AS5045 (15%) (as5045-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AS5045 (15%) (as5045-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.52 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-as5045-il-1000000.txt Download as CSV file: xf-as5045-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AS5045 (15%)
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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5803 0.13008 0.12752 -0.0045 0.7394 0.0113
-13.000 -0.5834 0.12411 0.12155 -0.0073 0.7378 0.0115
-9.250 -0.7769 0.02651 0.02103 -0.0408 0.7181 0.0096
-9.000 -0.7581 0.02369 0.01795 -0.0399 0.7170 0.0092
-8.750 -0.7361 0.02203 0.01613 -0.0394 0.7158 0.0093
-8.500 -0.7131 0.02079 0.01477 -0.0390 0.7145 0.0094
-8.250 -0.6896 0.01973 0.01361 -0.0387 0.7131 0.0095
-8.000 -0.6657 0.01881 0.01261 -0.0384 0.7117 0.0096
-7.750 -0.6416 0.01796 0.01169 -0.0382 0.7102 0.0097
-7.500 -0.6173 0.01719 0.01086 -0.0381 0.7089 0.0098
-7.250 -0.5927 0.01645 0.01007 -0.0379 0.7076 0.0099
-7.000 -0.5677 0.01580 0.00936 -0.0379 0.7063 0.0100
-6.750 -0.5422 0.01519 0.00870 -0.0380 0.7048 0.0101
-6.500 -0.5162 0.01464 0.00811 -0.0382 0.7034 0.0102
-6.250 -0.4896 0.01409 0.00754 -0.0385 0.7025 0.0103
-6.000 -0.4642 0.01315 0.00656 -0.0388 0.7013 0.0107
-5.750 -0.4367 0.01263 0.00602 -0.0392 0.7000 0.0111
-5.500 -0.4086 0.01221 0.00557 -0.0397 0.6988 0.0115
-5.250 -0.3801 0.01183 0.00517 -0.0401 0.6976 0.0119
-5.000 -0.3513 0.01150 0.00482 -0.0406 0.6963 0.0126
-4.750 -0.3223 0.01123 0.00452 -0.0410 0.6949 0.0132
-4.500 -0.2933 0.01086 0.00413 -0.0416 0.6935 0.0145
-4.250 -0.2639 0.01064 0.00388 -0.0421 0.6922 0.0161
-4.000 -0.2345 0.01037 0.00361 -0.0426 0.6909 0.0213
-3.750 -0.2046 0.00877 0.00288 -0.0447 0.6894 0.2307
-3.500 -0.1723 0.00716 0.00227 -0.0476 0.6876 0.4871
-3.250 -0.1414 0.00687 0.00225 -0.0484 0.6865 0.5682
-3.000 -0.1112 0.00688 0.00230 -0.0489 0.6850 0.5918
-2.750 -0.0811 0.00697 0.00240 -0.0492 0.6832 0.6095
-2.500 -0.0509 0.00705 0.00242 -0.0497 0.6811 0.6178
-2.250 -0.0211 0.00711 0.00251 -0.0499 0.6789 0.6249
-2.000 0.0089 0.00718 0.00253 -0.0503 0.6767 0.6298
-1.750 0.0390 0.00724 0.00252 -0.0507 0.6745 0.6333
-1.250 0.0985 0.00730 0.00259 -0.0515 0.6697 0.6393
-1.000 0.1285 0.00728 0.00257 -0.0519 0.6672 0.6416
-0.750 0.1585 0.00728 0.00255 -0.0523 0.6644 0.6439
-0.500 0.1885 0.00729 0.00253 -0.0527 0.6617 0.6462
-0.250 0.2186 0.00731 0.00251 -0.0532 0.6589 0.6479
0.000 0.2483 0.00732 0.00249 -0.0536 0.6557 0.6500
0.250 0.2782 0.00726 0.00247 -0.0540 0.6531 0.6522
0.500 0.3080 0.00722 0.00246 -0.0543 0.6495 0.6542
0.750 0.3378 0.00719 0.00243 -0.0547 0.6455 0.6559
1.000 0.3676 0.00718 0.00240 -0.0551 0.6417 0.6574
1.250 0.3975 0.00716 0.00239 -0.0555 0.6377 0.6589
1.500 0.4275 0.00711 0.00237 -0.0560 0.6327 0.6603
1.750 0.4573 0.00709 0.00233 -0.0564 0.6276 0.6617
2.000 0.4872 0.00709 0.00233 -0.0568 0.6222 0.6629
2.250 0.5171 0.00707 0.00233 -0.0572 0.6152 0.6639
2.500 0.5468 0.00703 0.00228 -0.0576 0.6076 0.6653
2.750 0.5764 0.00698 0.00225 -0.0580 0.5972 0.6667
3.000 0.6057 0.00699 0.00224 -0.0583 0.5825 0.6680
3.250 0.6344 0.00706 0.00227 -0.0585 0.5606 0.6694
3.500 0.6626 0.00721 0.00233 -0.0587 0.5314 0.6707
3.750 0.6902 0.00746 0.00244 -0.0588 0.4949 0.6719
4.000 0.7171 0.00780 0.00263 -0.0588 0.4543 0.6732
4.250 0.7442 0.00813 0.00282 -0.0589 0.4181 0.6744
4.500 0.7712 0.00846 0.00302 -0.0589 0.3847 0.6758
4.750 0.7973 0.00888 0.00327 -0.0589 0.3443 0.6772
5.000 0.8237 0.00927 0.00350 -0.0589 0.3084 0.6785
5.250 0.8502 0.00963 0.00374 -0.0589 0.2808 0.6795
5.500 0.8766 0.00998 0.00398 -0.0589 0.2534 0.6804
5.750 0.9030 0.01028 0.00419 -0.0589 0.2295 0.6820
6.000 0.9291 0.01061 0.00444 -0.0589 0.2079 0.6835
6.250 0.9551 0.01096 0.00472 -0.0588 0.1879 0.6850
6.500 0.9811 0.01129 0.00499 -0.0587 0.1706 0.6864
6.750 1.0070 0.01163 0.00527 -0.0586 0.1548 0.6877
7.000 1.0325 0.01198 0.00558 -0.0585 0.1398 0.6891
7.250 1.0580 0.01234 0.00589 -0.0584 0.1263 0.6905
7.500 1.0831 0.01272 0.00621 -0.0582 0.1137 0.6919
7.750 1.1080 0.01311 0.00656 -0.0579 0.1024 0.6934
8.000 1.1324 0.01354 0.00692 -0.0577 0.0916 0.6947
8.250 1.1571 0.01392 0.00728 -0.0574 0.0832 0.6959
8.500 1.1814 0.01429 0.00765 -0.0571 0.0756 0.6976
8.750 1.2046 0.01476 0.00809 -0.0567 0.0674 0.6993
9.000 1.2286 0.01513 0.00848 -0.0563 0.0622 0.7008
9.250 1.2512 0.01562 0.00895 -0.0558 0.0560 0.7024
9.500 1.2741 0.01605 0.00940 -0.0553 0.0519 0.7040
9.750 1.2953 0.01661 0.00995 -0.0546 0.0474 0.7056
10.000 1.3179 0.01702 0.01041 -0.0540 0.0449 0.7073
10.250 1.3382 0.01759 0.01097 -0.0532 0.0418 0.7091
10.500 1.3577 0.01820 0.01160 -0.0523 0.0391 0.7107
10.750 1.3784 0.01866 0.01212 -0.0515 0.0375 0.7123
11.000 1.3969 0.01924 0.01273 -0.0505 0.0353 0.7145
11.250 1.4105 0.02005 0.01357 -0.0488 0.0326 0.7165
11.500 1.4259 0.02050 0.01408 -0.0472 0.0316 0.7185
11.750 1.4411 0.02113 0.01477 -0.0458 0.0302 0.7206
12.000 1.4545 0.02196 0.01564 -0.0444 0.0288 0.7227
12.250 1.4642 0.02312 0.01684 -0.0430 0.0272 0.7248
12.500 1.4774 0.02414 0.01793 -0.0421 0.0263 0.7268
12.750 1.4917 0.02515 0.01902 -0.0415 0.0255 0.7292
13.000 1.5051 0.02631 0.02025 -0.0411 0.0246 0.7319
13.250 1.5168 0.02764 0.02163 -0.0406 0.0236 0.7346
13.500 1.5252 0.02928 0.02333 -0.0400 0.0225 0.7373
13.750 1.5335 0.03095 0.02508 -0.0393 0.0217 0.7402
14.000 1.5454 0.03226 0.02646 -0.0389 0.0211 0.7431
14.250 1.5560 0.03368 0.02797 -0.0384 0.0203 0.7469
14.500 1.5647 0.03529 0.02965 -0.0379 0.0196 0.7508
14.750 1.5707 0.03712 0.03154 -0.0373 0.0188 0.7550
15.000 1.5717 0.03946 0.03395 -0.0366 0.0179 0.7590
15.250 1.5768 0.04144 0.03604 -0.0361 0.0175 0.7643
15.500 1.5831 0.04329 0.03799 -0.0356 0.0170 0.7706
15.750 1.5882 0.04529 0.04009 -0.0352 0.0164 0.7780
16.000 1.5911 0.04754 0.04246 -0.0349 0.0159 0.7882
16.250 1.5918 0.05004 0.04508 -0.0346 0.0153 0.8031
16.500 1.5895 0.05299 0.04818 -0.0345 0.0147 0.8323
16.750 1.5776 0.05612 0.05167 -0.0332 0.0142 1.0000
17.000 1.5796 0.05886 0.05450 -0.0334 0.0139 1.0000
17.250 1.5800 0.06187 0.05761 -0.0338 0.0135 1.0000
17.500 1.5788 0.06519 0.06102 -0.0343 0.0131 1.0000
17.750 1.5753 0.06891 0.06482 -0.0351 0.0126 1.0000
18.000 1.5689 0.07310 0.06909 -0.0361 0.0122 1.0000
18.250 1.5592 0.07785 0.07394 -0.0374 0.0119 1.0000
18.500 1.5442 0.08357 0.07977 -0.0392 0.0115 1.0000
18.750 1.5254 0.09003 0.08636 -0.0415 0.0112 1.0000
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