TRAINER60 (trainer60-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: TRAINER60 (trainer60-il) Reynolds number: 200,000 Max Cl/Cd: 50.93 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-trainer60-il-200000-n5.txt Download as CSV file: xf-trainer60-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -1.1582 0.08986 0.08340 0.0070 1.0000 0.0454
-16.000 -1.1656 0.08508 0.07857 0.0050 1.0000 0.0461
-15.750 -1.1727 0.08037 0.07378 0.0031 1.0000 0.0469
-15.500 -1.1791 0.07582 0.06915 0.0013 1.0000 0.0478
-15.250 -1.1848 0.07147 0.06471 -0.0003 1.0000 0.0490
-15.000 -1.1890 0.06741 0.06054 -0.0017 1.0000 0.0501
-14.750 -1.1953 0.06323 0.05627 -0.0032 1.0000 0.0513
-14.500 -1.2022 0.05909 0.05206 -0.0045 1.0000 0.0524
-14.250 -1.2071 0.05527 0.04816 -0.0057 1.0000 0.0538
-14.000 -1.2094 0.05183 0.04462 -0.0066 1.0000 0.0558
-13.750 -1.2120 0.04838 0.04109 -0.0075 1.0000 0.0575
-13.500 -1.2144 0.04502 0.03767 -0.0084 1.0000 0.0598
-13.250 -1.2132 0.04210 0.03468 -0.0090 1.0000 0.0625
-13.000 -1.2133 0.03911 0.03164 -0.0096 1.0000 0.0656
-12.750 -1.2107 0.03652 0.02899 -0.0099 1.0000 0.0695
-12.500 -1.2087 0.03400 0.02644 -0.0100 1.0000 0.0739
-12.250 -1.2055 0.03173 0.02415 -0.0097 1.0000 0.0800
-12.000 -1.2020 0.02970 0.02212 -0.0091 1.0000 0.0877
-11.750 -1.1978 0.02790 0.02035 -0.0081 1.0000 0.0972
-11.500 -1.1921 0.02641 0.01891 -0.0067 1.0000 0.1088
-11.250 -1.1841 0.02527 0.01780 -0.0049 1.0000 0.1200
-11.000 -1.1733 0.02436 0.01690 -0.0030 1.0000 0.1304
-10.750 -1.1578 0.02359 0.01612 -0.0018 1.0000 0.1401
-10.500 -1.1396 0.02292 0.01543 -0.0008 1.0000 0.1493
-10.250 -1.1216 0.02225 0.01477 0.0003 1.0000 0.1564
-10.000 -1.1004 0.02174 0.01419 0.0010 1.0000 0.1639
-9.750 -1.0811 0.02113 0.01360 0.0020 1.0000 0.1703
-9.250 -1.0439 0.02003 0.01246 0.0048 0.9802 0.1819
-9.000 -0.9983 0.01949 0.01188 0.0004 0.9594 0.1902
-8.750 -0.9512 0.01898 0.01129 -0.0041 0.9468 0.1980
-8.500 -0.9082 0.01845 0.01073 -0.0079 0.9353 0.2069
-8.250 -0.8721 0.01804 0.01030 -0.0102 0.9235 0.2176
-8.000 -0.8415 0.01769 0.00992 -0.0111 0.9113 0.2285
-7.750 -0.8159 0.01731 0.00957 -0.0110 0.8981 0.2361
-7.500 -0.7925 0.01697 0.00922 -0.0102 0.8834 0.2426
-7.250 -0.7696 0.01666 0.00886 -0.0092 0.8668 0.2489
-7.000 -0.7482 0.01627 0.00851 -0.0080 0.8481 0.2562
-6.750 -0.7250 0.01596 0.00817 -0.0070 0.8283 0.2647
-6.500 -0.7019 0.01564 0.00783 -0.0059 0.8084 0.2733
-6.250 -0.6777 0.01538 0.00750 -0.0051 0.7897 0.2844
-6.000 -0.6538 0.01511 0.00721 -0.0042 0.7720 0.2959
-5.750 -0.6289 0.01489 0.00695 -0.0035 0.7558 0.3084
-5.500 -0.6033 0.01471 0.00670 -0.0029 0.7420 0.3213
-5.250 -0.5774 0.01452 0.00649 -0.0024 0.7287 0.3332
-5.000 -0.5510 0.01439 0.00628 -0.0020 0.7168 0.3454
-4.750 -0.5255 0.01425 0.00612 -0.0013 0.7048 0.3578
-4.500 -0.4991 0.01413 0.00595 -0.0008 0.6946 0.3687
-4.250 -0.4728 0.01402 0.00581 -0.0004 0.6843 0.3794
-3.750 -0.4195 0.01381 0.00555 0.0005 0.6659 0.3982
-3.500 -0.3925 0.01375 0.00541 0.0009 0.6563 0.4077
-3.250 -0.3662 0.01365 0.00532 0.0014 0.6473 0.4172
-3.000 -0.3392 0.01359 0.00522 0.0018 0.6375 0.4269
-2.750 -0.3127 0.01352 0.00514 0.0024 0.6291 0.4353
-2.500 -0.2855 0.01345 0.00508 0.0027 0.6205 0.4442
-2.250 -0.2584 0.01340 0.00501 0.0031 0.6114 0.4526
-2.000 -0.2316 0.01337 0.00496 0.0036 0.6031 0.4621
-1.750 -0.2041 0.01332 0.00491 0.0039 0.5933 0.4714
-1.500 -0.1772 0.01329 0.00488 0.0044 0.5840 0.4799
-1.250 -0.1496 0.01327 0.00485 0.0047 0.5754 0.4891
-1.000 -0.1223 0.01325 0.00484 0.0050 0.5663 0.4977
-0.750 -0.0951 0.01326 0.00482 0.0054 0.5583 0.5077
-0.500 -0.0677 0.01325 0.00485 0.0058 0.5491 0.5189
-0.250 -0.0408 0.01328 0.00486 0.0062 0.5398 0.5311
0.000 -0.0136 0.01330 0.00488 0.0066 0.5308 0.5417
0.250 0.0138 0.01331 0.00489 0.0070 0.5199 0.5507
0.500 0.0412 0.01336 0.00485 0.0073 0.5088 0.5591
0.750 0.0686 0.01335 0.00486 0.0077 0.4961 0.5660
1.000 0.0962 0.01338 0.00487 0.0080 0.4857 0.5737
1.250 0.1241 0.01344 0.00488 0.0082 0.4760 0.5811
1.500 0.1519 0.01348 0.00491 0.0084 0.4681 0.5880
1.750 0.1803 0.01350 0.00498 0.0085 0.4594 0.5957
2.000 0.2082 0.01357 0.00502 0.0087 0.4511 0.6037
2.250 0.2366 0.01362 0.00509 0.0088 0.4433 0.6104
2.500 0.2649 0.01365 0.00517 0.0089 0.4349 0.6176
2.750 0.2928 0.01375 0.00523 0.0090 0.4266 0.6255
3.000 0.3215 0.01380 0.00534 0.0090 0.4181 0.6332
3.250 0.3499 0.01386 0.00545 0.0090 0.4094 0.6416
3.500 0.3781 0.01396 0.00556 0.0091 0.4014 0.6505
3.750 0.4069 0.01403 0.00570 0.0091 0.3918 0.6588
4.000 0.4349 0.01415 0.00582 0.0091 0.3823 0.6679
4.500 0.4921 0.01436 0.00615 0.0090 0.3614 0.6893
4.750 0.5217 0.01448 0.00634 0.0088 0.3499 0.7018
5.000 0.5508 0.01463 0.00655 0.0086 0.3380 0.7150
5.250 0.5799 0.01481 0.00676 0.0083 0.3237 0.7290
5.500 0.6090 0.01500 0.00701 0.0081 0.3089 0.7453
5.750 0.6378 0.01523 0.00728 0.0079 0.2947 0.7623
6.000 0.6658 0.01550 0.00758 0.0078 0.2811 0.7798
6.250 0.6926 0.01580 0.00792 0.0080 0.2685 0.7987
6.500 0.7178 0.01611 0.00827 0.0085 0.2580 0.8182
6.750 0.7412 0.01648 0.00865 0.0093 0.2484 0.8384
7.000 0.7647 0.01682 0.00902 0.0102 0.2409 0.8580
7.250 0.7869 0.01721 0.00940 0.0113 0.2332 0.8763
7.500 0.8090 0.01763 0.00980 0.0122 0.2257 0.8921
7.750 0.8325 0.01802 0.01019 0.0128 0.2170 0.9056
8.000 0.8577 0.01846 0.01059 0.0129 0.2088 0.9178
8.250 0.8887 0.01883 0.01098 0.0118 0.2003 0.9284
8.500 0.9245 0.01930 0.01144 0.0095 0.1918 0.9374
8.750 0.9662 0.01972 0.01193 0.0059 0.1831 0.9446
9.000 1.0105 0.02025 0.01250 0.0017 0.1759 0.9517
9.250 1.0579 0.02077 0.01311 -0.0030 0.1680 0.9591
9.750 1.1172 0.02213 0.01453 -0.0051 0.1540 1.0000
10.000 1.1390 0.02278 0.01518 -0.0047 0.1475 1.0000
10.250 1.1610 0.02342 0.01585 -0.0043 0.1390 1.0000
10.500 1.1817 0.02415 0.01660 -0.0039 0.1300 1.0000
10.750 1.2003 0.02502 0.01746 -0.0033 0.1185 1.0000
11.000 1.2158 0.02610 0.01849 -0.0025 0.1053 1.0000
11.250 1.2234 0.02744 0.01976 -0.0008 0.0919 1.0000
11.500 1.2273 0.02909 0.02137 0.0007 0.0815 1.0000
11.750 1.2310 0.03104 0.02331 0.0016 0.0740 1.0000
12.000 1.2346 0.03321 0.02549 0.0020 0.0689 1.0000
12.250 1.2393 0.03547 0.02781 0.0020 0.0650 1.0000
12.500 1.2411 0.03819 0.03056 0.0017 0.0618 1.0000
12.750 1.2447 0.04082 0.03327 0.0013 0.0593 1.0000
13.000 1.2451 0.04387 0.03639 0.0006 0.0572 1.0000
13.250 1.2434 0.04723 0.03981 -0.0002 0.0557 1.0000
13.500 1.2441 0.05035 0.04303 -0.0010 0.0541 1.0000
13.750 1.2424 0.05380 0.04658 -0.0020 0.0527 1.0000
14.000 1.2383 0.05759 0.05046 -0.0031 0.0516 1.0000
14.250 1.2320 0.06172 0.05467 -0.0045 0.0506 1.0000
14.500 1.2247 0.06604 0.05905 -0.0059 0.0498 1.0000
14.750 1.2211 0.06995 0.06307 -0.0072 0.0489 1.0000
15.000 1.2168 0.07409 0.06731 -0.0086 0.0481 1.0000
15.250 1.2118 0.07838 0.07170 -0.0102 0.0473 1.0000
15.500 1.2069 0.08274 0.07614 -0.0118 0.0467 1.0000
15.750 1.2016 0.08722 0.08069 -0.0135 0.0460 1.0000
16.000 1.1961 0.09172 0.08524 -0.0152 0.0453 1.0000
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Polar data table (+)
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