GOE 683 AIRFOIL (goe683-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 683 AIRFOIL (goe683-il) Reynolds number: 200,000 Max Cl/Cd: 59.26 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe683-il-200000-n5.txt Download as CSV file: xf-goe683-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 683 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.8015 0.08320 0.07779 -0.0730 1.0000 0.0525
-17.250 -0.8337 0.07519 0.06955 -0.0778 1.0000 0.0529
-17.000 -0.8573 0.06889 0.06303 -0.0813 1.0000 0.0533
-16.750 -0.8756 0.06364 0.05759 -0.0839 1.0000 0.0537
-16.500 -0.8927 0.05888 0.05260 -0.0860 1.0000 0.0542
-16.250 -0.9078 0.05470 0.04819 -0.0875 1.0000 0.0547
-16.000 -0.9062 0.05245 0.04591 -0.0876 1.0000 0.0551
-15.750 -0.9043 0.05035 0.04379 -0.0876 1.0000 0.0556
-15.500 -0.9035 0.04825 0.04164 -0.0875 1.0000 0.0561
-15.250 -0.9033 0.04615 0.03948 -0.0871 1.0000 0.0565
-15.000 -0.9032 0.04420 0.03746 -0.0864 1.0000 0.0570
-14.750 -0.9029 0.04238 0.03555 -0.0855 1.0000 0.0576
-14.500 -0.9023 0.04068 0.03376 -0.0843 1.0000 0.0582
-14.250 -0.9016 0.03911 0.03209 -0.0827 1.0000 0.0588
-14.000 -0.9012 0.03765 0.03051 -0.0809 1.0000 0.0596
-13.750 -0.9002 0.03633 0.02907 -0.0787 1.0000 0.0603
-13.500 -0.9002 0.03514 0.02772 -0.0762 1.0000 0.0610
-13.250 -0.8937 0.03413 0.02673 -0.0741 1.0000 0.0616
-13.000 -0.8886 0.03322 0.02584 -0.0717 1.0000 0.0623
-12.750 -0.8850 0.03240 0.02501 -0.0689 1.0000 0.0630
-12.500 -0.8617 0.03111 0.02371 -0.0696 0.9870 0.0640
-12.250 -0.8383 0.03001 0.02254 -0.0703 0.9691 0.0652
-12.000 -0.8107 0.02895 0.02136 -0.0717 0.9500 0.0664
-11.750 -0.7768 0.02795 0.02017 -0.0743 0.9340 0.0679
-11.500 -0.7368 0.02674 0.01897 -0.0780 0.9210 0.0694
-11.250 -0.6933 0.02566 0.01784 -0.0824 0.9073 0.0711
-11.000 -0.6489 0.02466 0.01673 -0.0869 0.8921 0.0730
-10.750 -0.6068 0.02381 0.01571 -0.0907 0.8755 0.0750
-10.500 -0.5722 0.02295 0.01476 -0.0932 0.8583 0.0768
-10.250 -0.5465 0.02222 0.01397 -0.0937 0.8411 0.0784
-10.000 -0.5258 0.02166 0.01331 -0.0931 0.8249 0.0800
-9.750 -0.5072 0.02118 0.01273 -0.0919 0.8098 0.0817
-9.500 -0.4889 0.02075 0.01217 -0.0905 0.7962 0.0834
-9.250 -0.4746 0.02030 0.01164 -0.0883 0.7827 0.0850
-9.000 -0.4620 0.01981 0.01112 -0.0859 0.7705 0.0870
-8.750 -0.4471 0.01941 0.01065 -0.0837 0.7594 0.0891
-8.500 -0.4322 0.01905 0.01022 -0.0814 0.7482 0.0914
-8.250 -0.4163 0.01870 0.00978 -0.0793 0.7382 0.0939
-8.000 -0.4020 0.01832 0.00940 -0.0769 0.7274 0.0970
-7.750 -0.3855 0.01799 0.00902 -0.0748 0.7183 0.1012
-7.500 -0.3692 0.01767 0.00870 -0.0727 0.7084 0.1061
-7.250 -0.3518 0.01737 0.00839 -0.0708 0.6998 0.1142
-7.000 -0.3341 0.01709 0.00814 -0.0689 0.6909 0.1253
-6.750 -0.3155 0.01687 0.00788 -0.0671 0.6821 0.1380
-6.500 -0.2966 0.01666 0.00766 -0.0654 0.6741 0.1500
-6.250 -0.2778 0.01645 0.00744 -0.0636 0.6659 0.1597
-6.000 -0.2577 0.01629 0.00721 -0.0620 0.6589 0.1691
-5.750 -0.2383 0.01611 0.00704 -0.0604 0.6510 0.1782
-5.500 -0.2182 0.01596 0.00684 -0.0588 0.6433 0.1864
-5.250 -0.1980 0.01581 0.00666 -0.0572 0.6362 0.1944
-5.000 -0.1774 0.01568 0.00650 -0.0558 0.6287 0.2025
-4.750 -0.1573 0.01554 0.00634 -0.0542 0.6221 0.2104
-4.500 -0.1361 0.01543 0.00620 -0.0528 0.6155 0.2191
-4.250 -0.1163 0.01529 0.00608 -0.0512 0.6083 0.2288
-4.000 -0.0951 0.01520 0.00593 -0.0497 0.6015 0.2371
-3.750 -0.0750 0.01507 0.00583 -0.0482 0.5945 0.2462
-3.500 -0.0541 0.01498 0.00572 -0.0467 0.5875 0.2562
-3.250 -0.0338 0.01487 0.00561 -0.0451 0.5814 0.2669
-3.000 -0.0132 0.01477 0.00553 -0.0436 0.5748 0.2790
-2.750 0.0074 0.01468 0.00545 -0.0421 0.5677 0.2931
-2.500 0.0268 0.01456 0.00535 -0.0404 0.5614 0.3086
-2.250 0.0462 0.01444 0.00529 -0.0386 0.5545 0.3261
-2.000 0.0651 0.01431 0.00523 -0.0368 0.5478 0.3464
-1.750 0.0833 0.01419 0.00516 -0.0348 0.5421 0.3716
-1.500 0.0998 0.01403 0.00515 -0.0325 0.5358 0.4038
-1.250 0.1147 0.01385 0.00513 -0.0298 0.5291 0.4453
-1.000 0.1294 0.01371 0.00509 -0.0270 0.5234 0.4876
-0.750 0.1442 0.01353 0.00510 -0.0242 0.5173 0.5323
-0.500 0.1606 0.01336 0.00511 -0.0218 0.5113 0.5791
-0.250 0.1829 0.01318 0.00511 -0.0205 0.5057 0.6326
0.000 0.2307 0.01300 0.00520 -0.0246 0.4989 0.7045
0.250 0.3543 0.01361 0.00603 -0.0439 0.4886 0.7842
0.500 0.4146 0.01419 0.00661 -0.0499 0.4820 0.8134
0.750 0.4510 0.01455 0.00695 -0.0512 0.4757 0.8342
1.000 0.4771 0.01487 0.00721 -0.0505 0.4702 0.8557
1.750 0.5550 0.01586 0.00810 -0.0486 0.4551 0.9019
2.000 0.5793 0.01616 0.00831 -0.0477 0.4502 0.9122
2.250 0.6114 0.01648 0.00859 -0.0485 0.4455 0.9205
2.500 0.6440 0.01680 0.00890 -0.0493 0.4404 0.9291
2.750 0.6708 0.01715 0.00922 -0.0490 0.4356 0.9394
3.000 0.7115 0.01741 0.00939 -0.0517 0.4309 0.9440
3.250 0.7439 0.01763 0.00959 -0.0527 0.4263 0.9498
3.500 0.7706 0.01783 0.00981 -0.0526 0.4219 0.9554
3.750 0.8054 0.01796 0.00991 -0.0542 0.4171 0.9587
4.000 0.8356 0.01815 0.01004 -0.0549 0.4128 0.9636
4.250 0.8659 0.01835 0.01023 -0.0556 0.4078 0.9690
4.500 0.9021 0.01843 0.01032 -0.0575 0.4018 0.9732
4.750 0.9301 0.01860 0.01045 -0.0578 0.3962 0.9780
5.000 0.9579 0.01877 0.01056 -0.0581 0.3924 0.9814
5.250 0.9896 0.01881 0.01066 -0.0593 0.3879 0.9841
5.500 1.0187 0.01890 0.01078 -0.0599 0.3835 0.9873
5.750 1.0460 0.01906 0.01093 -0.0602 0.3793 0.9907
6.000 1.0746 0.01919 0.01102 -0.0607 0.3755 0.9934
6.250 1.1057 0.01924 0.01112 -0.0618 0.3714 0.9964
6.500 1.1369 0.01932 0.01125 -0.0629 0.3673 0.9993
6.750 1.1561 0.01951 0.01147 -0.0616 0.3633 1.0000
7.000 1.1703 0.01977 0.01171 -0.0593 0.3597 1.0000
7.250 1.1843 0.02004 0.01196 -0.0570 0.3563 1.0000
7.500 1.1978 0.02030 0.01230 -0.0546 0.3528 1.0000
7.750 1.2102 0.02057 0.01263 -0.0520 0.3491 1.0000
8.000 1.2212 0.02086 0.01294 -0.0491 0.3454 1.0000
8.250 1.2313 0.02116 0.01324 -0.0462 0.3422 1.0000
8.500 1.2378 0.02146 0.01354 -0.0425 0.3386 1.0000
8.750 1.2418 0.02175 0.01392 -0.0384 0.3351 1.0000
9.000 1.2457 0.02208 0.01430 -0.0344 0.3314 1.0000
9.250 1.2503 0.02244 0.01470 -0.0306 0.3281 1.0000
9.500 1.2550 0.02284 0.01511 -0.0269 0.3249 1.0000
9.750 1.2602 0.02329 0.01556 -0.0234 0.3216 1.0000
10.000 1.2649 0.02379 0.01616 -0.0201 0.3179 1.0000
10.250 1.2702 0.02433 0.01678 -0.0169 0.3145 1.0000
10.500 1.2750 0.02493 0.01741 -0.0138 0.3110 1.0000
10.750 1.2795 0.02558 0.01807 -0.0108 0.3075 1.0000
11.000 1.2848 0.02627 0.01881 -0.0081 0.3042 1.0000
11.250 1.2887 0.02708 0.01971 -0.0053 0.3002 1.0000
11.500 1.2913 0.02797 0.02065 -0.0025 0.2955 1.0000
11.750 1.2942 0.02889 0.02158 0.0001 0.2913 1.0000
12.000 1.2963 0.02995 0.02270 0.0026 0.2865 1.0000
12.250 1.2983 0.03110 0.02393 0.0049 0.2818 1.0000
12.500 1.2998 0.03232 0.02518 0.0072 0.2770 1.0000
12.750 1.3012 0.03358 0.02646 0.0093 0.2723 1.0000
13.000 1.3020 0.03504 0.02802 0.0113 0.2673 1.0000
13.250 1.3017 0.03660 0.02964 0.0132 0.2621 1.0000
13.500 1.3003 0.03826 0.03128 0.0150 0.2568 1.0000
13.750 1.2991 0.04010 0.03324 0.0166 0.2513 1.0000
14.000 1.2951 0.04218 0.03535 0.0181 0.2447 1.0000
14.250 1.2921 0.04427 0.03749 0.0195 0.2391 1.0000
14.500 1.2880 0.04661 0.03991 0.0207 0.2326 1.0000
14.750 1.2809 0.04922 0.04251 0.0219 0.2256 1.0000
15.000 1.2753 0.05192 0.04530 0.0228 0.2183 1.0000
15.250 1.2650 0.05508 0.04846 0.0236 0.2101 1.0000
15.500 1.2565 0.05825 0.05170 0.0242 0.2015 1.0000
15.750 1.2447 0.06184 0.05530 0.0247 0.1926 1.0000
16.000 1.2326 0.06558 0.05906 0.0250 0.1834 1.0000
16.250 1.2204 0.06944 0.06294 0.0251 0.1741 1.0000
16.500 1.2072 0.07349 0.06699 0.0251 0.1660 1.0000
16.750 1.1961 0.07739 0.07090 0.0250 0.1586 1.0000
17.000 1.1856 0.08128 0.07479 0.0249 0.1531 1.0000
17.250 1.1774 0.08493 0.07845 0.0247 0.1479 1.0000
17.500 1.1705 0.08841 0.08193 0.0245 0.1438 1.0000
17.750 1.1664 0.09160 0.08514 0.0243 0.1403 1.0000
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