GOE 514 AIRFOIL (goe514-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 514 AIRFOIL (goe514-il) Reynolds number: 200,000 Max Cl/Cd: 57.19 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe514-il-200000.txt Download as CSV file: xf-goe514-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 514 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4372 0.07106 0.06775 -0.0854 0.9657 0.0389
-10.500 -0.5336 0.05603 0.05237 -0.0936 0.9501 0.0371
-10.250 -0.5703 0.04711 0.04270 -0.0945 0.9414 0.0369
-10.000 -0.5851 0.04405 0.03930 -0.0900 0.9297 0.0371
-9.750 -0.5732 0.04054 0.03531 -0.0900 0.9261 0.0377
-9.500 -0.5795 0.03866 0.03315 -0.0850 0.9150 0.0381
-9.250 -0.5605 0.03615 0.03015 -0.0846 0.9113 0.0390
-9.000 -0.5568 0.03466 0.02834 -0.0807 0.9020 0.0397
-8.750 -0.5327 0.03324 0.02694 -0.0806 0.8975 0.0410
-8.500 -0.5019 0.03224 0.02583 -0.0815 0.8948 0.0433
-8.250 -0.4925 0.03140 0.02477 -0.0782 0.8860 0.0448
-8.000 -0.4667 0.03002 0.02327 -0.0779 0.8811 0.0471
-7.750 -0.4299 0.02891 0.02209 -0.0795 0.8785 0.0501
-7.500 -0.4149 0.02812 0.02106 -0.0768 0.8699 0.0527
-7.250 -0.3856 0.02710 0.02013 -0.0770 0.8649 0.0568
-7.000 -0.3487 0.02591 0.01884 -0.0785 0.8624 0.0634
-6.750 -0.3103 0.02465 0.01752 -0.0802 0.8607 0.0727
-6.500 -0.3024 0.02425 0.01701 -0.0763 0.8495 0.0792
-6.250 -0.2659 0.02302 0.01576 -0.0776 0.8468 0.0909
-6.000 -0.2254 0.02205 0.01480 -0.0797 0.8451 0.1030
-5.750 -0.1906 0.02152 0.01432 -0.0806 0.8420 0.1137
-5.250 -0.1384 0.02096 0.01371 -0.0791 0.8301 0.1322
-5.000 -0.0964 0.02049 0.01315 -0.0813 0.8286 0.1450
-4.750 -0.0883 0.02048 0.01320 -0.0773 0.8179 0.1517
-4.500 -0.0495 0.01980 0.01248 -0.0789 0.8150 0.1650
-4.250 -0.0068 0.01913 0.01179 -0.0813 0.8130 0.1799
-4.000 0.0074 0.01905 0.01166 -0.0782 0.8036 0.1897
-3.750 0.0442 0.01860 0.01125 -0.0795 0.7993 0.2007
-3.500 0.0912 0.01806 0.01061 -0.0828 0.7962 0.2119
-3.250 0.1052 0.01801 0.01057 -0.0797 0.7859 0.2175
-3.000 0.1501 0.01753 0.00991 -0.0826 0.7812 0.2261
-2.750 0.1757 0.01731 0.00973 -0.0819 0.7720 0.2313
-2.500 0.2199 0.01693 0.00924 -0.0847 0.7645 0.2387
-2.250 0.2463 0.01668 0.00888 -0.0842 0.7538 0.2439
-2.000 0.2965 0.01637 0.00854 -0.0884 0.7449 0.2505
-1.750 0.3204 0.01623 0.00829 -0.0874 0.7324 0.2557
-1.500 0.3483 0.01605 0.00798 -0.0871 0.7195 0.2608
-1.250 0.3800 0.01591 0.00781 -0.0877 0.7060 0.2660
-1.000 0.4086 0.01586 0.00764 -0.0876 0.6915 0.2730
-0.750 0.4339 0.01578 0.00743 -0.0869 0.6762 0.2793
-0.500 0.4537 0.01573 0.00734 -0.0851 0.6601 0.2847
-0.250 0.4689 0.01570 0.00721 -0.0823 0.6427 0.2905
0.000 0.4812 0.01566 0.00705 -0.0789 0.6240 0.2964
0.250 0.4920 0.01564 0.00700 -0.0752 0.6043 0.3018
0.500 0.5030 0.01571 0.00695 -0.0716 0.5844 0.3094
0.750 0.5159 0.01577 0.00691 -0.0685 0.5650 0.3166
1.000 0.5300 0.01590 0.00694 -0.0657 0.5475 0.3252
1.250 0.5455 0.01602 0.00696 -0.0633 0.5318 0.3341
1.500 0.5627 0.01619 0.00701 -0.0612 0.5184 0.3441
1.750 0.5811 0.01631 0.00706 -0.0594 0.5063 0.3528
2.000 0.5992 0.01649 0.00717 -0.0575 0.4955 0.3629
2.250 0.6203 0.01661 0.00723 -0.0563 0.4860 0.3725
2.500 0.6389 0.01675 0.00735 -0.0546 0.4769 0.3824
2.750 0.6630 0.01692 0.00744 -0.0540 0.4693 0.3937
3.000 0.6813 0.01701 0.00759 -0.0523 0.4620 0.4034
3.250 0.7055 0.01716 0.00768 -0.0518 0.4556 0.4155
3.500 0.7261 0.01729 0.00783 -0.0505 0.4498 0.4278
3.750 0.7439 0.01739 0.00799 -0.0487 0.4438 0.4425
4.000 0.7680 0.01745 0.00808 -0.0482 0.4384 0.4729
4.250 1.0851 0.01907 0.01066 -0.1096 0.4201 1.0000
4.500 1.1025 0.01936 0.01094 -0.1078 0.4163 1.0000
4.750 1.1135 0.01959 0.01119 -0.1047 0.4123 1.0000
5.000 1.1296 0.01985 0.01142 -0.1027 0.4083 1.0000
5.250 1.1519 0.02019 0.01167 -0.1019 0.4042 1.0000
5.500 1.1809 0.02065 0.01207 -0.1026 0.4002 1.0000
5.750 1.1887 0.02088 0.01236 -0.0989 0.3972 1.0000
6.000 1.2013 0.02115 0.01266 -0.0962 0.3938 1.0000
6.250 1.2191 0.02147 0.01297 -0.0945 0.3905 1.0000
6.500 1.2428 0.02183 0.01329 -0.0941 0.3873 1.0000
6.750 1.2820 0.02246 0.01382 -0.0969 0.3837 1.0000
7.000 1.2828 0.02268 0.01415 -0.0918 0.3810 1.0000
7.250 1.2895 0.02296 0.01451 -0.0880 0.3779 1.0000
7.500 1.3031 0.02329 0.01487 -0.0856 0.3748 1.0000
7.750 1.3217 0.02363 0.01520 -0.0842 0.3717 1.0000
8.000 1.3507 0.02407 0.01558 -0.0848 0.3686 1.0000
8.250 1.3690 0.02457 0.01611 -0.0835 0.3653 1.0000
8.500 1.3667 0.02484 0.01649 -0.0780 0.3622 1.0000
8.750 1.3736 0.02517 0.01689 -0.0745 0.3588 1.0000
9.000 1.3876 0.02550 0.01723 -0.0723 0.3555 1.0000
9.250 1.4101 0.02584 0.01753 -0.0717 0.3523 1.0000
9.500 1.4374 0.02639 0.01805 -0.0722 0.3490 1.0000
9.750 1.4321 0.02679 0.01861 -0.0665 0.3461 1.0000
10.000 1.4357 0.02721 0.01914 -0.0626 0.3427 1.0000
10.250 1.4465 0.02760 0.01957 -0.0601 0.3394 1.0000
10.500 1.4654 0.02794 0.01990 -0.0590 0.3364 1.0000
10.750 1.4996 0.02839 0.02028 -0.0606 0.3332 1.0000
11.000 1.4972 0.02903 0.02109 -0.0560 0.3307 1.0000
11.250 1.4955 0.02967 0.02188 -0.0516 0.3276 1.0000
11.500 1.5007 0.03020 0.02250 -0.0485 0.3241 1.0000
11.750 1.5133 0.03050 0.02280 -0.0465 0.3204 1.0000
12.000 1.5380 0.03073 0.02292 -0.0465 0.3160 1.0000
12.250 1.5275 0.03166 0.02407 -0.0412 0.3129 1.0000
12.500 1.5250 0.03245 0.02499 -0.0374 0.3091 1.0000
12.750 1.5316 0.03290 0.02546 -0.0349 0.3047 1.0000
13.000 1.5549 0.03305 0.02551 -0.0346 0.3005 1.0000
13.250 1.5472 0.03429 0.02694 -0.0306 0.2975 1.0000
13.500 1.5410 0.03548 0.02830 -0.0269 0.2934 1.0000
13.750 1.5456 0.03630 0.02918 -0.0247 0.2894 1.0000
14.000 1.5615 0.03660 0.02941 -0.0236 0.2851 1.0000
14.250 1.5531 0.03822 0.03121 -0.0203 0.2812 1.0000
14.500 1.5455 0.03987 0.03302 -0.0174 0.2767 1.0000
14.750 1.5479 0.04098 0.03416 -0.0155 0.2720 1.0000
15.000 1.5554 0.04197 0.03516 -0.0141 0.2676 1.0000
15.250 1.5429 0.04444 0.03784 -0.0116 0.2630 1.0000
15.500 1.5397 0.04634 0.03984 -0.0099 0.2581 1.0000
15.750 1.5464 0.04750 0.04096 -0.0089 0.2529 1.0000
16.000 1.5331 0.05063 0.04432 -0.0072 0.2482 1.0000
16.250 1.5264 0.05325 0.04702 -0.0060 0.2423 1.0000
16.500 1.5215 0.05581 0.04964 -0.0051 0.2362 1.0000
16.750 1.5089 0.05940 0.05340 -0.0043 0.2304 1.0000
17.000 1.5076 0.06180 0.05578 -0.0038 0.2246 1.0000
17.250 1.4907 0.06620 0.06039 -0.0034 0.2184 1.0000
17.500 1.4802 0.06991 0.06414 -0.0033 0.2114 1.0000
17.750 1.4663 0.07423 0.06858 -0.0033 0.2058 1.0000
18.000 1.4477 0.07924 0.07365 -0.0037 0.1979 1.0000
18.250 1.4323 0.08400 0.07851 -0.0042 0.1921 1.0000
18.500 1.4116 0.08957 0.08414 -0.0050 0.1844 1.0000
18.750 1.3962 0.09449 0.08914 -0.0058 0.1788 1.0000
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Polar data table (+)
Polar graphs
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