 0.9052 0.0421
-10.750 -0.3294 0.02155 0.01715 -0.1973 0.9034 0.0425
-10.500 -0.3410 0.02138 0.01690 -0.1893 0.8981 0.0428
-10.250 -0.3311 0.02090 0.01631 -0.1862 0.8947 0.0430
-10.000 -0.3197 0.01976 0.01497 -0.1838 0.8920 0.0433
-9.750 -0.2985 0.01813 0.01319 -0.1839 0.8901 0.0439
-9.500 -0.2655 0.01750 0.01250 -0.1858 0.8887 0.0443
-9.250 -0.2645 0.01736 0.01234 -0.1803 0.8851 0.0446
-9.000 -0.2605 0.01707 0.01200 -0.1755 0.8815 0.0448
-8.750 -0.2423 0.01667 0.01155 -0.1738 0.8790 0.0452
-8.500 -0.2198 0.01627 0.01110 -0.1730 0.8768 0.0456
-8.250 -0.1929 0.01567 0.01040 -0.1733 0.8750 0.0458
-8.000 -0.1599 0.01518 0.00984 -0.1749 0.8734 0.0464
-7.750 -0.1480 0.01491 0.00952 -0.1717 0.8707 0.0467
-7.500 -0.1480 0.01469 0.00926 -0.1657 0.8670 0.0470
-7.250 -0.1310 0.01437 0.00888 -0.1635 0.8644 0.0475
-7.000 -0.1086 0.01404 0.00849 -0.1626 0.8623 0.0479
-6.750 -0.0839 0.01366 0.00804 -0.1621 0.8604 0.0482
-6.500 -0.0532 0.01338 0.00768 -0.1630 0.8588 0.0486
-6.250 -0.0179 0.01311 0.00735 -0.1649 0.8572 0.0488
-6.000 -0.0168 0.01259 0.00679 -0.1592 0.8541 0.0493
-5.750 -0.0092 0.01223 0.00640 -0.1549 0.8508 0.0496
-5.500 0.0090 0.01190 0.00607 -0.1529 0.8483 0.0501
-5.250 0.0320 0.01161 0.00577 -0.1520 0.8460 0.0505
-5.000 0.0589 0.01138 0.00552 -0.1520 0.8442 0.0512
-4.750 0.0940 0.01109 0.00521 -0.1538 0.8422 0.0517
-4.500 0.1054 0.01100 0.00511 -0.1502 0.8389 0.0523
-4.250 0.1082 0.01093 0.00503 -0.1446 0.8351 0.0527
-4.000 0.1267 0.01077 0.00485 -0.1426 0.8324 0.0532
-3.750 0.1490 0.01058 0.00464 -0.1414 0.8301 0.0537
-3.500 0.1766 0.01039 0.00442 -0.1415 0.8279 0.0544
-3.250 0.2108 0.01019 0.00419 -0.1430 0.8259 0.0548
-3.000 0.2193 0.01016 0.00416 -0.1387 0.8228 0.0551
-2.750 0.2279 0.01012 0.00411 -0.1344 0.8193 0.0553
-2.500 0.2439 0.00989 0.00387 -0.1318 0.8166 0.0560
-2.250 0.2638 0.00969 0.00366 -0.1301 0.8143 0.0568
-2.000 0.2905 0.00951 0.00347 -0.1300 0.8122 0.0579
-1.750 0.3238 0.00936 0.00333 -0.1313 0.8105 0.0591
-1.500 0.3392 0.00933 0.00330 -0.1286 0.8077 0.0602
-1.250 0.3454 0.00933 0.00331 -0.1237 0.8042 0.0606
-1.000 0.3629 0.00928 0.00325 -0.1214 0.8013 0.0617
-0.750 0.3839 0.00921 0.00318 -0.1199 0.7986 0.0624
-0.500 0.4113 0.00912 0.00308 -0.1199 0.7968 0.0632
-0.250 0.4428 0.00897 0.00293 -0.1208 0.7949 0.0663
0.000 0.4680 0.00892 0.00290 -0.1203 0.7927 0.0684
0.250 0.4761 0.00896 0.00297 -0.1160 0.7896 0.0698
0.500 0.4913 0.00896 0.00298 -0.1132 0.7866 0.0738
0.750 0.5117 0.00891 0.00298 -0.1116 0.7840 0.0803
1.000 0.5368 0.00875 0.00300 -0.1112 0.7819 0.1290
1.250 0.5680 0.00863 0.00297 -0.1121 0.7798 0.1647
1.500 0.6043 0.00847 0.00295 -0.1142 0.7775 0.2082
1.750 0.6174 0.00830 0.00314 -0.1113 0.7747 0.3306
2.000 0.8606 0.00743 0.00408 -0.1617 0.7784 0.9774
2.250 0.9257 0.00774 0.00439 -0.1702 0.7765 0.9887
2.500 0.9712 0.00791 0.00459 -0.1744 0.7726 0.9949
2.750 1.0178 0.00789 0.00450 -0.1788 0.7625 0.9996
3.000 1.0242 0.00802 0.00465 -0.1742 0.7551 1.0000
3.250 1.0344 0.00813 0.00470 -0.1703 0.7453 1.0000
3.500 1.0358 0.00835 0.00490 -0.1646 0.7342 1.0000
3.750 1.0441 0.00854 0.00507 -0.1604 0.7231 1.0000
4.000 1.0509 0.00878 0.00526 -0.1559 0.7105 1.0000
4.250 1.0573 0.00906 0.00549 -0.1513 0.6972 1.0000
4.500 1.0642 0.00938 0.00576 -0.1470 0.6811 1.0000
4.750 1.0633 0.00987 0.00618 -0.1410 0.6547 1.0000
5.000 1.0161 0.01162 0.00752 -0.1256 0.5668 1.0000
5.250 0.9748 0.01370 0.00917 -0.1122 0.4845 1.0000
5.500 0.9737 0.01465 0.00997 -0.1070 0.4534 1.0000
5.750 0.9825 0.01529 0.01054 -0.1036 0.4363 1.0000
6.000 0.9937 0.01586 0.01104 -0.1007 0.4222 1.0000
6.250 1.0062 0.01640 0.01155 -0.0981 0.4110 1.0000
6.500 1.0203 0.01690 0.01202 -0.0959 0.3995 1.0000
6.750 1.0334 0.01744 0.01251 -0.0935 0.3888 1.0000
7.000 1.0503 0.01785 0.01291 -0.0917 0.3785 1.0000
7.250 1.0638 0.01841 0.01344 -0.0895 0.3669 1.0000
7.500 1.0771 0.01899 0.01395 -0.0872 0.3529 1.0000
7.750 1.0907 0.01956 0.01446 -0.0850 0.3353 1.0000
8.000 1.1026 0.02023 0.01505 -0.0826 0.3132 1.0000
8.250 1.1093 0.02115 0.01580 -0.0794 0.2798 1.0000
8.500 1.1119 0.02229 0.01668 -0.0756 0.2343 1.0000
8.750 1.1183 0.02327 0.01748 -0.0725 0.2005 1.0000
9.000 1.1259 0.02422 0.01825 -0.0697 0.1688 1.0000
9.250 1.1359 0.02507 0.01895 -0.0672 0.1428 1.0000
9.500 1.1485 0.02581 0.01958 -0.0652 0.1258 1.0000
9.750 1.1622 0.02650 0.02022 -0.0634 0.1141 1.0000
10.000 1.1759 0.02720 0.02086 -0.0616 0.1039 1.0000
10.250 1.1912 0.02782 0.02146 -0.0600 0.0972 1.0000
10.500 1.2058 0.02848 0.02208 -0.0584 0.0906 1.0000
10.750 1.2214 0.02909 0.02269 -0.0570 0.0856 1.0000
11.000 1.2355 0.02979 0.02337 -0.0554 0.0808 1.0000
11.250 1.2496 0.03051 0.02408 -0.0538 0.0770 1.0000
11.500 1.2656 0.03112 0.02472 -0.0525 0.0747 1.0000
11.750 1.2804 0.03181 0.02540 -0.0510 0.0715 1.0000
12.000 1.2936 0.03261 0.02618 -0.0494 0.0677 1.0000
12.250 1.3085 0.03330 0.02691 -0.0481 0.0666 1.0000
12.500 1.3229 0.03402 0.02765 -0.0467 0.0644 1.0000
12.750 1.3366 0.03480 0.02843 -0.0452 0.0619 1.0000
13.000 1.3487 0.03570 0.02932 -0.0436 0.0594 1.0000
13.250 1.3636 0.03641 0.03008 -0.0424 0.0580 1.0000
13.500 1.3770 0.03724 0.03093 -0.0410 0.0563 1.0000
13.750 1.3895 0.03813 0.03184 -0.0396 0.0545 1.0000
14.000 1.3996 0.03920 0.03290 -0.0379 0.0519 1.0000
14.250 1.4139 0.03998 0.03374 -0.0367 0.0506 1.0000
14.500 1.4264 0.04090 0.03470 -0.0354 0.0491 1.0000
14.750 1.4376 0.04190 0.03570 -0.0340 0.0470 1.0000
15.000 1.4468 0.04308 0.03689 -0.0323 0.0451 1.0000
15.250 1.4593 0.04403 0.03789 -0.0311 0.0437 1.0000
15.500 1.4703 0.04509 0.03897 -0.0298 0.0418 1.0000
15.750 1.4782 0.04640 0.04029 -0.0282 0.0398 1.0000
16.000 1.4879 0.04760 0.04155 -0.0269 0.0386 1.0000
16.250 1.4976 0.04880 0.04277 -0.0256 0.0365 1.0000
16.500 1.5051 0.05019 0.04418 -0.0241 0.0351 1.0000
16.750 1.5115 0.05170 0.04573 -0.0227 0.0339 1.0000
17.000 1.5201 0.05304 0.04712 -0.0214 0.0326 1.0000
17.250 1.5260 0.05462 0.04874 -0.0200 0.0313 1.0000
17.500 1.5287 0.05652 0.05066 -0.0185 0.0299 1.0000
17.750 1.5355 0.05808 0.05228 -0.0173 0.0290 1.0000
18.000 1.5397 0.05991 0.05418 -0.0161 0.0284 1.0000
18.250 1.5437 0.06178 0.05608 -0.0149 0.0270 1.0000
18.500 1.5452 0.06391 0.05826 -0.0137 0.0263 1.0000
18.750 1.5453 0.06623 0.06064 -0.0125 0.0254 1.0000
19.000 1.5487 0.06825 0.06274 -0.0115 0.0248 1.0000
19.250 1.5499 0.07055 0.06511 -0.0106 0.0242 1.0000
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