GOE 531 AIRFOIL (goe531-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 531 AIRFOIL (goe531-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.82 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe531-il-1000000.txt Download as CSV file: xf-goe531-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 531 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
------ -------- --------- --------- -------- -------- --------
-11.500 0.6560 0.09170 0.08761 -0.2468 0.6809 0.0300
-11.250 0.6658 0.09013 0.08604 -0.2474 0.6799 0.0305
-11.000 0.6752 0.08854 0.08445 -0.2480 0.6790 0.0307
-10.750 0.6843 0.08695 0.08286 -0.2486 0.6779 0.0313
-10.500 0.6929 0.08536 0.08126 -0.2491 0.6768 0.0316
-10.250 0.7011 0.08380 0.07970 -0.2496 0.6755 0.0318
-10.000 0.7086 0.08230 0.07818 -0.2502 0.6741 0.0319
-9.750 0.7168 0.08083 0.07670 -0.2509 0.6723 0.0320
-9.500 0.7270 0.07934 0.07520 -0.2519 0.6706 0.0320
-9.250 0.7332 0.07790 0.07378 -0.2522 0.6700 0.0321
-9.000 0.7390 0.07649 0.07239 -0.2522 0.6695 0.0321
-8.750 0.7441 0.07506 0.07100 -0.2522 0.6689 0.0321
-8.500 0.7527 0.07306 0.06902 -0.2519 0.6682 0.0323
-8.250 0.7624 0.07163 0.06761 -0.2516 0.6674 0.0323
-8.000 0.7721 0.07036 0.06635 -0.2513 0.6666 0.0324
-7.750 0.7807 0.06917 0.06519 -0.2508 0.6655 0.0326
-7.500 0.7892 0.06808 0.06411 -0.2504 0.6645 0.0328
-7.250 0.7965 0.06697 0.06302 -0.2497 0.6634 0.0329
-7.000 0.8036 0.06593 0.06199 -0.2490 0.6623 0.0332
-6.750 0.8095 0.06486 0.06094 -0.2482 0.6612 0.0334
-6.500 0.8147 0.06383 0.05993 -0.2471 0.6602 0.0339
-6.250 0.8183 0.06281 0.05893 -0.2458 0.6591 0.0343
-6.000 0.8205 0.06181 0.05794 -0.2442 0.6579 0.0347
-5.750 0.8206 0.06084 0.05698 -0.2423 0.6565 0.0353
-5.500 0.8133 0.05995 0.05611 -0.2394 0.6547 0.0359
-5.250 0.8108 0.05895 0.05511 -0.2389 0.6525 0.0362
-5.000 0.8080 0.05798 0.05419 -0.2367 0.6519 0.0362
-4.750 0.8049 0.05704 0.05329 -0.2341 0.6512 0.0362
-4.500 0.7967 0.05629 0.05259 -0.2300 0.6503 0.0362
-4.250 0.7931 0.05532 0.05166 -0.2271 0.6493 0.0363
-4.000 0.7901 0.05383 0.05021 -0.2240 0.6482 0.0365
-3.750 0.7915 0.05290 0.04931 -0.2215 0.6470 0.0366
-3.500 0.7952 0.05203 0.04846 -0.2193 0.6458 0.0367
-3.250 0.8007 0.05108 0.04753 -0.2177 0.6446 0.0368
-3.000 0.8064 0.05016 0.04662 -0.2161 0.6433 0.0370
-2.750 0.8841 0.02220 0.01783 -0.2629 0.6420 0.0331
-2.500 0.9169 0.01910 0.01446 -0.2678 0.6408 0.0334
-2.250 0.9449 0.01743 0.01259 -0.2698 0.6395 0.0335
-2.000 0.9731 0.01626 0.01125 -0.2714 0.6381 0.0338
-1.750 1.0039 0.01531 0.01014 -0.2731 0.6365 0.0340
-1.500 1.0351 0.01458 0.00927 -0.2748 0.6350 0.0343
-1.250 1.0535 0.01408 0.00869 -0.2736 0.6344 0.0345
-1.000 1.0723 0.01370 0.00824 -0.2723 0.6336 0.0346
-0.750 1.0908 0.01351 0.00801 -0.2709 0.6327 0.0349
-0.500 1.1093 0.01339 0.00785 -0.2694 0.6316 0.0350
-0.250 1.1287 0.01329 0.00771 -0.2681 0.6304 0.0352
0.000 1.1487 0.01322 0.00760 -0.2669 0.6291 0.0355
0.250 1.1690 0.01318 0.00753 -0.2658 0.6278 0.0357
0.500 1.1884 0.01316 0.00746 -0.2644 0.6264 0.0360
0.750 1.2085 0.01317 0.00744 -0.2633 0.6251 0.0362
1.000 1.2291 0.01316 0.00740 -0.2622 0.6239 0.0367
1.250 1.2513 0.01314 0.00734 -0.2614 0.6225 0.0381
1.500 1.2753 0.01317 0.00734 -0.2610 0.6211 0.0391
1.750 1.3033 0.01318 0.00730 -0.2613 0.6194 0.0419
2.000 1.3318 0.01321 0.00740 -0.2618 0.6178 0.0613
2.250 1.3456 0.01349 0.00772 -0.2595 0.6170 0.0676
2.500 1.3594 0.01378 0.00806 -0.2572 0.6159 0.0707
2.750 1.3756 0.01403 0.00832 -0.2554 0.6147 0.0726
3.000 1.3923 0.01424 0.00854 -0.2538 0.6133 0.0746
3.250 1.4086 0.01448 0.00881 -0.2521 0.6118 0.0764
3.500 1.4264 0.01469 0.00904 -0.2506 0.6103 0.0780
3.750 1.4448 0.01489 0.00923 -0.2493 0.6088 0.0792
4.000 1.4631 0.01511 0.00945 -0.2480 0.6073 0.0803
4.250 1.4822 0.01527 0.00960 -0.2468 0.6058 0.0816
4.500 1.5039 0.01541 0.00975 -0.2461 0.6042 0.0835
4.750 1.5314 0.01547 0.00980 -0.2465 0.6023 0.0852
5.000 1.5497 0.01575 0.01009 -0.2453 0.6005 0.0871
5.250 1.5585 0.01623 0.01061 -0.2424 0.5991 0.0883
5.500 1.5695 0.01668 0.01110 -0.2400 0.5975 0.0889
5.750 1.5807 0.01711 0.01156 -0.2376 0.5955 0.0912
6.000 1.5957 0.01747 0.01195 -0.2359 0.5936 0.0922
6.250 1.6114 0.01783 0.01233 -0.2343 0.5917 0.0935
6.500 1.6260 0.01825 0.01276 -0.2326 0.5899 0.0949
6.750 1.6446 0.01854 0.01305 -0.2315 0.5879 0.0963
7.000 1.6689 0.01866 0.01316 -0.2314 0.5860 0.0977
7.250 1.6898 0.01890 0.01341 -0.2307 0.5839 0.1016
7.500 1.6960 0.01968 0.01426 -0.2278 0.5824 0.1039
7.750 1.6932 0.02087 0.01551 -0.2235 0.5788 0.1071
8.000 1.7063 0.02145 0.01615 -0.2217 0.5768 0.1180
8.250 1.7158 0.02219 0.01699 -0.2194 0.5741 0.1610
8.500 1.7315 0.02268 0.01752 -0.2181 0.5718 0.1857
8.750 1.7533 0.02289 0.01773 -0.2176 0.5695 0.1999
9.000 1.7712 0.02331 0.01818 -0.2167 0.5671 0.2090
9.250 1.7668 0.02493 0.01987 -0.2126 0.5643 0.2131
9.500 1.7722 0.02608 0.02109 -0.2100 0.5614 0.2199
9.750 1.7799 0.02714 0.02218 -0.2078 0.5587 0.2259
10.000 1.7918 0.02795 0.02300 -0.2061 0.5561 0.2305
10.250 1.8100 0.02836 0.02343 -0.2053 0.5538 0.2386
10.500 1.8361 0.02829 0.02334 -0.2056 0.5511 0.2452
10.750 1.8265 0.03052 0.02566 -0.2013 0.5482 0.2473
11.000 1.8280 0.03209 0.02729 -0.1985 0.5451 0.2512
11.250 1.8292 0.03371 0.02896 -0.1957 0.5411 0.2566
11.500 1.8429 0.03445 0.02970 -0.1944 0.5377 0.2623
11.750 1.8670 0.03444 0.02966 -0.1944 0.5344 0.2681
12.000 1.8487 0.03754 0.03289 -0.1895 0.5301 0.2717
12.250 1.8488 0.03936 0.03476 -0.1868 0.5258 0.2761
12.500 1.8589 0.04040 0.03581 -0.1852 0.5219 0.2820
12.750 1.8781 0.04074 0.03613 -0.1847 0.5183 0.2897
13.000 1.8645 0.04370 0.03919 -0.1806 0.5134 0.2925
13.250 1.8588 0.04606 0.04159 -0.1775 0.5072 0.2964
13.500 1.8702 0.04701 0.04254 -0.1762 0.5030 0.3015
13.750 1.8703 0.04896 0.04454 -0.1738 0.4976 0.3068
14.000 1.8650 0.05139 0.04704 -0.1708 0.4919 0.3121
14.250 1.8715 0.05278 0.04840 -0.1691 0.4853 0.3186
14.500 1.8690 0.05503 0.05073 -0.1666 0.4784 0.3260
14.750 1.8635 0.05750 0.05320 -0.1638 0.4698 0.3321
15.000 1.8635 0.05956 0.05530 -0.1616 0.4615 0.3433
15.250 1.8522 0.06261 0.05834 -0.1584 0.4490 0.3544
15.500 1.8378 0.06599 0.06168 -0.1549 0.4297 0.3676
15.750 1.7921 0.07231 0.06781 -0.1488 0.3925 0.3633
16.000 1.7343 0.08017 0.07541 -0.1422 0.3522 0.3533
16.250 1.8057 0.09568 0.09155 -0.1684 0.3103 1.0000
16.500 1.8025 0.09845 0.09430 -0.1666 0.3009 1.0000
16.750 1.7993 0.10123 0.09706 -0.1649 0.2929 1.0000
17.000 1.8032 0.10320 0.09903 -0.1637 0.2851 1.0000
17.250 1.8013 0.10584 0.10162 -0.1621 0.2756 1.0000
17.500 1.8006 0.10838 0.10417 -0.1607 0.2660 1.0000
17.750 1.7990 0.11101 0.10675 -0.1593 0.2540 1.0000
18.000 1.7942 0.11400 0.10965 -0.1578 0.2363 1.0000
18.250 1.7780 0.11833 0.11382 -0.1558 0.2098 1.0000
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