GOE 652 AIRFOIL (goe652-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 652 AIRFOIL (goe652-il) Reynolds number: 200,000 Max Cl/Cd: 77.96 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe652-il-200000-n5.txt Download as CSV file: xf-goe652-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 652 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
------ -------- --------- --------- -------- -------- --------
-10.000 0.2722 0.09530 0.09019 -0.1473 0.8589 0.0602
-9.750 0.2847 0.09277 0.08762 -0.1492 0.8517 0.0604
-9.500 0.2986 0.09019 0.08497 -0.1515 0.8456 0.0610
-9.250 0.3053 0.08787 0.08264 -0.1522 0.8383 0.0615
-9.000 0.3132 0.08540 0.08014 -0.1533 0.8313 0.0616
-8.750 0.3217 0.08269 0.07737 -0.1549 0.8251 0.0618
-8.500 0.3273 0.08008 0.07473 -0.1559 0.8190 0.0620
-8.250 0.3295 0.07730 0.07194 -0.1565 0.8124 0.0624
-8.000 0.3203 0.07252 0.06711 -0.1585 0.8060 0.0635
-7.750 0.3394 0.07178 0.06634 -0.1589 0.8011 0.0641
-7.500 0.3495 0.07053 0.06511 -0.1586 0.7952 0.0646
-6.500 0.1697 0.03670 0.03083 -0.1788 0.7628 0.0764
-6.250 0.1954 0.03573 0.02984 -0.1810 0.7583 0.0776
-6.000 0.2230 0.03252 0.02652 -0.1889 0.7535 0.0797
-5.750 0.2650 0.02829 0.02207 -0.2017 0.7480 0.0828
-5.500 0.2997 0.02720 0.02099 -0.2056 0.7431 0.0848
-5.250 0.3544 0.02435 0.01793 -0.2170 0.7388 0.0891
-5.000 0.4017 0.02284 0.01633 -0.2239 0.7347 0.0926
-4.750 0.4555 0.02067 0.01398 -0.2333 0.7286 0.0978
-4.500 0.4979 0.01959 0.01286 -0.2382 0.7216 0.1017
-4.250 0.5433 0.01847 0.01154 -0.2435 0.7157 0.1070
-4.000 0.5813 0.01792 0.01091 -0.2463 0.7104 0.1118
-3.750 0.6167 0.01746 0.01039 -0.2485 0.7044 0.1168
-3.500 0.6507 0.01715 0.01002 -0.2500 0.6985 0.1217
-3.250 0.6852 0.01684 0.00959 -0.2515 0.6927 0.1267
-3.000 0.7167 0.01667 0.00939 -0.2523 0.6860 0.1317
-2.750 0.7486 0.01647 0.00912 -0.2531 0.6790 0.1370
-2.500 0.7797 0.01639 0.00900 -0.2536 0.6735 0.1419
-2.250 0.8118 0.01625 0.00874 -0.2544 0.6684 0.1478
-2.000 0.8405 0.01627 0.00881 -0.2544 0.6617 0.1525
-1.750 0.8713 0.01618 0.00859 -0.2548 0.6548 0.1588
-1.500 0.9009 0.01621 0.00859 -0.2549 0.6487 0.1633
-1.250 0.9291 0.01622 0.00859 -0.2547 0.6407 0.1685
-1.000 0.9589 0.01616 0.00842 -0.2549 0.6329 0.1737
-0.750 0.9872 0.01623 0.00848 -0.2547 0.6263 0.1778
-0.500 1.0155 0.01627 0.00851 -0.2546 0.6194 0.1827
-0.250 1.0449 0.01626 0.00838 -0.2547 0.6129 0.1878
0.000 1.0731 0.01634 0.00846 -0.2544 0.6070 0.1917
0.250 1.1004 0.01642 0.00856 -0.2541 0.6002 0.1963
0.500 1.1287 0.01647 0.00853 -0.2539 0.5933 0.2014
0.750 1.1569 0.01654 0.00852 -0.2537 0.5871 0.2057
1.000 1.1835 0.01665 0.00869 -0.2533 0.5801 0.2097
1.250 1.2103 0.01677 0.00879 -0.2528 0.5727 0.2144
1.500 1.2377 0.01689 0.00878 -0.2524 0.5657 0.2194
1.750 1.2639 0.01699 0.00891 -0.2519 0.5577 0.2236
2.000 1.2893 0.01716 0.00907 -0.2512 0.5495 0.2277
2.250 1.3148 0.01734 0.00922 -0.2505 0.5417 0.2324
2.500 1.3400 0.01751 0.00936 -0.2498 0.5331 0.2373
2.750 1.3650 0.01770 0.00945 -0.2491 0.5250 0.2417
3.000 1.3891 0.01789 0.00970 -0.2482 0.5162 0.2458
3.250 1.4118 0.01815 0.00993 -0.2470 0.5064 0.2503
3.500 1.4344 0.01840 0.01016 -0.2458 0.4960 0.2550
3.750 1.4553 0.01871 0.01037 -0.2444 0.4845 0.2597
4.000 1.4762 0.01899 0.01065 -0.2430 0.4724 0.2641
4.250 1.4947 0.01936 0.01100 -0.2412 0.4605 0.2683
4.500 1.5121 0.01973 0.01135 -0.2392 0.4479 0.2727
4.750 1.5275 0.02014 0.01172 -0.2368 0.4360 0.2774
5.250 1.5553 0.02117 0.01264 -0.2319 0.4110 0.2867
5.500 1.5682 0.02180 0.01323 -0.2293 0.4000 0.2910
5.750 1.5814 0.02246 0.01385 -0.2269 0.3900 0.2958
6.000 1.5953 0.02314 0.01449 -0.2247 0.3824 0.3011
6.250 1.6104 0.02381 0.01514 -0.2228 0.3752 0.3066
6.500 1.6239 0.02458 0.01591 -0.2206 0.3687 0.3115
6.750 1.6387 0.02534 0.01666 -0.2187 0.3633 0.3172
7.000 1.6547 0.02605 0.01740 -0.2170 0.3578 0.3234
7.250 1.6694 0.02688 0.01820 -0.2152 0.3525 0.3290
7.500 1.6832 0.02778 0.01910 -0.2133 0.3476 0.3344
7.750 1.6992 0.02858 0.01993 -0.2118 0.3434 0.3411
8.000 1.7156 0.02937 0.02076 -0.2103 0.3393 0.3483
8.250 1.7312 0.03023 0.02166 -0.2088 0.3352 0.3540
8.500 1.7460 0.03116 0.02261 -0.2072 0.3312 0.3601
8.750 1.7609 0.03213 0.02356 -0.2057 0.3278 0.3672
9.000 1.7768 0.03305 0.02451 -0.2043 0.3246 0.3740
9.250 1.7925 0.03394 0.02551 -0.2029 0.3212 0.3810
9.500 1.8073 0.03492 0.02655 -0.2015 0.3175 0.3886
9.750 1.8211 0.03599 0.02766 -0.2000 0.3137 0.3951
10.000 1.8342 0.03713 0.02884 -0.1985 0.3100 0.4021
10.250 1.8482 0.03826 0.02994 -0.1970 0.3067 0.4103
10.500 1.8618 0.03937 0.03116 -0.1956 0.3034 0.4177
10.750 1.8740 0.04059 0.03250 -0.1942 0.2996 0.4257
11.000 1.8851 0.04191 0.03391 -0.1927 0.2952 0.4340
11.250 1.8946 0.04339 0.03543 -0.1911 0.2907 0.4421
11.500 1.9041 0.04491 0.03693 -0.1896 0.2864 0.4514
11.750 1.9135 0.04644 0.03862 -0.1881 0.2818 0.4600
12.000 1.9216 0.04813 0.04042 -0.1867 0.2765 0.4702
12.250 1.9280 0.05000 0.04234 -0.1852 0.2712 0.4806
12.500 1.9348 0.05192 0.04430 -0.1838 0.2664 0.4930
12.750 1.9424 0.05381 0.04635 -0.1826 0.2606 0.5069
13.000 1.9471 0.05602 0.04864 -0.1813 0.2546 0.5223
13.250 1.9517 0.05831 0.05101 -0.1801 0.2491 0.5428
13.500 1.9573 0.06058 0.05344 -0.1791 0.2423 0.5737
13.750 1.9598 0.06323 0.05620 -0.1781 0.2359 0.6286
14.000 1.9628 0.06561 0.05885 -0.1771 0.2294 1.0000
14.250 1.9640 0.06859 0.06186 -0.1762 0.2223 1.0000
14.500 1.9651 0.07164 0.06494 -0.1754 0.2156 1.0000
14.750 1.9645 0.07499 0.06831 -0.1747 0.2086 1.0000
15.000 1.9629 0.07851 0.07185 -0.1741 0.2024 1.0000
15.250 1.9622 0.08200 0.07537 -0.1737 0.1965 1.0000
15.500 1.9586 0.08590 0.07927 -0.1733 0.1913 1.0000
15.750 1.9589 0.08933 0.08275 -0.1730 0.1868 1.0000
16.000 1.9577 0.09299 0.08646 -0.1728 0.1824 1.0000
16.250 1.9554 0.09683 0.09030 -0.1728 0.1783 1.0000
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