GOE 652 AIRFOIL (goe652-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 652 AIRFOIL (goe652-il) Reynolds number: 1,000,000 Max Cl/Cd: 135.65 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe652-il-1000000.txt Download as CSV file: xf-goe652-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.1024 0.06263 0.05951 -0.1711 0.8779 0.0524
-12.250 -0.1192 0.05627 0.05293 -0.1778 0.8630 0.0529
-12.000 -0.1239 0.05252 0.04905 -0.1811 0.8510 0.0532
-11.750 -0.1242 0.04963 0.04606 -0.1833 0.8415 0.0535
-11.500 -0.1242 0.04704 0.04338 -0.1849 0.8324 0.0538
-11.250 -0.1222 0.04476 0.04100 -0.1862 0.8234 0.0540
-11.000 -0.1191 0.04308 0.03931 -0.1865 0.8175 0.0544
-10.750 -0.1127 0.04186 0.03807 -0.1862 0.8109 0.0548
-10.500 -0.1092 0.04063 0.03680 -0.1856 0.8038 0.0553
-10.250 -0.1023 0.03924 0.03540 -0.1860 0.7984 0.0556
-10.000 -0.0929 0.03768 0.03383 -0.1870 0.7930 0.0559
-9.750 -0.0832 0.03591 0.03202 -0.1887 0.7871 0.0563
-9.500 -0.0700 0.03424 0.03029 -0.1906 0.7807 0.0568
-9.250 -0.0538 0.03254 0.02856 -0.1931 0.7763 0.0573
-9.000 -0.0356 0.03057 0.02656 -0.1965 0.7719 0.0578
-8.750 -0.0132 0.02883 0.02476 -0.2000 0.7671 0.0583
-8.500 0.0123 0.02697 0.02282 -0.2043 0.7622 0.0588
-8.250 0.0423 0.02517 0.02092 -0.2093 0.7567 0.0592
-8.000 0.0767 0.02345 0.01920 -0.2148 0.7535 0.0603
-7.750 0.1168 0.02124 0.01695 -0.2224 0.7491 0.0614
-7.500 0.1597 0.01917 0.01479 -0.2298 0.7437 0.0625
-7.250 0.2032 0.01738 0.01288 -0.2366 0.7380 0.0637
-7.000 0.2463 0.01587 0.01126 -0.2425 0.7331 0.0648
-6.750 0.2986 0.01352 0.00882 -0.2516 0.7285 0.0669
-6.500 0.3418 0.01204 0.00723 -0.2569 0.7230 0.0687
-6.250 0.3771 0.01146 0.00654 -0.2590 0.7179 0.0702
-6.000 0.4124 0.01093 0.00593 -0.2610 0.7127 0.0723
-5.750 0.4468 0.01049 0.00548 -0.2626 0.7090 0.0748
-5.500 0.4791 0.01025 0.00519 -0.2635 0.7040 0.0771
-5.250 0.5122 0.00991 0.00481 -0.2646 0.6981 0.0805
-5.000 0.5431 0.00978 0.00460 -0.2651 0.6912 0.0838
-4.750 0.5756 0.00950 0.00433 -0.2660 0.6858 0.0881
-4.500 0.6067 0.00936 0.00416 -0.2664 0.6800 0.0923
-4.250 0.6377 0.00922 0.00399 -0.2668 0.6740 0.0971
-4.000 0.6685 0.00912 0.00385 -0.2672 0.6686 0.1016
-3.750 0.6994 0.00900 0.00373 -0.2676 0.6633 0.1061
-3.500 0.7299 0.00892 0.00362 -0.2678 0.6569 0.1105
-3.250 0.7594 0.00890 0.00354 -0.2679 0.6494 0.1149
-3.000 0.7900 0.00882 0.00346 -0.2681 0.6438 0.1193
-2.750 0.8200 0.00878 0.00340 -0.2682 0.6367 0.1241
-2.500 0.8490 0.00880 0.00336 -0.2681 0.6287 0.1287
-2.250 0.8791 0.00875 0.00332 -0.2683 0.6222 0.1338
-2.000 0.9082 0.00877 0.00329 -0.2682 0.6140 0.1381
-1.750 0.9372 0.00880 0.00329 -0.2681 0.6063 0.1433
-1.500 0.9667 0.00882 0.00329 -0.2680 0.6001 0.1476
-1.250 0.9958 0.00884 0.00330 -0.2680 0.5930 0.1531
-1.000 1.0241 0.00892 0.00334 -0.2677 0.5858 0.1580
-0.750 1.0534 0.00894 0.00335 -0.2677 0.5800 0.1624
-0.500 1.0821 0.00900 0.00340 -0.2675 0.5730 0.1678
-0.250 1.1096 0.00913 0.00348 -0.2671 0.5656 0.1725
0.000 1.1388 0.00915 0.00350 -0.2670 0.5600 0.1775
0.250 1.1670 0.00923 0.00358 -0.2667 0.5525 0.1820
0.500 1.1941 0.00938 0.00366 -0.2663 0.5442 0.1857
0.750 1.2223 0.00946 0.00373 -0.2660 0.5371 0.1883
1.000 1.2499 0.00956 0.00379 -0.2657 0.5283 0.1937
1.250 1.2774 0.00967 0.00389 -0.2653 0.5209 0.1977
1.500 1.3050 0.00978 0.00398 -0.2649 0.5132 0.2013
1.750 1.3309 0.00998 0.00411 -0.2642 0.5041 0.2037
2.000 1.3589 0.01004 0.00417 -0.2640 0.4957 0.2086
2.250 1.3843 0.01025 0.00433 -0.2632 0.4838 0.2128
2.500 1.4108 0.01040 0.00445 -0.2627 0.4722 0.2165
2.750 1.4356 0.01064 0.00462 -0.2618 0.4585 0.2196
3.000 1.4594 0.01092 0.00480 -0.2608 0.4416 0.2225
3.250 1.4823 0.01125 0.00503 -0.2597 0.4198 0.2280
3.500 1.5031 0.01168 0.00534 -0.2583 0.3949 0.2321
3.750 1.5238 0.01211 0.00566 -0.2567 0.3759 0.2358
4.000 1.5447 0.01251 0.00596 -0.2553 0.3625 0.2388
4.250 1.5673 0.01279 0.00621 -0.2541 0.3537 0.2433
4.500 1.5881 0.01314 0.00652 -0.2526 0.3451 0.2488
4.750 1.6102 0.01335 0.00675 -0.2513 0.3407 0.2536
5.000 1.6297 0.01362 0.00701 -0.2495 0.3362 0.2574
5.250 1.6480 0.01394 0.00730 -0.2476 0.3315 0.2609
5.500 1.6655 0.01430 0.00766 -0.2455 0.3262 0.2678
5.750 1.6869 0.01452 0.00793 -0.2442 0.3238 0.2736
6.000 1.7075 0.01479 0.00821 -0.2427 0.3210 0.2783
6.250 1.7266 0.01511 0.00854 -0.2410 0.3177 0.2836
6.500 1.7450 0.01548 0.00893 -0.2392 0.3145 0.2907
6.750 1.7621 0.01591 0.00937 -0.2372 0.3111 0.2969
7.000 1.7777 0.01643 0.00987 -0.2350 0.3076 0.3012
7.250 1.7974 0.01677 0.01026 -0.2336 0.3057 0.3084
7.500 1.8177 0.01708 0.01064 -0.2322 0.3038 0.3152
7.750 1.8368 0.01747 0.01105 -0.2307 0.3011 0.3210
8.000 1.8547 0.01792 0.01153 -0.2290 0.2982 0.3268
8.250 1.8710 0.01847 0.01210 -0.2271 0.2953 0.3339
8.500 1.8862 0.01910 0.01274 -0.2252 0.2922 0.3399
8.750 1.8987 0.01990 0.01354 -0.2229 0.2883 0.3444
9.000 1.9182 0.02032 0.01402 -0.2216 0.2864 0.3509
9.250 1.9372 0.02079 0.01455 -0.2203 0.2841 0.3577
9.500 1.9541 0.02138 0.01518 -0.2187 0.2810 0.3639
9.750 1.9700 0.02207 0.01587 -0.2171 0.2779 0.3692
10.000 1.9834 0.02292 0.01675 -0.2152 0.2744 0.3758
10.250 1.9949 0.02393 0.01777 -0.2132 0.2699 0.3816
10.500 2.0131 0.02451 0.01841 -0.2119 0.2674 0.3873
10.750 2.0293 0.02525 0.01919 -0.2105 0.2635 0.3943
11.000 2.0431 0.02617 0.02013 -0.2088 0.2587 0.4015
11.250 2.0522 0.02746 0.02142 -0.2068 0.2530 0.4074
11.500 2.0680 0.02829 0.02229 -0.2054 0.2488 0.4145
11.750 2.0795 0.02946 0.02348 -0.2037 0.2418 0.4222
12.000 2.0878 0.03092 0.02492 -0.2018 0.2340 0.4293
12.250 2.0955 0.03248 0.02648 -0.1999 0.2235 0.4380
12.500 2.1002 0.03435 0.02831 -0.1978 0.2114 0.4466
12.750 2.1008 0.03665 0.03058 -0.1956 0.1991 0.4552
13.000 2.1021 0.03898 0.03288 -0.1935 0.1889 0.4661
13.250 2.1053 0.04121 0.03512 -0.1917 0.1825 0.4789
13.500 2.1079 0.04356 0.03749 -0.1900 0.1762 0.4949
13.750 2.1148 0.04555 0.03956 -0.1887 0.1729 0.5218
14.000 2.1214 0.04763 0.04172 -0.1874 0.1694 0.5716
14.250 2.1248 0.04985 0.04436 -0.1861 0.1658 1.0000
14.500 2.1295 0.05219 0.04671 -0.1848 0.1624 1.0000
14.750 2.1371 0.05425 0.04882 -0.1838 0.1604 1.0000
15.000 2.1439 0.05643 0.05104 -0.1827 0.1579 1.0000
15.250 2.1476 0.05902 0.05366 -0.1816 0.1553 1.0000
15.500 2.1493 0.06191 0.05658 -0.1806 0.1523 1.0000
15.750 2.1504 0.06492 0.05962 -0.1796 0.1496 1.0000
16.000 2.1595 0.06693 0.06170 -0.1789 0.1480 1.0000
16.250 2.1670 0.06917 0.06398 -0.1782 0.1459 1.0000
16.500 2.1697 0.07209 0.06695 -0.1775 0.1434 1.0000
16.750 2.1715 0.07513 0.07002 -0.1768 0.1406 1.0000
17.000 2.1681 0.07898 0.07391 -0.1763 0.1376 1.0000
17.250 2.1765 0.08116 0.07615 -0.1758 0.1358 1.0000
17.500 2.1810 0.08393 0.07898 -0.1754 0.1331 1.0000
17.750 2.1816 0.08727 0.08235 -0.1750 0.1299 1.0000
18.000 2.1775 0.09135 0.08646 -0.1748 0.1263 1.0000
18.250 2.1816 0.09420 0.08937 -0.1746 0.1235 1.0000
18.500 2.1818 0.09764 0.09285 -0.1745 0.1194 1.0000
18.750 2.1755 0.10211 0.09734 -0.1747 0.1153 1.0000
19.000 2.1753 0.10566 0.10093 -0.1748 0.1113 1.0000
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