GOE 652 AIRFOIL (goe652-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 652 AIRFOIL (goe652-il) Reynolds number: 500,000 Max Cl/Cd: 102.76 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe652-il-500000-n5.txt Download as CSV file: xf-goe652-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 652 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.0185 0.06269 0.05832 -0.1692 0.8267 0.0520
-11.250 -0.0450 0.05656 0.05200 -0.1733 0.8181 0.0525
-11.000 -0.0353 0.05512 0.05055 -0.1739 0.8109 0.0529
-10.750 -0.0264 0.05354 0.04894 -0.1746 0.8044 0.0533
-10.500 -0.0205 0.05166 0.04702 -0.1754 0.7984 0.0536
-10.250 -0.0172 0.04965 0.04500 -0.1761 0.7922 0.0541
-10.000 -0.0140 0.04772 0.04303 -0.1766 0.7856 0.0545
-9.750 -0.0129 0.04573 0.04098 -0.1770 0.7796 0.0549
-9.500 -0.0139 0.04386 0.03909 -0.1769 0.7744 0.0554
-9.250 -0.0139 0.04204 0.03726 -0.1770 0.7688 0.0559
-9.000 -0.0089 0.04007 0.03523 -0.1783 0.7631 0.0564
-8.750 0.0005 0.03824 0.03333 -0.1799 0.7577 0.0569
-8.500 0.0124 0.03637 0.03141 -0.1821 0.7529 0.0574
-8.250 0.0275 0.03449 0.02949 -0.1847 0.7476 0.0579
-8.000 0.0471 0.03300 0.02800 -0.1872 0.7423 0.0585
-7.750 0.0692 0.03117 0.02613 -0.1909 0.7375 0.0593
-7.500 0.0953 0.02916 0.02406 -0.1957 0.7331 0.0601
-7.250 0.1261 0.02715 0.02201 -0.2013 0.7289 0.0611
-7.000 0.1617 0.02511 0.01990 -0.2077 0.7242 0.0622
-6.750 0.2005 0.02325 0.01794 -0.2141 0.7192 0.0633
-6.500 0.2473 0.02093 0.01551 -0.2230 0.7135 0.0648
-6.250 0.2971 0.01870 0.01319 -0.2319 0.7075 0.0668
-6.000 0.3436 0.01702 0.01138 -0.2388 0.7005 0.0690
-5.750 0.3935 0.01513 0.00934 -0.2466 0.6941 0.0716
-5.500 0.4363 0.01389 0.00797 -0.2515 0.6886 0.0745
-5.250 0.4740 0.01319 0.00720 -0.2543 0.6827 0.0772
-5.000 0.5088 0.01274 0.00668 -0.2562 0.6767 0.0805
-4.750 0.5421 0.01243 0.00629 -0.2575 0.6714 0.0837
-4.500 0.5752 0.01214 0.00596 -0.2587 0.6661 0.0875
-4.250 0.6073 0.01191 0.00569 -0.2595 0.6592 0.0914
-4.000 0.6385 0.01175 0.00546 -0.2601 0.6517 0.0958
-3.750 0.6698 0.01159 0.00526 -0.2607 0.6451 0.0999
-3.500 0.7008 0.01147 0.00510 -0.2612 0.6380 0.1043
-3.250 0.7311 0.01138 0.00495 -0.2615 0.6310 0.1082
-3.000 0.7615 0.01131 0.00484 -0.2618 0.6248 0.1126
-2.750 0.7917 0.01124 0.00474 -0.2620 0.6174 0.1168
-2.500 0.8212 0.01122 0.00467 -0.2622 0.6098 0.1218
-2.250 0.8508 0.01119 0.00461 -0.2623 0.6034 0.1263
-2.000 0.8804 0.01117 0.00457 -0.2623 0.5956 0.1313
-1.500 0.9382 0.01122 0.00454 -0.2622 0.5802 0.1408
-1.250 0.9668 0.01127 0.00454 -0.2620 0.5725 0.1461
-1.000 0.9949 0.01134 0.00458 -0.2618 0.5657 0.1518
-0.750 1.0238 0.01138 0.00461 -0.2617 0.5593 0.1578
-0.500 1.0519 0.01146 0.00465 -0.2615 0.5517 0.1626
-0.250 1.0793 0.01157 0.00472 -0.2611 0.5445 0.1671
0.000 1.1076 0.01164 0.00477 -0.2609 0.5376 0.1715
0.250 1.1352 0.01174 0.00484 -0.2605 0.5300 0.1754
0.500 1.1622 0.01187 0.00494 -0.2601 0.5232 0.1795
0.750 1.1900 0.01196 0.00502 -0.2598 0.5164 0.1838
1.000 1.2167 0.01211 0.00511 -0.2593 0.5086 0.1872
1.250 1.2432 0.01225 0.00523 -0.2587 0.5005 0.1911
1.500 1.2694 0.01240 0.00536 -0.2582 0.4895 0.1952
1.750 1.2943 0.01262 0.00551 -0.2573 0.4778 0.1990
2.000 1.3184 0.01287 0.00568 -0.2564 0.4639 0.2023
2.250 1.3431 0.01307 0.00584 -0.2556 0.4504 0.2059
2.500 1.3665 0.01334 0.00606 -0.2545 0.4359 0.2099
2.750 1.3884 0.01367 0.00631 -0.2532 0.4190 0.2139
3.000 1.4090 0.01406 0.00659 -0.2517 0.4010 0.2175
3.250 1.4286 0.01448 0.00690 -0.2500 0.3847 0.2206
3.500 1.4486 0.01485 0.00722 -0.2484 0.3713 0.2244
3.750 1.4663 0.01524 0.00756 -0.2464 0.3605 0.2282
4.000 1.4830 0.01565 0.00792 -0.2442 0.3505 0.2322
4.250 1.5005 0.01605 0.00829 -0.2422 0.3428 0.2361
4.500 1.5198 0.01640 0.00862 -0.2405 0.3371 0.2393
4.750 1.5387 0.01677 0.00898 -0.2388 0.3326 0.2432
5.000 1.5567 0.01719 0.00941 -0.2370 0.3283 0.2480
5.250 1.5755 0.01758 0.00982 -0.2353 0.3249 0.2527
5.500 1.5953 0.01794 0.01020 -0.2338 0.3222 0.2571
5.750 1.6145 0.01833 0.01061 -0.2322 0.3194 0.2611
6.000 1.6333 0.01876 0.01107 -0.2307 0.3165 0.2666
6.250 1.6509 0.01924 0.01159 -0.2289 0.3137 0.2722
6.500 1.6676 0.01980 0.01215 -0.2271 0.3105 0.2774
6.750 1.6829 0.02044 0.01279 -0.2251 0.3071 0.2820
7.000 1.7008 0.02097 0.01337 -0.2236 0.3047 0.2870
7.250 1.7194 0.02147 0.01392 -0.2221 0.3025 0.2934
7.500 1.7373 0.02202 0.01452 -0.2206 0.2996 0.2999
7.750 1.7541 0.02265 0.01518 -0.2190 0.2966 0.3051
8.000 1.7699 0.02336 0.01592 -0.2173 0.2936 0.3106
8.250 1.7849 0.02414 0.01672 -0.2156 0.2906 0.3164
8.500 1.7984 0.02503 0.01764 -0.2138 0.2876 0.3221
8.750 1.8145 0.02578 0.01843 -0.2122 0.2850 0.3277
9.000 1.8319 0.02646 0.01918 -0.2109 0.2824 0.3341
9.250 1.8477 0.02725 0.02003 -0.2094 0.2791 0.3405
9.500 1.8624 0.02815 0.02095 -0.2079 0.2752 0.3461
9.750 1.8747 0.02924 0.02206 -0.2061 0.2712 0.3508
10.000 1.8866 0.03040 0.02324 -0.2044 0.2674 0.3564
10.250 1.9028 0.03124 0.02416 -0.2032 0.2645 0.3633
10.500 1.9170 0.03226 0.02523 -0.2017 0.2606 0.3695
10.750 1.9294 0.03344 0.02645 -0.2002 0.2556 0.3750
11.000 1.9381 0.03497 0.02798 -0.1985 0.2502 0.3805
11.250 1.9514 0.03613 0.02919 -0.1971 0.2438 0.3869
11.500 1.9597 0.03777 0.03083 -0.1955 0.2362 0.3926
11.750 1.9695 0.03932 0.03242 -0.1940 0.2294 0.3993
12.000 1.9760 0.04122 0.03431 -0.1924 0.2201 0.4058
12.250 1.9807 0.04335 0.03643 -0.1908 0.2087 0.4119
12.500 1.9824 0.04587 0.03893 -0.1891 0.1976 0.4182
12.750 1.9841 0.04847 0.04152 -0.1876 0.1889 0.4251
13.000 1.9874 0.05097 0.04403 -0.1862 0.1823 0.4318
13.250 1.9901 0.05360 0.04668 -0.1849 0.1770 0.4392
13.500 1.9955 0.05599 0.04912 -0.1838 0.1734 0.4488
13.750 2.0014 0.05837 0.05156 -0.1828 0.1698 0.4592
14.000 2.0046 0.06112 0.05437 -0.1818 0.1664 0.4707
14.250 2.0069 0.06404 0.05734 -0.1809 0.1630 0.4830
14.500 2.0134 0.06648 0.05988 -0.1802 0.1607 0.4996
14.750 2.0198 0.06898 0.06248 -0.1795 0.1583 0.5254
15.000 2.0248 0.07170 0.06531 -0.1789 0.1557 0.5653
15.250 2.0274 0.07476 0.06853 -0.1784 0.1530 0.6616
15.500 2.0266 0.07765 0.07166 -0.1774 0.1505 1.0000
15.750 2.0298 0.08065 0.07472 -0.1769 0.1484 1.0000
16.000 2.0365 0.08317 0.07731 -0.1764 0.1462 1.0000
16.250 2.0396 0.08624 0.08044 -0.1761 0.1436 1.0000
16.500 2.0418 0.08943 0.08368 -0.1758 0.1409 1.0000
16.750 2.0402 0.09325 0.08754 -0.1756 0.1382 1.0000
17.000 2.0420 0.09654 0.09089 -0.1755 0.1357 1.0000
17.250 2.0459 0.09954 0.09396 -0.1754 0.1331 1.0000
17.500 2.0475 0.10289 0.09737 -0.1755 0.1298 1.0000
17.750 2.0456 0.10680 0.10133 -0.1757 0.1266 1.0000
18.000 2.0449 0.11051 0.10509 -0.1760 0.1238 1.0000
18.250 2.0472 0.11375 0.10840 -0.1762 0.1203 1.0000
18.500 2.0448 0.11775 0.11245 -0.1768 0.1166 1.0000
18.750 2.0417 0.12185 0.11658 -0.1775 0.1133 1.0000
19.000 2.0401 0.12569 0.12049 -0.1782 0.1090 1.0000
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