TRAINER60 (trainer60-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: TRAINER60 (trainer60-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.44 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-trainer60-il-1000000.txt Download as CSV file: xf-trainer60-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.750 -1.3935 0.10378 0.09963 0.0270 1.0000 0.0257
-18.500 -1.4052 0.09841 0.09417 0.0250 1.0000 0.0259
-18.250 -1.4190 0.09281 0.08847 0.0229 1.0000 0.0261
-18.000 -1.4292 0.08783 0.08340 0.0212 1.0000 0.0264
-17.750 -1.4397 0.08283 0.07831 0.0195 1.0000 0.0266
-17.500 -1.4500 0.07790 0.07328 0.0178 1.0000 0.0267
-17.250 -1.4588 0.07327 0.06856 0.0164 1.0000 0.0270
-17.000 -1.4662 0.06887 0.06406 0.0151 1.0000 0.0271
-16.750 -1.4729 0.06465 0.05974 0.0139 1.0000 0.0273
-16.500 -1.4865 0.05971 0.05471 0.0126 1.0000 0.0276
-16.250 -1.4990 0.05507 0.04997 0.0115 1.0000 0.0279
-16.000 -1.5092 0.05082 0.04563 0.0106 1.0000 0.0283
-15.750 -1.5144 0.04715 0.04188 0.0100 1.0000 0.0287
-15.500 -1.5173 0.04377 0.03843 0.0094 1.0000 0.0291
-15.250 -1.5159 0.04087 0.03547 0.0089 1.0000 0.0297
-15.000 -1.5129 0.03814 0.03267 0.0084 1.0000 0.0302
-14.750 -1.5074 0.03572 0.03018 0.0080 1.0000 0.0307
-14.500 -1.5002 0.03354 0.02792 0.0078 1.0000 0.0311
-14.250 -1.4961 0.03110 0.02541 0.0077 1.0000 0.0317
-14.000 -1.4923 0.02879 0.02304 0.0078 1.0000 0.0326
-13.750 -1.4845 0.02698 0.02119 0.0082 1.0000 0.0334
-13.500 -1.4686 0.02548 0.01964 0.0076 0.9994 0.0343
-13.250 -1.4476 0.02427 0.01837 0.0066 0.9982 0.0353
-13.000 -1.4301 0.02295 0.01702 0.0062 0.9962 0.0367
-12.750 -1.4361 0.02184 0.01587 0.0114 0.9679 0.0375
-12.500 -1.4086 0.02096 0.01494 0.0101 0.9620 0.0392
-12.250 -1.3799 0.02011 0.01405 0.0088 0.9565 0.0411
-12.000 -1.3433 0.01913 0.01307 0.0058 0.9546 0.0441
-11.750 -1.3043 0.01818 0.01212 0.0024 0.9529 0.0480
-11.500 -1.2649 0.01728 0.01123 -0.0011 0.9500 0.0534
-11.250 -1.2278 0.01642 0.01040 -0.0041 0.9457 0.0613
-11.000 -1.1949 0.01550 0.00955 -0.0063 0.9410 0.0743
-10.750 -1.1626 0.01454 0.00872 -0.0084 0.9358 0.0944
-10.500 -1.1341 0.01382 0.00810 -0.0094 0.9302 0.1143
-10.250 -1.1069 0.01332 0.00768 -0.0098 0.9240 0.1288
-10.000 -1.0802 0.01303 0.00740 -0.0097 0.9179 0.1383
-9.750 -1.0546 0.01272 0.00713 -0.0095 0.9117 0.1466
-9.500 -1.0305 0.01251 0.00691 -0.0087 0.9052 0.1521
-9.250 -1.0069 0.01224 0.00665 -0.0079 0.8985 0.1587
-9.000 -0.9847 0.01205 0.00646 -0.0066 0.8911 0.1634
-8.750 -0.9618 0.01183 0.00622 -0.0055 0.8837 0.1677
-8.500 -0.9415 0.01156 0.00598 -0.0038 0.8732 0.1726
-8.250 -0.9195 0.01136 0.00576 -0.0024 0.8611 0.1768
-8.000 -0.8975 0.01122 0.00557 -0.0009 0.8419 0.1798
-7.750 -0.8763 0.01100 0.00527 0.0006 0.8109 0.1848
-7.500 -0.8494 0.01084 0.00501 0.0010 0.7761 0.1897
-7.250 -0.8202 0.01074 0.00481 0.0008 0.7510 0.1944
-7.000 -0.7918 0.01060 0.00461 0.0007 0.7333 0.1991
-6.750 -0.7646 0.01040 0.00439 0.0009 0.7189 0.2066
-6.500 -0.7364 0.01028 0.00424 0.0010 0.7067 0.2127
-6.250 -0.7102 0.01004 0.00402 0.0014 0.6960 0.2239
-6.000 -0.6829 0.00988 0.00385 0.0016 0.6863 0.2327
-5.750 -0.6564 0.00968 0.00366 0.0020 0.6760 0.2442
-5.500 -0.6298 0.00946 0.00349 0.0024 0.6685 0.2571
-5.250 -0.6032 0.00925 0.00333 0.0028 0.6606 0.2732
-5.000 -0.5764 0.00908 0.00318 0.0032 0.6521 0.2911
-4.750 -0.5491 0.00890 0.00306 0.0034 0.6461 0.3082
-4.500 -0.5213 0.00876 0.00296 0.0037 0.6389 0.3234
-4.250 -0.4937 0.00864 0.00286 0.0039 0.6305 0.3382
-4.000 -0.4653 0.00855 0.00278 0.0040 0.6237 0.3488
-3.750 -0.4370 0.00846 0.00271 0.0041 0.6160 0.3594
-3.500 -0.4083 0.00842 0.00263 0.0042 0.6077 0.3674
-3.250 -0.3799 0.00833 0.00256 0.0043 0.6006 0.3765
-3.000 -0.3508 0.00828 0.00251 0.0043 0.5925 0.3837
-2.750 -0.3224 0.00823 0.00244 0.0045 0.5833 0.3918
-2.500 -0.2935 0.00816 0.00239 0.0045 0.5754 0.4002
-2.250 -0.2644 0.00814 0.00234 0.0045 0.5652 0.4062
-2.000 -0.2358 0.00808 0.00228 0.0046 0.5546 0.4148
-1.750 -0.2069 0.00806 0.00224 0.0046 0.5419 0.4224
-1.500 -0.1778 0.00806 0.00220 0.0046 0.5291 0.4289
-1.250 -0.1493 0.00803 0.00216 0.0047 0.5152 0.4379
-1.000 -0.1199 0.00802 0.00214 0.0046 0.5048 0.4461
-0.750 -0.0911 0.00803 0.00213 0.0046 0.4923 0.4554
-0.500 -0.0617 0.00801 0.00212 0.0045 0.4821 0.4656
-0.250 -0.0326 0.00804 0.00212 0.0045 0.4709 0.4743
0.000 -0.0030 0.00802 0.00213 0.0044 0.4633 0.4845
0.250 0.0266 0.00805 0.00214 0.0042 0.4551 0.4930
0.500 0.0559 0.00807 0.00217 0.0041 0.4458 0.5040
0.750 0.0858 0.00809 0.00220 0.0040 0.4393 0.5140
1.000 0.1156 0.00810 0.00224 0.0038 0.4319 0.5246
1.250 0.1449 0.00816 0.00228 0.0037 0.4244 0.5340
1.500 0.1752 0.00817 0.00232 0.0034 0.4183 0.5428
1.750 0.2049 0.00821 0.00237 0.0032 0.4108 0.5524
2.000 0.2340 0.00831 0.00243 0.0032 0.4033 0.5587
2.250 0.2651 0.00830 0.00247 0.0027 0.3979 0.5671
2.500 0.2955 0.00834 0.00252 0.0024 0.3910 0.5736
2.750 0.3249 0.00845 0.00259 0.0023 0.3827 0.5791
3.000 0.3552 0.00849 0.00263 0.0020 0.3766 0.5835
3.250 0.3869 0.00853 0.00269 0.0013 0.3677 0.5904
3.500 0.4179 0.00860 0.00277 0.0008 0.3595 0.5967
3.750 0.4486 0.00866 0.00283 0.0004 0.3505 0.6023
4.000 0.4785 0.00879 0.00291 0.0002 0.3400 0.6069
4.250 0.5116 0.00885 0.00299 -0.0009 0.3275 0.6142
4.500 0.5434 0.00897 0.00309 -0.0016 0.3118 0.6205
4.750 0.5741 0.00916 0.00321 -0.0022 0.2916 0.6264
5.000 0.6052 0.00942 0.00337 -0.0029 0.2678 0.6326
5.250 0.6395 0.00969 0.00357 -0.0044 0.2435 0.6415
5.500 0.6718 0.00994 0.00377 -0.0054 0.2276 0.6498
5.750 0.7058 0.01013 0.00396 -0.0067 0.2173 0.6601
6.000 0.7398 0.01032 0.00416 -0.0081 0.2088 0.6719
6.250 0.7745 0.01048 0.00436 -0.0095 0.2018 0.6860
6.500 0.8088 0.01070 0.00460 -0.0110 0.1936 0.7038
6.750 0.8447 0.01083 0.00480 -0.0127 0.1885 0.7255
7.000 0.8802 0.01105 0.00506 -0.0144 0.1818 0.7495
7.250 0.9175 0.01123 0.00532 -0.0165 0.1762 0.7725
7.500 0.9503 0.01140 0.00556 -0.0175 0.1712 0.7945
7.750 0.9792 0.01162 0.00585 -0.0177 0.1659 0.8185
8.000 1.0048 0.01183 0.00612 -0.0171 0.1617 0.8396
8.250 1.0278 0.01203 0.00637 -0.0160 0.1578 0.8572
8.500 1.0479 0.01231 0.00665 -0.0142 0.1529 0.8720
8.750 1.0648 0.01259 0.00692 -0.0118 0.1482 0.8841
9.000 1.0777 0.01279 0.00714 -0.0084 0.1441 0.8925
9.250 1.0918 0.01310 0.00742 -0.0054 0.1377 0.9001
9.500 1.1096 0.01337 0.00769 -0.0033 0.1317 0.9061
9.750 1.1265 0.01374 0.00801 -0.0011 0.1220 0.9119
10.000 1.1477 0.01422 0.00841 -0.0001 0.1076 0.9171
10.250 1.1633 0.01507 0.00908 0.0017 0.0840 0.9224
10.750 1.2077 0.01687 0.01068 0.0021 0.0548 0.9307
11.000 1.2425 0.01766 0.01145 -0.0004 0.0492 0.9330
11.250 1.2741 0.01838 0.01217 -0.0021 0.0457 0.9362
11.500 1.2979 0.01902 0.01282 -0.0020 0.0436 0.9406
11.750 1.3275 0.01969 0.01352 -0.0033 0.0417 0.9439
12.000 1.3502 0.02048 0.01433 -0.0034 0.0402 0.9478
12.250 1.3741 0.02123 0.01512 -0.0038 0.0390 0.9513
12.500 1.3953 0.02196 0.01591 -0.0038 0.0380 0.9554
12.750 1.4162 0.02291 0.01694 -0.0043 0.0370 0.9603
13.000 1.4408 0.02427 0.01836 -0.0064 0.0360 0.9649
13.250 1.4268 0.02598 0.02010 -0.0007 0.0357 0.9961
13.500 1.4429 0.02782 0.02201 -0.0021 0.0348 0.9978
13.750 1.4645 0.02926 0.02352 -0.0039 0.0343 0.9992
14.000 1.4828 0.03104 0.02536 -0.0056 0.0337 1.0000
14.250 1.4908 0.03310 0.02749 -0.0058 0.0332 1.0000
14.500 1.4971 0.03541 0.02986 -0.0061 0.0328 1.0000
14.750 1.5018 0.03790 0.03240 -0.0065 0.0322 1.0000
15.000 1.5028 0.04084 0.03541 -0.0070 0.0319 1.0000
15.250 1.5000 0.04424 0.03889 -0.0077 0.0315 1.0000
15.500 1.4941 0.04802 0.04275 -0.0085 0.0311 1.0000
15.750 1.4813 0.05268 0.04752 -0.0095 0.0306 1.0000
16.000 1.4785 0.05620 0.05113 -0.0103 0.0305 1.0000
16.250 1.4748 0.05990 0.05492 -0.0113 0.0303 1.0000
16.500 1.4696 0.06387 0.05898 -0.0124 0.0301 1.0000
16.750 1.4632 0.06810 0.06330 -0.0137 0.0299 1.0000
17.000 1.4546 0.07274 0.06803 -0.0152 0.0298 1.0000
17.250 1.4463 0.07738 0.07276 -0.0167 0.0296 1.0000
17.500 1.4381 0.08204 0.07752 -0.0183 0.0292 1.0000
17.750 1.4278 0.08707 0.08263 -0.0201 0.0291 1.0000
18.000 1.4173 0.09219 0.08784 -0.0219 0.0289 1.0000
18.250 1.4067 0.09737 0.09311 -0.0239 0.0287 1.0000
|
Polar data table (+)
Polar graphs
<< Back to TRAINER60 (trainer60-il)