USA 28 AIRFOIL (usa28-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: USA 28 AIRFOIL (usa28-il) Reynolds number: 50,000 Max Cl/Cd: 31.72 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa28-il-50000-n5.txt Download as CSV file: xf-usa28-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 28 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4334 0.10204 0.09462 -0.0503 1.0000 0.0812
-10.250 -0.4452 0.09689 0.08956 -0.0517 1.0000 0.0813
-10.000 -0.4590 0.09160 0.08436 -0.0531 1.0000 0.0813
-9.750 -0.4768 0.08595 0.07883 -0.0545 1.0000 0.0812
-9.500 -0.5029 0.07955 0.07255 -0.0563 1.0000 0.0810
-9.250 -0.5402 0.07312 0.06626 -0.0578 1.0000 0.0805
-9.000 -0.5817 0.06719 0.06040 -0.0578 1.0000 0.0799
-8.750 -0.6169 0.06188 0.05503 -0.0566 1.0000 0.0795
-8.500 -0.6451 0.05710 0.05004 -0.0546 1.0000 0.0795
-8.250 -0.6642 0.05284 0.04548 -0.0523 1.0000 0.0798
-8.000 -0.6753 0.04906 0.04131 -0.0499 1.0000 0.0804
-7.750 -0.6797 0.04575 0.03754 -0.0475 1.0000 0.0814
-7.500 -0.6758 0.04357 0.03514 -0.0453 1.0000 0.0831
-7.250 -0.6669 0.04241 0.03397 -0.0432 1.0000 0.0856
-7.000 -0.6458 0.04063 0.03195 -0.0437 0.9957 0.0893
-6.750 -0.6207 0.03831 0.02915 -0.0449 0.9895 0.0926
-6.500 -0.5941 0.03638 0.02682 -0.0459 0.9835 0.0959
-6.250 -0.5671 0.03528 0.02566 -0.0466 0.9771 0.0994
-6.000 -0.5408 0.03412 0.02423 -0.0472 0.9705 0.1060
-5.750 -0.5117 0.03329 0.02333 -0.0483 0.9643 0.1133
-5.500 -0.4868 0.03228 0.02210 -0.0483 0.9569 0.1218
-5.250 -0.4574 0.03138 0.02099 -0.0492 0.9508 0.1338
-5.000 -0.4328 0.03060 0.02013 -0.0491 0.9434 0.1503
-4.750 -0.4042 0.02993 0.01950 -0.0499 0.9377 0.1738
-4.500 -0.3802 0.02944 0.01898 -0.0497 0.9301 0.1997
-4.250 -0.3480 0.02926 0.01875 -0.0510 0.9247 0.2281
-4.000 -0.3267 0.02933 0.01886 -0.0500 0.9162 0.2486
-3.750 -0.2954 0.02951 0.01894 -0.0509 0.9107 0.2735
-3.500 -0.2753 0.02993 0.01935 -0.0496 0.9027 0.2933
-3.250 -0.2465 0.03023 0.01952 -0.0500 0.8968 0.3162
-3.000 -0.2209 0.03027 0.01943 -0.0497 0.8902 0.3309
-2.750 -0.1939 0.03014 0.01917 -0.0498 0.8835 0.3426
-2.500 -0.1586 0.02992 0.01877 -0.0514 0.8789 0.3572
-2.250 -0.1370 0.02983 0.01855 -0.0505 0.8701 0.3698
-2.000 -0.0993 0.02953 0.01807 -0.0523 0.8642 0.3851
-1.750 -0.0720 0.02940 0.01779 -0.0524 0.8550 0.3992
-1.500 -0.0318 0.02904 0.01729 -0.0545 0.8484 0.4166
-1.250 -0.0031 0.02885 0.01699 -0.0547 0.8381 0.4318
-1.000 0.0406 0.02839 0.01641 -0.0573 0.8321 0.4493
-0.750 0.0664 0.02830 0.01625 -0.0571 0.8219 0.4628
-0.500 0.1082 0.02792 0.01581 -0.0595 0.8168 0.4798
-0.250 0.1321 0.02795 0.01583 -0.0590 0.8074 0.4943
0.000 0.1712 0.02760 0.01551 -0.0610 0.8017 0.5152
0.250 0.1971 0.02754 0.01554 -0.0608 0.7930 0.5369
0.500 0.2344 0.02716 0.01531 -0.0625 0.7866 0.5632
0.750 0.2630 0.02700 0.01534 -0.0627 0.7781 0.5875
1.000 0.2999 0.02661 0.01521 -0.0642 0.7710 0.6194
1.250 0.3409 0.02612 0.01525 -0.0666 0.7634 0.6965
1.500 0.4546 0.02576 0.01521 -0.0839 0.7586 1.0000
1.750 0.4946 0.02561 0.01493 -0.0858 0.7520 1.0000
2.000 0.5132 0.02594 0.01518 -0.0842 0.7402 1.0000
2.250 0.5355 0.02619 0.01535 -0.0831 0.7293 1.0000
2.500 0.5748 0.02598 0.01507 -0.0848 0.7220 1.0000
2.750 0.5924 0.02633 0.01538 -0.0829 0.7097 1.0000
3.000 0.6150 0.02656 0.01558 -0.0818 0.6985 1.0000
3.250 0.6543 0.02635 0.01534 -0.0833 0.6911 1.0000
3.500 0.6727 0.02670 0.01569 -0.0815 0.6787 1.0000
3.750 0.6950 0.02698 0.01597 -0.0804 0.6672 1.0000
4.000 0.7311 0.02690 0.01589 -0.0814 0.6589 1.0000
4.250 0.7518 0.02727 0.01628 -0.0800 0.6473 1.0000
4.500 0.7727 0.02767 0.01673 -0.0787 0.6361 1.0000
4.750 0.8110 0.02758 0.01666 -0.0801 0.6282 1.0000
5.000 0.8239 0.02826 0.01740 -0.0776 0.6160 1.0000
5.250 0.8440 0.02876 0.01796 -0.0762 0.6055 1.0000
5.500 0.8754 0.02891 0.01818 -0.0765 0.5970 1.0000
5.750 0.8852 0.02974 0.01910 -0.0736 0.5856 1.0000
6.000 0.9083 0.03016 0.01960 -0.0727 0.5763 1.0000
6.250 0.9277 0.03066 0.02022 -0.0712 0.5666 1.0000
6.500 0.9378 0.03148 0.02114 -0.0683 0.5560 1.0000
6.750 0.9671 0.03160 0.02136 -0.0682 0.5475 1.0000
7.000 0.9754 0.03241 0.02228 -0.0650 0.5364 1.0000
7.250 0.9860 0.03312 0.02311 -0.0622 0.5257 1.0000
7.500 1.0107 0.03325 0.02339 -0.0612 0.5159 1.0000
7.750 1.0254 0.03373 0.02399 -0.0589 0.5053 1.0000
8.000 1.0338 0.03446 0.02485 -0.0557 0.4946 1.0000
8.250 1.0562 0.03467 0.02520 -0.0544 0.4844 1.0000
8.500 1.0854 0.03463 0.02532 -0.0539 0.4737 1.0000
8.750 1.0919 0.03546 0.02633 -0.0505 0.4623 1.0000
9.000 1.1082 0.03588 0.02691 -0.0483 0.4499 1.0000
9.250 1.1253 0.03590 0.02701 -0.0458 0.4326 1.0000
9.500 1.1332 0.03572 0.02673 -0.0417 0.4069 1.0000
9.750 1.1238 0.03651 0.02750 -0.0361 0.3827 1.0000
10.000 1.1122 0.03764 0.02862 -0.0309 0.3577 1.0000
10.250 1.1005 0.03915 0.03018 -0.0266 0.3321 1.0000
10.500 1.0901 0.04107 0.03221 -0.0232 0.3057 1.0000
10.750 1.0839 0.04292 0.03411 -0.0203 0.2750 1.0000
11.000 1.0777 0.04492 0.03593 -0.0177 0.2366 1.0000
11.250 1.0678 0.04751 0.03821 -0.0153 0.1980 1.0000
11.500 1.0558 0.05074 0.04120 -0.0135 0.1642 1.0000
11.750 1.0406 0.05460 0.04485 -0.0121 0.1333 1.0000
12.000 1.0267 0.05864 0.04871 -0.0111 0.1126 1.0000
12.250 1.0142 0.06271 0.05263 -0.0105 0.0984 1.0000
12.500 1.0040 0.06668 0.05654 -0.0101 0.0876 1.0000
12.750 0.9963 0.07046 0.06029 -0.0097 0.0790 1.0000
13.000 0.9890 0.07424 0.06400 -0.0095 0.0735 1.0000
13.250 0.9873 0.07742 0.06726 -0.0091 0.0679 1.0000
13.500 0.9865 0.08049 0.07036 -0.0087 0.0641 1.0000
13.750 0.9857 0.08353 0.07335 -0.0084 0.0609 1.0000
14.000 0.9897 0.08611 0.07612 -0.0078 0.0571 1.0000
14.250 0.9930 0.08878 0.07887 -0.0074 0.0540 1.0000
14.500 0.9961 0.09139 0.08151 -0.0071 0.0515 1.0000
14.750 1.0035 0.09352 0.08372 -0.0062 0.0495 1.0000
15.000 1.0116 0.09585 0.08630 -0.0054 0.0477 1.0000
15.250 1.0167 0.09868 0.08934 -0.0051 0.0461 1.0000
15.500 1.0195 0.10184 0.09269 -0.0052 0.0447 1.0000
15.750 1.0208 0.10524 0.09625 -0.0056 0.0435 1.0000
16.000 1.0223 0.10856 0.09966 -0.0061 0.0421 1.0000
16.250 1.0273 0.11136 0.10251 -0.0061 0.0410 1.0000
16.500 1.0175 0.11700 0.10840 -0.0082 0.0406 1.0000
16.750 1.0050 0.12330 0.11495 -0.0111 0.0403 1.0000
17.000 0.9901 0.13041 0.12229 -0.0146 0.0402 1.0000
17.250 0.9742 0.13810 0.13019 -0.0187 0.0403 1.0000
17.500 0.9565 0.14669 0.13895 -0.0235 0.0405 1.0000
17.750 0.9398 0.15571 0.14809 -0.0285 0.0407 1.0000
18.000 0.9241 0.16513 0.15758 -0.0337 0.0409 1.0000
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