GOE 438 AIRFOIL (goe438-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 438 AIRFOIL (goe438-il) Reynolds number: 500,000 Max Cl/Cd: 90.44 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe438-il-500000-n5.txt Download as CSV file: xf-goe438-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 438 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.4508 0.12314 0.12058 -0.0288 1.0000 0.0157
-13.000 -0.4451 0.12046 0.11791 -0.0297 1.0000 0.0161
-11.500 -0.8291 0.03202 0.02888 -0.0761 0.9940 0.0263
-10.750 -0.7622 0.02447 0.02046 -0.0803 0.9839 0.0312
-10.500 -0.7295 0.02541 0.02151 -0.0806 0.9809 0.0317
-10.250 -0.6957 0.02622 0.02241 -0.0812 0.9783 0.0322
-10.000 -0.6611 0.02684 0.02308 -0.0822 0.9760 0.0328
-9.750 -0.6335 0.02518 0.02117 -0.0836 0.9733 0.0340
-9.500 -0.6166 0.02206 0.01750 -0.0837 0.9671 0.0357
-9.250 -0.5873 0.02130 0.01662 -0.0845 0.9635 0.0364
-9.000 -0.5532 0.02152 0.01689 -0.0857 0.9610 0.0369
-8.750 -0.5221 0.02171 0.01710 -0.0863 0.9564 0.0374
-8.500 -0.4919 0.02172 0.01711 -0.0869 0.9504 0.0380
-8.250 -0.4585 0.02177 0.01714 -0.0880 0.9463 0.0388
-8.000 -0.4312 0.02136 0.01664 -0.0882 0.9398 0.0399
-7.750 -0.4041 0.02041 0.01547 -0.0885 0.9332 0.0412
-7.500 -0.3780 0.01922 0.01404 -0.0886 0.9261 0.0418
-7.250 -0.3517 0.01832 0.01294 -0.0886 0.9174 0.0421
-7.000 -0.3253 0.01744 0.01188 -0.0885 0.9089 0.0424
-6.750 -0.2996 0.01635 0.01065 -0.0884 0.8998 0.0431
-6.500 -0.2732 0.01581 0.01003 -0.0882 0.8899 0.0435
-6.250 -0.2461 0.01535 0.00948 -0.0881 0.8803 0.0440
-6.000 -0.2197 0.01487 0.00889 -0.0878 0.8701 0.0443
-5.750 -0.1936 0.01442 0.00835 -0.0874 0.8591 0.0447
-5.500 -0.1675 0.01399 0.00780 -0.0869 0.8466 0.0451
-5.250 -0.1417 0.01361 0.00729 -0.0864 0.8332 0.0456
-4.750 -0.0906 0.01287 0.00634 -0.0853 0.8072 0.0465
-4.500 -0.0650 0.01253 0.00591 -0.0847 0.7940 0.0471
-4.250 -0.0394 0.01223 0.00550 -0.0841 0.7808 0.0476
-4.000 -0.0137 0.01196 0.00515 -0.0835 0.7674 0.0482
-3.750 0.0119 0.01174 0.00485 -0.0829 0.7520 0.0489
-3.500 0.0375 0.01152 0.00453 -0.0822 0.7352 0.0494
-3.250 0.0626 0.01132 0.00424 -0.0815 0.7147 0.0498
-2.750 0.1121 0.01103 0.00371 -0.0799 0.6712 0.0505
-2.500 0.1361 0.01072 0.00331 -0.0791 0.6539 0.0513
-2.250 0.1608 0.01054 0.00306 -0.0783 0.6389 0.0523
-2.000 0.1861 0.01043 0.00289 -0.0777 0.6261 0.0531
-1.750 0.2117 0.01034 0.00275 -0.0771 0.6142 0.0539
-1.500 0.2376 0.01026 0.00263 -0.0766 0.6038 0.0549
-1.250 0.2634 0.01020 0.00252 -0.0761 0.5932 0.0559
-1.000 0.2895 0.01015 0.00243 -0.0756 0.5822 0.0573
-0.750 0.3157 0.01009 0.00235 -0.0751 0.5721 0.0585
-0.500 0.3416 0.01006 0.00227 -0.0746 0.5609 0.0595
-0.250 0.3676 0.01004 0.00220 -0.0741 0.5484 0.0603
0.000 0.3936 0.00999 0.00212 -0.0736 0.5359 0.0615
0.250 0.4193 0.00994 0.00204 -0.0731 0.5223 0.0639
0.500 0.4449 0.00994 0.00200 -0.0725 0.5066 0.0662
0.750 0.4703 0.00998 0.00199 -0.0719 0.4897 0.0689
1.000 0.4958 0.01003 0.00198 -0.0714 0.4739 0.0719
1.250 0.5210 0.01009 0.00199 -0.0708 0.4577 0.0771
1.750 0.5703 0.01007 0.00209 -0.0695 0.4277 0.1529
2.000 0.5788 0.00859 0.00226 -0.0661 0.4172 0.7344
2.500 0.7015 0.00861 0.00263 -0.0804 0.3873 1.0000
2.750 0.7239 0.00879 0.00272 -0.0792 0.3744 1.0000
3.000 0.7464 0.00897 0.00283 -0.0781 0.3613 1.0000
3.250 0.7689 0.00915 0.00293 -0.0770 0.3488 1.0000
3.500 0.7915 0.00934 0.00305 -0.0759 0.3386 1.0000
3.750 0.8145 0.00951 0.00317 -0.0749 0.3293 1.0000
4.000 0.8375 0.00969 0.00330 -0.0738 0.3202 1.0000
4.250 0.8600 0.00989 0.00345 -0.0728 0.3104 1.0000
4.500 0.8831 0.01007 0.00359 -0.0718 0.3002 1.0000
4.750 0.9056 0.01028 0.00375 -0.0707 0.2901 1.0000
5.000 0.9286 0.01048 0.00391 -0.0697 0.2821 1.0000
5.250 0.9515 0.01067 0.00408 -0.0687 0.2743 1.0000
5.500 0.9741 0.01089 0.00426 -0.0677 0.2648 1.0000
5.750 0.9971 0.01109 0.00445 -0.0668 0.2575 1.0000
6.000 1.0197 0.01132 0.00465 -0.0658 0.2494 1.0000
6.250 1.0426 0.01153 0.00485 -0.0648 0.2419 1.0000
6.500 1.0646 0.01179 0.00507 -0.0638 0.2329 1.0000
6.750 1.0871 0.01202 0.00530 -0.0628 0.2242 1.0000
7.000 1.1086 0.01231 0.00556 -0.0617 0.2133 1.0000
7.250 1.1295 0.01264 0.00584 -0.0605 0.2002 1.0000
7.500 1.1493 0.01304 0.00616 -0.0591 0.1826 1.0000
7.750 1.1679 0.01350 0.00653 -0.0576 0.1630 1.0000
8.000 1.1853 0.01402 0.00695 -0.0559 0.1427 1.0000
8.250 1.2019 0.01459 0.00742 -0.0541 0.1247 1.0000
8.500 1.2184 0.01513 0.00790 -0.0523 0.1104 1.0000
8.750 1.2342 0.01566 0.00839 -0.0503 0.0964 1.0000
9.000 1.2412 0.01657 0.00911 -0.0470 0.0673 1.0000
9.250 1.2541 0.01715 0.00966 -0.0445 0.0607 1.0000
9.500 1.2684 0.01767 0.01020 -0.0424 0.0575 1.0000
9.750 1.2821 0.01824 0.01078 -0.0403 0.0549 1.0000
10.000 1.2955 0.01883 0.01141 -0.0381 0.0525 1.0000
10.250 1.3093 0.01941 0.01204 -0.0362 0.0506 1.0000
10.500 1.3245 0.01992 0.01261 -0.0344 0.0496 1.0000
10.750 1.3389 0.02049 0.01324 -0.0327 0.0481 1.0000
11.000 1.3519 0.02115 0.01396 -0.0309 0.0464 1.0000
11.250 1.3637 0.02190 0.01477 -0.0290 0.0449 1.0000
11.500 1.3735 0.02279 0.01570 -0.0270 0.0432 1.0000
11.750 1.3832 0.02373 0.01669 -0.0251 0.0417 1.0000
12.000 1.3971 0.02442 0.01746 -0.0237 0.0403 1.0000
12.250 1.4088 0.02529 0.01840 -0.0222 0.0389 1.0000
12.500 1.4193 0.02627 0.01943 -0.0208 0.0369 1.0000
12.750 1.4274 0.02747 0.02067 -0.0193 0.0349 1.0000
13.000 1.4376 0.02856 0.02183 -0.0181 0.0328 1.0000
13.250 1.4456 0.02987 0.02316 -0.0168 0.0290 1.0000
13.500 1.4519 0.03137 0.02469 -0.0156 0.0249 1.0000
13.750 1.4551 0.03320 0.02653 -0.0145 0.0211 1.0000
14.000 1.4547 0.03546 0.02880 -0.0134 0.0178 1.0000
14.250 1.4539 0.03787 0.03129 -0.0126 0.0162 1.0000
14.500 1.4536 0.04038 0.03388 -0.0120 0.0151 1.0000
14.750 1.4524 0.04312 0.03671 -0.0117 0.0142 1.0000
15.000 1.4506 0.04604 0.03973 -0.0116 0.0137 1.0000
15.250 1.4459 0.04941 0.04320 -0.0118 0.0131 1.0000
15.500 1.4412 0.05289 0.04678 -0.0121 0.0127 1.0000
15.750 1.4363 0.05651 0.05051 -0.0127 0.0123 1.0000
16.000 1.4310 0.06030 0.05441 -0.0133 0.0120 1.0000
16.250 1.4245 0.06433 0.05856 -0.0142 0.0117 1.0000
16.500 1.4163 0.06872 0.06306 -0.0153 0.0114 1.0000
16.750 1.4087 0.07312 0.06758 -0.0166 0.0112 1.0000
17.000 1.3988 0.07799 0.07257 -0.0181 0.0110 1.0000
17.250 1.3877 0.08311 0.07779 -0.0197 0.0107 1.0000
17.500 1.3769 0.08831 0.08310 -0.0215 0.0105 1.0000
17.750 1.3663 0.09356 0.08846 -0.0234 0.0103 1.0000
18.000 1.3538 0.09919 0.09419 -0.0256 0.0102 1.0000
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