TRAINER60 (trainer60-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: TRAINER60 (trainer60-il) Reynolds number: 200,000 Max Cl/Cd: 51.65 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-trainer60-il-200000.txt Download as CSV file: xf-trainer60-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: TRAINER60
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
------ -------- --------- --------- -------- -------- --------
-19.750 -1.2099 0.13163 0.12645 0.0179 1.0000 0.0488
-19.500 -1.2307 0.12376 0.11834 0.0130 1.0000 0.0492
-19.250 -1.2469 0.11696 0.11132 0.0090 1.0000 0.0495
-19.000 -1.2615 0.11064 0.10478 0.0054 1.0000 0.0500
-18.750 -1.2740 0.10483 0.09874 0.0023 1.0000 0.0504
-18.500 -1.2851 0.09934 0.09302 -0.0006 1.0000 0.0507
-18.250 -1.2662 0.09898 0.09277 0.0009 1.0000 0.0517
-18.000 -1.2570 0.09694 0.09075 0.0006 1.0000 0.0526
-17.750 -1.2532 0.09398 0.08773 -0.0003 1.0000 0.0533
-17.500 -1.2513 0.09074 0.08440 -0.0013 1.0000 0.0541
-17.250 -1.2516 0.08712 0.08065 -0.0026 1.0000 0.0551
-17.000 -1.2523 0.08345 0.07683 -0.0039 1.0000 0.0559
-16.750 -1.2505 0.08028 0.07354 -0.0048 1.0000 0.0569
-16.500 -1.2364 0.07921 0.07259 -0.0040 1.0000 0.0583
-16.250 -1.2309 0.07664 0.07003 -0.0045 1.0000 0.0596
-16.000 -1.2278 0.07372 0.06703 -0.0053 1.0000 0.0611
-15.750 -1.2269 0.07044 0.06362 -0.0062 1.0000 0.0625
-15.500 -1.2205 0.06825 0.06146 -0.0061 1.0000 0.0641
-15.250 -1.2169 0.06562 0.05886 -0.0065 1.0000 0.0658
-15.000 -1.2149 0.06272 0.05592 -0.0070 1.0000 0.0676
-14.750 -1.2136 0.05974 0.05282 -0.0076 1.0000 0.0696
-14.500 -1.2136 0.05688 0.05001 -0.0078 1.0000 0.0716
-14.250 -1.2147 0.05376 0.04688 -0.0083 1.0000 0.0738
-14.000 -1.2148 0.05071 0.04375 -0.0089 1.0000 0.0767
-13.750 -1.2185 0.04737 0.04042 -0.0094 1.0000 0.0795
-13.500 -1.2208 0.04415 0.03718 -0.0099 1.0000 0.0831
-13.250 -1.2232 0.04096 0.03397 -0.0103 1.0000 0.0873
-13.000 -1.2258 0.03783 0.03083 -0.0107 1.0000 0.0928
-12.750 -1.2294 0.03475 0.02778 -0.0108 1.0000 0.0994
-12.500 -1.2316 0.03201 0.02508 -0.0106 1.0000 0.1086
-12.250 -1.2324 0.02966 0.02278 -0.0099 1.0000 0.1210
-12.000 -1.2294 0.02790 0.02102 -0.0088 1.0000 0.1356
-11.750 -1.2235 0.02663 0.01972 -0.0072 1.0000 0.1488
-11.500 -1.2174 0.02566 0.01875 -0.0050 1.0000 0.1592
-11.250 -1.2063 0.02489 0.01792 -0.0031 1.0000 0.1686
-11.000 -1.1910 0.02427 0.01720 -0.0017 1.0000 0.1775
-10.750 -1.1748 0.02357 0.01652 -0.0004 1.0000 0.1850
-10.500 -1.1566 0.02307 0.01593 0.0007 1.0000 0.1928
-10.250 -1.1372 0.02245 0.01528 0.0016 1.0000 0.1996
-10.000 -1.1171 0.02192 0.01475 0.0026 1.0000 0.2065
-9.750 -1.0962 0.02151 0.01419 0.0035 1.0000 0.2131
-9.500 -1.0746 0.02084 0.01365 0.0042 1.0000 0.2198
-9.250 -1.0525 0.02040 0.01315 0.0049 1.0000 0.2266
-9.000 -1.0299 0.01988 0.01260 0.0056 1.0000 0.2329
-8.750 -1.0076 0.01937 0.01217 0.0063 1.0000 0.2397
-8.500 -0.9848 0.01898 0.01170 0.0070 1.0000 0.2466
-8.250 -0.9624 0.01845 0.01125 0.0077 1.0000 0.2535
-8.000 -0.9406 0.01809 0.01092 0.0085 1.0000 0.2619
-7.750 -0.9201 0.01770 0.01059 0.0095 1.0000 0.2712
-7.500 -0.8885 0.01723 0.01014 0.0082 0.9754 0.2824
-7.250 -0.8326 0.01667 0.00964 0.0021 0.9667 0.2942
-7.000 -0.7738 0.01618 0.00908 -0.0046 0.9554 0.3068
-6.750 -0.7203 0.01585 0.00876 -0.0103 0.9401 0.3210
-6.500 -0.6791 0.01566 0.00861 -0.0133 0.9227 0.3342
-6.250 -0.6537 0.01561 0.00853 -0.0127 0.9027 0.3474
-6.000 -0.6317 0.01553 0.00845 -0.0113 0.8844 0.3609
-5.750 -0.6108 0.01533 0.00830 -0.0096 0.8676 0.3738
-5.500 -0.5893 0.01515 0.00806 -0.0081 0.8515 0.3876
-5.250 -0.5667 0.01496 0.00790 -0.0067 0.8359 0.4004
-5.000 -0.5433 0.01476 0.00770 -0.0054 0.8213 0.4126
-4.750 -0.5196 0.01466 0.00750 -0.0042 0.8082 0.4255
-4.500 -0.4947 0.01451 0.00738 -0.0032 0.7948 0.4364
-4.250 -0.4698 0.01446 0.00722 -0.0023 0.7818 0.4481
-4.000 -0.4433 0.01436 0.00712 -0.0017 0.7701 0.4576
-3.750 -0.4178 0.01434 0.00703 -0.0009 0.7568 0.4681
-3.500 -0.3909 0.01431 0.00696 -0.0003 0.7454 0.4771
-3.250 -0.3653 0.01432 0.00694 0.0004 0.7323 0.4871
-3.000 -0.3385 0.01434 0.00688 0.0010 0.7215 0.4962
-2.750 -0.3122 0.01434 0.00691 0.0016 0.7094 0.5049
-2.500 -0.2857 0.01442 0.00681 0.0023 0.6993 0.5142
-2.250 -0.2588 0.01437 0.00686 0.0027 0.6874 0.5216
-2.000 -0.2320 0.01444 0.00684 0.0033 0.6771 0.5309
-1.750 -0.2057 0.01443 0.00682 0.0039 0.6658 0.5395
-1.500 -0.1784 0.01445 0.00684 0.0044 0.6556 0.5475
-1.250 -0.1520 0.01452 0.00684 0.0050 0.6457 0.5567
-1.000 -0.1247 0.01447 0.00682 0.0054 0.6354 0.5647
-0.750 -0.0973 0.01455 0.00684 0.0058 0.6267 0.5735
-0.500 -0.0715 0.01455 0.00684 0.0065 0.6160 0.5838
-0.250 -0.0440 0.01454 0.00687 0.0070 0.6071 0.5937
0.000 -0.0184 0.01464 0.00692 0.0077 0.5975 0.6057
0.250 0.0093 0.01451 0.00686 0.0082 0.5868 0.6149
0.500 0.0362 0.01449 0.00680 0.0087 0.5763 0.6245
0.750 0.0634 0.01437 0.00669 0.0091 0.5650 0.6335
1.000 0.0913 0.01436 0.00666 0.0094 0.5563 0.6425
1.250 0.1181 0.01435 0.00666 0.0099 0.5466 0.6523
1.500 0.1468 0.01428 0.00662 0.0100 0.5385 0.6608
1.750 0.1744 0.01431 0.00667 0.0103 0.5298 0.6706
2.000 0.2023 0.01428 0.00668 0.0106 0.5209 0.6804
2.500 0.2579 0.01437 0.00678 0.0111 0.5041 0.7003
2.750 0.2866 0.01434 0.00681 0.0112 0.4954 0.7093
3.000 0.3143 0.01443 0.00690 0.0114 0.4870 0.7203
3.250 0.3425 0.01443 0.00700 0.0116 0.4777 0.7306
3.500 0.3706 0.01455 0.00705 0.0118 0.4694 0.7425
3.750 0.3983 0.01456 0.00721 0.0120 0.4595 0.7536
4.000 0.4261 0.01463 0.00726 0.0123 0.4499 0.7662
4.250 0.4537 0.01469 0.00742 0.0125 0.4395 0.7782
4.500 0.4806 0.01476 0.00751 0.0130 0.4291 0.7930
4.750 0.5071 0.01487 0.00772 0.0135 0.4180 0.8069
5.000 0.5325 0.01498 0.00785 0.0143 0.4065 0.8217
5.250 0.5562 0.01511 0.00807 0.0155 0.3934 0.8379
5.500 0.5784 0.01530 0.00821 0.0169 0.3808 0.8552
5.750 0.5993 0.01543 0.00840 0.0186 0.3665 0.8741
6.000 0.6190 0.01560 0.00858 0.0205 0.3525 0.8953
6.250 0.6427 0.01573 0.00863 0.0214 0.3388 0.9169
6.500 0.6816 0.01580 0.00865 0.0188 0.3226 0.9371
6.750 0.7427 0.01601 0.00888 0.0113 0.3045 0.9517
7.000 0.8117 0.01643 0.00934 0.0021 0.2884 0.9609
7.250 0.8735 0.01694 0.00986 -0.0053 0.2733 0.9694
7.500 0.9072 0.01768 0.01046 -0.0071 0.2625 1.0000
7.750 0.9319 0.01805 0.01084 -0.0070 0.2530 1.0000
8.000 0.9562 0.01860 0.01128 -0.0067 0.2447 1.0000
8.250 0.9814 0.01900 0.01173 -0.0066 0.2364 1.0000
8.500 1.0056 0.01964 0.01223 -0.0064 0.2293 1.0000
8.750 1.0308 0.02009 0.01277 -0.0063 0.2231 1.0000
9.000 1.0554 0.02059 0.01328 -0.0061 0.2166 1.0000
9.250 1.0793 0.02129 0.01389 -0.0059 0.2104 1.0000
9.500 1.1035 0.02173 0.01446 -0.0056 0.2041 1.0000
9.750 1.1264 0.02230 0.01501 -0.0053 0.1973 1.0000
10.000 1.1491 0.02293 0.01567 -0.0049 0.1909 1.0000
10.250 1.1711 0.02345 0.01628 -0.0045 0.1836 1.0000
10.500 1.1914 0.02416 0.01697 -0.0040 0.1764 1.0000
10.750 1.2115 0.02473 0.01765 -0.0034 0.1674 1.0000
11.000 1.2298 0.02548 0.01847 -0.0028 0.1574 1.0000
11.250 1.2453 0.02637 0.01939 -0.0019 0.1447 1.0000
11.500 1.2536 0.02752 0.02055 -0.0003 0.1294 1.0000
11.750 1.2545 0.02928 0.02225 0.0014 0.1144 1.0000
12.000 1.2536 0.03160 0.02449 0.0024 0.1026 1.0000
12.250 1.2536 0.03416 0.02703 0.0028 0.0942 1.0000
12.500 1.2537 0.03693 0.02982 0.0028 0.0878 1.0000
12.750 1.2513 0.04010 0.03296 0.0024 0.0839 1.0000
13.000 1.2529 0.04292 0.03585 0.0021 0.0801 1.0000
13.250 1.2510 0.04615 0.03907 0.0015 0.0775 1.0000
13.500 1.2505 0.04922 0.04217 0.0012 0.0751 1.0000
13.750 1.2521 0.05211 0.04514 0.0007 0.0730 1.0000
14.000 1.2527 0.05509 0.04814 0.0003 0.0711 1.0000
14.250 1.2532 0.05795 0.05094 0.0001 0.0695 1.0000
14.500 1.2563 0.06064 0.05369 -0.0001 0.0680 1.0000
14.750 1.2590 0.06344 0.05658 -0.0006 0.0666 1.0000
15.000 1.2625 0.06613 0.05931 -0.0010 0.0651 1.0000
15.250 1.2674 0.06861 0.06178 -0.0012 0.0638 1.0000
15.500 1.2785 0.07005 0.06311 -0.0005 0.0624 1.0000
15.750 1.2808 0.07307 0.06625 -0.0011 0.0613 1.0000
16.000 1.2834 0.07608 0.06938 -0.0018 0.0603 1.0000
16.250 1.2868 0.07899 0.07237 -0.0025 0.0593 1.0000
16.500 1.2919 0.08163 0.07506 -0.0029 0.0584 1.0000
16.750 1.2993 0.08390 0.07736 -0.0031 0.0576 1.0000
17.000 1.3112 0.08544 0.07886 -0.0027 0.0567 1.0000
17.250 1.3282 0.08620 0.07954 -0.0014 0.0558 1.0000
17.500 1.3219 0.09067 0.08422 -0.0033 0.0553 1.0000
17.750 1.3172 0.09495 0.08867 -0.0049 0.0549 1.0000
18.000 1.3102 0.09966 0.09356 -0.0070 0.0544 1.0000
18.250 1.3030 0.10449 0.09856 -0.0091 0.0540 1.0000
18.500 1.2940 0.10972 0.10397 -0.0116 0.0535 1.0000
18.750 1.2841 0.11516 0.10958 -0.0144 0.0530 1.0000
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Polar data table (+)
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