GOE 479 AIRFOIL (goe479-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 479 AIRFOIL (goe479-il) Reynolds number: 200,000 Max Cl/Cd: 72.45 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe479-il-200000-n5.txt Download as CSV file: xf-goe479-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 479 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3826 0.08854 0.08478 -0.0441 1.0000 0.0336
-9.500 -0.3954 0.08461 0.08091 -0.0442 1.0000 0.0336
-9.000 -0.5331 0.03844 0.03360 -0.0827 0.9736 0.0350
-8.750 -0.5113 0.03667 0.03174 -0.0837 0.9680 0.0355
-8.500 -0.4881 0.03455 0.02941 -0.0852 0.9627 0.0361
-8.250 -0.4612 0.03219 0.02678 -0.0873 0.9592 0.0368
-8.000 -0.4426 0.03024 0.02458 -0.0872 0.9515 0.0375
-7.500 -0.3904 0.02567 0.01912 -0.0894 0.9427 0.0399
-7.250 -0.3676 0.02399 0.01704 -0.0890 0.9352 0.0406
-7.000 -0.3373 0.02259 0.01548 -0.0901 0.9309 0.0413
-6.750 -0.3088 0.02174 0.01455 -0.0905 0.9255 0.0421
-6.500 -0.2820 0.02099 0.01371 -0.0905 0.9183 0.0431
-6.250 -0.2500 0.02010 0.01265 -0.0915 0.9136 0.0444
-6.000 -0.2240 0.01926 0.01166 -0.0912 0.9053 0.0454
-5.750 -0.1939 0.01842 0.01064 -0.0916 0.8987 0.0464
-5.500 -0.1651 0.01771 0.00978 -0.0917 0.8912 0.0473
-5.250 -0.1367 0.01694 0.00899 -0.0918 0.8828 0.0485
-5.000 -0.1085 0.01641 0.00845 -0.0918 0.8732 0.0500
-4.750 -0.0777 0.01586 0.00783 -0.0922 0.8633 0.0518
-4.500 -0.0506 0.01536 0.00724 -0.0919 0.8494 0.0534
-4.250 -0.0231 0.01490 0.00667 -0.0915 0.8355 0.0550
-4.000 0.0038 0.01437 0.00612 -0.0912 0.8228 0.0568
-3.750 0.0315 0.01400 0.00571 -0.0910 0.8111 0.0592
-3.500 0.0587 0.01370 0.00534 -0.0907 0.7988 0.0624
-3.250 0.0851 0.01339 0.00496 -0.0903 0.7863 0.0658
-3.000 0.1117 0.01310 0.00465 -0.0898 0.7745 0.0699
-2.750 0.1388 0.01290 0.00434 -0.0895 0.7633 0.0749
-2.500 0.1647 0.01265 0.00410 -0.0889 0.7516 0.0828
-2.250 0.1908 0.01244 0.00390 -0.0885 0.7408 0.0944
-1.750 0.2428 0.01208 0.00362 -0.0875 0.7204 0.1425
-1.500 0.2687 0.01192 0.00352 -0.0870 0.7108 0.1744
-1.250 0.2942 0.01178 0.00345 -0.0865 0.7010 0.2098
-1.000 0.3197 0.01163 0.00341 -0.0859 0.6921 0.2518
-0.750 0.3448 0.01147 0.00337 -0.0853 0.6831 0.3021
-0.500 0.3688 0.01121 0.00335 -0.0845 0.6741 0.3776
-0.250 0.3888 0.01070 0.00339 -0.0829 0.6652 0.5488
0.000 0.4085 0.01007 0.00352 -0.0806 0.6569 0.7767
0.250 0.4920 0.00995 0.00357 -0.0916 0.6469 0.9656
0.500 0.5368 0.01003 0.00356 -0.0951 0.6367 0.9922
0.750 0.5686 0.01015 0.00356 -0.0959 0.6276 1.0000
1.000 0.5917 0.01026 0.00359 -0.0949 0.6178 1.0000
1.250 0.6149 0.01038 0.00363 -0.0938 0.6082 1.0000
1.500 0.6377 0.01050 0.00366 -0.0927 0.5966 1.0000
1.750 0.6601 0.01063 0.00371 -0.0915 0.5827 1.0000
2.000 0.6825 0.01076 0.00376 -0.0902 0.5687 1.0000
2.250 0.7052 0.01090 0.00383 -0.0891 0.5562 1.0000
2.500 0.7279 0.01105 0.00390 -0.0879 0.5445 1.0000
2.750 0.7508 0.01120 0.00401 -0.0868 0.5323 1.0000
3.000 0.7736 0.01136 0.00412 -0.0857 0.5202 1.0000
3.250 0.7962 0.01153 0.00423 -0.0846 0.5084 1.0000
3.750 0.8412 0.01191 0.00451 -0.0823 0.4844 1.0000
4.000 0.8637 0.01212 0.00467 -0.0812 0.4731 1.0000
4.250 0.8859 0.01235 0.00485 -0.0800 0.4619 1.0000
4.500 0.9079 0.01259 0.00504 -0.0788 0.4498 1.0000
4.750 0.9296 0.01284 0.00525 -0.0776 0.4366 1.0000
5.000 0.9505 0.01312 0.00548 -0.0762 0.4210 1.0000
5.250 0.9711 0.01342 0.00571 -0.0748 0.4054 1.0000
5.500 0.9915 0.01372 0.00596 -0.0734 0.3895 1.0000
5.750 1.0118 0.01402 0.00623 -0.0720 0.3732 1.0000
6.000 1.0318 0.01434 0.00650 -0.0705 0.3566 1.0000
6.250 1.0512 0.01467 0.00679 -0.0690 0.3386 1.0000
6.500 1.0702 0.01503 0.00711 -0.0674 0.3212 1.0000
6.750 1.0882 0.01543 0.00745 -0.0657 0.3026 1.0000
7.000 1.1049 0.01588 0.00782 -0.0638 0.2814 1.0000
7.250 1.1198 0.01641 0.00825 -0.0616 0.2592 1.0000
7.500 1.1343 0.01696 0.00872 -0.0595 0.2407 1.0000
7.750 1.1483 0.01750 0.00921 -0.0572 0.2247 1.0000
8.000 1.1606 0.01808 0.00972 -0.0546 0.2082 1.0000
8.250 1.1726 0.01869 0.01028 -0.0521 0.1896 1.0000
8.500 1.1838 0.01937 0.01090 -0.0495 0.1689 1.0000
8.750 1.1918 0.02024 0.01163 -0.0467 0.1409 1.0000
9.000 1.1939 0.02150 0.01263 -0.0432 0.1009 1.0000
9.250 1.1938 0.02297 0.01385 -0.0397 0.0705 1.0000
9.500 1.2007 0.02407 0.01491 -0.0371 0.0625 1.0000
9.750 1.2083 0.02516 0.01603 -0.0348 0.0579 1.0000
10.000 1.2170 0.02622 0.01713 -0.0327 0.0551 1.0000
10.250 1.2260 0.02728 0.01828 -0.0308 0.0532 1.0000
10.500 1.2336 0.02848 0.01955 -0.0289 0.0516 1.0000
10.750 1.2398 0.02982 0.02097 -0.0270 0.0503 1.0000
11.000 1.2443 0.03135 0.02258 -0.0252 0.0492 1.0000
11.250 1.2462 0.03315 0.02444 -0.0235 0.0482 1.0000
11.500 1.2524 0.03470 0.02610 -0.0221 0.0474 1.0000
11.750 1.2574 0.03641 0.02791 -0.0209 0.0466 1.0000
12.000 1.2615 0.03828 0.02988 -0.0198 0.0458 1.0000
12.250 1.2653 0.04023 0.03192 -0.0189 0.0449 1.0000
12.500 1.2678 0.04238 0.03417 -0.0180 0.0442 1.0000
12.750 1.2698 0.04465 0.03652 -0.0173 0.0435 1.0000
13.000 1.2716 0.04699 0.03893 -0.0167 0.0429 1.0000
13.250 1.2729 0.04944 0.04146 -0.0162 0.0423 1.0000
13.500 1.2735 0.05202 0.04409 -0.0158 0.0417 1.0000
13.750 1.2737 0.05466 0.04676 -0.0154 0.0411 1.0000
14.000 1.2769 0.05705 0.04923 -0.0150 0.0405 1.0000
14.250 1.2813 0.05938 0.05168 -0.0149 0.0399 1.0000
14.500 1.2852 0.06179 0.05420 -0.0148 0.0393 1.0000
14.750 1.2891 0.06424 0.05675 -0.0147 0.0387 1.0000
15.000 1.2931 0.06672 0.05932 -0.0147 0.0381 1.0000
15.250 1.2968 0.06927 0.06196 -0.0148 0.0374 1.0000
15.500 1.3003 0.07186 0.06463 -0.0150 0.0368 1.0000
15.750 1.3035 0.07452 0.06736 -0.0152 0.0361 1.0000
16.000 1.3073 0.07712 0.07001 -0.0155 0.0355 1.0000
16.250 1.3124 0.07947 0.07238 -0.0155 0.0349 1.0000
16.500 1.3171 0.08194 0.07491 -0.0156 0.0342 1.0000
16.750 1.3182 0.08512 0.07826 -0.0164 0.0337 1.0000
17.000 1.3185 0.08849 0.08178 -0.0173 0.0331 1.0000
17.250 1.3184 0.09194 0.08539 -0.0183 0.0325 1.0000
17.500 1.3183 0.09541 0.08900 -0.0194 0.0319 1.0000
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Polar data table (+)
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