GOE 648 AIRFOIL (goe648-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 648 AIRFOIL (goe648-il) Reynolds number: 200,000 Max Cl/Cd: 57.42 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe648-il-200000.txt Download as CSV file: xf-goe648-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 648 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5181 0.06878 0.06503 -0.0669 1.0000 0.0554
-10.750 -0.5425 0.06466 0.06094 -0.0670 1.0000 0.0550
-10.500 -0.5738 0.06155 0.05784 -0.0657 1.0000 0.0548
-10.250 -0.6098 0.05978 0.05609 -0.0620 1.0000 0.0545
-10.000 -0.6460 0.05823 0.05451 -0.0569 1.0000 0.0543
-9.750 -0.6737 0.05107 0.04695 -0.0596 0.9944 0.0538
-9.500 -0.6813 0.04306 0.03815 -0.0633 0.9847 0.0544
-9.250 -0.6750 0.03789 0.03215 -0.0646 0.9771 0.0556
-9.000 -0.6426 0.03693 0.03136 -0.0662 0.9725 0.0570
-8.750 -0.6098 0.03529 0.02959 -0.0685 0.9688 0.0586
-8.500 -0.5907 0.03311 0.02706 -0.0683 0.9614 0.0602
-8.250 -0.5644 0.03092 0.02421 -0.0692 0.9560 0.0624
-8.000 -0.5275 0.02931 0.02265 -0.0718 0.9535 0.0644
-7.750 -0.5062 0.02840 0.02170 -0.0709 0.9451 0.0660
-7.500 -0.4718 0.02714 0.02015 -0.0724 0.9410 0.0688
-7.250 -0.4341 0.02563 0.01841 -0.0746 0.9384 0.0716
-7.000 -0.4128 0.02486 0.01766 -0.0735 0.9296 0.0736
-6.750 -0.3759 0.02392 0.01659 -0.0752 0.9256 0.0768
-6.500 -0.3356 0.02273 0.01524 -0.0775 0.9230 0.0807
-6.250 -0.3100 0.02201 0.01457 -0.0770 0.9147 0.0838
-6.000 -0.2703 0.02117 0.01358 -0.0789 0.9100 0.0885
-5.750 -0.2251 0.01993 0.01242 -0.0821 0.9074 0.0943
-5.500 -0.1762 0.01893 0.01133 -0.0857 0.9054 0.1013
-5.250 -0.1538 0.01826 0.01076 -0.0845 0.8946 0.1068
-5.000 -0.1118 0.01739 0.00987 -0.0868 0.8907 0.1150
-4.750 -0.0793 0.01681 0.00932 -0.0874 0.8833 0.1230
-4.500 -0.0461 0.01609 0.00865 -0.0880 0.8752 0.1316
-4.250 -0.0072 0.01546 0.00800 -0.0897 0.8691 0.1425
-4.000 0.0189 0.01498 0.00757 -0.0889 0.8575 0.1535
-3.750 0.0488 0.01444 0.00708 -0.0889 0.8476 0.1685
-3.500 0.0782 0.01389 0.00662 -0.0889 0.8375 0.1917
-3.250 0.1019 0.01338 0.00632 -0.0878 0.8258 0.2305
-3.000 0.1318 0.01284 0.00597 -0.0879 0.8163 0.2929
-2.750 0.1529 0.01248 0.00581 -0.0863 0.8028 0.3453
-2.500 0.1763 0.01215 0.00566 -0.0851 0.7905 0.4020
-2.250 0.2031 0.01185 0.00552 -0.0845 0.7796 0.4668
-2.000 0.2244 0.01168 0.00549 -0.0827 0.7658 0.5226
-1.750 0.2473 0.01152 0.00543 -0.0812 0.7522 0.5705
-1.500 0.2716 0.01138 0.00534 -0.0799 0.7389 0.6132
-1.250 0.2962 0.01124 0.00525 -0.0787 0.7252 0.6541
-1.000 0.3185 0.01115 0.00523 -0.0769 0.7100 0.6931
-0.750 0.3407 0.01109 0.00523 -0.0751 0.6948 0.7335
-0.500 0.3631 0.01104 0.00522 -0.0733 0.6795 0.7733
-0.250 0.3861 0.01100 0.00519 -0.0716 0.6635 0.8122
0.000 0.4117 0.01097 0.00517 -0.0704 0.6464 0.8524
0.250 0.4470 0.01102 0.00518 -0.0711 0.6265 0.8924
0.500 0.4949 0.01121 0.00523 -0.0746 0.6036 0.9245
0.750 0.5429 0.01146 0.00530 -0.0783 0.5785 0.9502
1.000 0.5903 0.01174 0.00537 -0.0821 0.5489 0.9691
1.250 0.6364 0.01204 0.00544 -0.0858 0.5161 0.9866
1.500 0.6813 0.01236 0.00550 -0.0895 0.4844 1.0000
1.750 0.6887 0.01253 0.00550 -0.0860 0.4649 1.0000
2.000 0.7011 0.01276 0.00556 -0.0831 0.4475 1.0000
2.250 0.7164 0.01303 0.00567 -0.0808 0.4325 1.0000
2.500 0.7334 0.01334 0.00579 -0.0787 0.4203 1.0000
2.750 0.7523 0.01360 0.00596 -0.0770 0.4088 1.0000
3.000 0.7718 0.01391 0.00614 -0.0753 0.3994 1.0000
3.250 0.7918 0.01420 0.00633 -0.0738 0.3904 1.0000
3.500 0.8130 0.01454 0.00655 -0.0725 0.3830 1.0000
3.750 0.8341 0.01482 0.00679 -0.0712 0.3755 1.0000
4.000 0.8568 0.01524 0.00704 -0.0703 0.3690 1.0000
4.250 0.8785 0.01552 0.00732 -0.0690 0.3628 1.0000
4.500 0.9004 0.01583 0.00759 -0.0679 0.3565 1.0000
4.750 0.9258 0.01633 0.00792 -0.0676 0.3508 1.0000
5.000 0.9468 0.01659 0.00824 -0.0662 0.3456 1.0000
5.250 0.9691 0.01692 0.00855 -0.0652 0.3401 1.0000
5.500 0.9938 0.01737 0.00889 -0.0647 0.3348 1.0000
5.750 1.0165 0.01777 0.00930 -0.0638 0.3299 1.0000
6.000 1.0380 0.01810 0.00965 -0.0627 0.3248 1.0000
6.250 1.0612 0.01848 0.01000 -0.0619 0.3200 1.0000
6.500 1.0885 0.01909 0.01050 -0.0620 0.3150 1.0000
6.750 1.1068 0.01938 0.01089 -0.0603 0.3104 1.0000
7.000 1.1277 0.01973 0.01127 -0.0591 0.3054 1.0000
7.250 1.1513 0.02017 0.01166 -0.0585 0.3009 1.0000
7.500 1.1764 0.02078 0.01223 -0.0582 0.2964 1.0000
7.750 1.1938 0.02112 0.01268 -0.0564 0.2919 1.0000
8.000 1.2139 0.02150 0.01309 -0.0552 0.2872 1.0000
8.250 1.2372 0.02196 0.01348 -0.0545 0.2828 1.0000
8.500 1.2587 0.02254 0.01409 -0.0537 0.2784 1.0000
8.750 1.2743 0.02292 0.01459 -0.0517 0.2741 1.0000
9.000 1.2933 0.02333 0.01503 -0.0503 0.2698 1.0000
9.250 1.3158 0.02380 0.01544 -0.0496 0.2658 1.0000
9.500 1.3353 0.02440 0.01609 -0.0485 0.2617 1.0000
9.750 1.3459 0.02477 0.01660 -0.0457 0.2573 1.0000
10.000 1.3590 0.02510 0.01695 -0.0433 0.2530 1.0000
10.250 1.3774 0.02548 0.01727 -0.0419 0.2490 1.0000
10.500 1.3896 0.02603 0.01790 -0.0396 0.2449 1.0000
10.750 1.3983 0.02652 0.01851 -0.0367 0.2410 1.0000
11.000 1.4110 0.02697 0.01901 -0.0346 0.2372 1.0000
11.250 1.4272 0.02740 0.01942 -0.0331 0.2337 1.0000
11.500 1.4440 0.02807 0.02010 -0.0318 0.2301 1.0000
11.750 1.4491 0.02873 0.02093 -0.0288 0.2265 1.0000
12.000 1.4587 0.02933 0.02162 -0.0266 0.2229 1.0000
12.250 1.4704 0.02983 0.02212 -0.0247 0.2193 1.0000
12.500 1.4896 0.03046 0.02268 -0.0240 0.2156 1.0000
12.750 1.4897 0.03139 0.02382 -0.0209 0.2124 1.0000
13.000 1.4952 0.03225 0.02480 -0.0187 0.2087 1.0000
13.250 1.5046 0.03302 0.02561 -0.0170 0.2054 1.0000
13.500 1.5194 0.03372 0.02628 -0.0159 0.2023 1.0000
13.750 1.5263 0.03485 0.02752 -0.0143 0.1992 1.0000
14.000 1.5274 0.03617 0.02901 -0.0122 0.1960 1.0000
14.250 1.5319 0.03736 0.03030 -0.0106 0.1926 1.0000
14.500 1.5397 0.03839 0.03135 -0.0093 0.1894 1.0000
14.750 1.5520 0.03939 0.03232 -0.0084 0.1859 1.0000
15.000 1.5469 0.04137 0.03453 -0.0067 0.1829 1.0000
15.250 1.5462 0.04316 0.03645 -0.0055 0.1794 1.0000
15.500 1.5496 0.04470 0.03803 -0.0045 0.1760 1.0000
15.750 1.5621 0.04574 0.03899 -0.0039 0.1722 1.0000
16.000 1.5507 0.04865 0.04216 -0.0029 0.1692 1.0000
16.250 1.5456 0.05123 0.04488 -0.0023 0.1655 1.0000
16.500 1.5458 0.05339 0.04709 -0.0020 0.1619 1.0000
16.750 1.5493 0.05535 0.04904 -0.0017 0.1579 1.0000
17.000 1.5342 0.05941 0.05333 -0.0019 0.1542 1.0000
17.250 1.5268 0.06277 0.05679 -0.0023 0.1500 1.0000
17.500 1.5315 0.06473 0.05864 -0.0023 0.1453 1.0000
17.750 1.5085 0.07038 0.06458 -0.0037 0.1413 1.0000
18.000 1.4959 0.07485 0.06914 -0.0050 0.1366 1.0000
18.250 1.4922 0.07811 0.07237 -0.0057 0.1318 1.0000
18.500 1.4672 0.08472 0.07919 -0.0080 0.1272 1.0000
18.750 1.4599 0.08876 0.08322 -0.0094 0.1228 1.0000
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Polar data table (+)
Polar graphs
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