USA 28 AIRFOIL (usa28-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 28 AIRFOIL (usa28-il) Reynolds number: 200,000 Max Cl/Cd: 72.07 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa28-il-200000-n5.txt Download as CSV file: xf-usa28-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6241 0.08604 0.08213 -0.0584 1.0000 0.0286
-13.000 -0.6823 0.07271 0.06866 -0.0662 1.0000 0.0281
-12.750 -0.7218 0.06377 0.05959 -0.0714 1.0000 0.0278
-12.500 -0.7526 0.05674 0.05244 -0.0754 1.0000 0.0278
-12.250 -0.7798 0.05041 0.04597 -0.0795 1.0000 0.0278
-12.000 -0.8067 0.04499 0.04038 -0.0829 1.0000 0.0278
-11.750 -0.8323 0.04252 0.03778 -0.0794 1.0000 0.0278
-11.500 -0.8525 0.04062 0.03572 -0.0749 1.0000 0.0282
-11.250 -0.8603 0.03850 0.03338 -0.0722 0.9992 0.0287
-11.000 -0.8413 0.03575 0.03026 -0.0746 0.9941 0.0297
-10.750 -0.8182 0.03420 0.02865 -0.0761 0.9892 0.0308
-10.500 -0.7910 0.03296 0.02731 -0.0780 0.9852 0.0321
-10.250 -0.7694 0.03159 0.02577 -0.0785 0.9789 0.0334
-10.000 -0.7452 0.03014 0.02407 -0.0794 0.9738 0.0348
-9.750 -0.7250 0.02882 0.02247 -0.0792 0.9669 0.0360
-9.500 -0.7040 0.02753 0.02097 -0.0790 0.9607 0.0371
-9.250 -0.6827 0.02626 0.01965 -0.0788 0.9544 0.0385
-9.000 -0.6605 0.02535 0.01865 -0.0785 0.9479 0.0397
-8.750 -0.6363 0.02446 0.01766 -0.0784 0.9419 0.0410
-8.500 -0.6108 0.02357 0.01664 -0.0785 0.9365 0.0426
-8.250 -0.5876 0.02269 0.01559 -0.0780 0.9298 0.0438
-8.000 -0.5592 0.02185 0.01459 -0.0785 0.9260 0.0450
-7.750 -0.5358 0.02096 0.01361 -0.0780 0.9199 0.0463
-7.500 -0.5106 0.02001 0.01262 -0.0779 0.9147 0.0479
-7.250 -0.4808 0.01922 0.01174 -0.0787 0.9113 0.0493
-7.000 -0.4532 0.01854 0.01099 -0.0789 0.9063 0.0510
-6.750 -0.4252 0.01792 0.01027 -0.0791 0.9008 0.0527
-6.500 -0.3923 0.01732 0.00956 -0.0803 0.8971 0.0551
-6.250 -0.3571 0.01664 0.00877 -0.0821 0.8942 0.0578
-6.000 -0.3312 0.01605 0.00813 -0.0819 0.8865 0.0614
-5.750 -0.2941 0.01549 0.00746 -0.0840 0.8815 0.0658
-5.500 -0.2566 0.01495 0.00682 -0.0862 0.8758 0.0716
-5.250 -0.2230 0.01440 0.00624 -0.0875 0.8679 0.0827
-5.000 -0.1844 0.01376 0.00583 -0.0902 0.8621 0.1267
-4.750 -0.1547 0.01357 0.00558 -0.0906 0.8534 0.1505
-4.500 -0.1167 0.01331 0.00526 -0.0929 0.8471 0.1674
-4.250 -0.0898 0.01313 0.00505 -0.0927 0.8379 0.1788
-4.000 -0.0552 0.01291 0.00479 -0.0941 0.8311 0.1900
-3.750 -0.0303 0.01276 0.00463 -0.0935 0.8220 0.2019
-3.500 0.0012 0.01256 0.00444 -0.0943 0.8151 0.2190
-3.250 0.0250 0.01242 0.00434 -0.0935 0.8057 0.2358
-2.750 0.0781 0.01222 0.00420 -0.0928 0.7881 0.2789
-2.500 0.1046 0.01219 0.00416 -0.0925 0.7800 0.2985
-2.250 0.1304 0.01218 0.00412 -0.0919 0.7715 0.3137
-2.000 0.1557 0.01218 0.00408 -0.0912 0.7625 0.3262
-1.750 0.1823 0.01219 0.00402 -0.0908 0.7539 0.3379
-1.500 0.2070 0.01221 0.00398 -0.0900 0.7453 0.3487
-1.250 0.2337 0.01221 0.00394 -0.0896 0.7372 0.3575
-1.000 0.2576 0.01222 0.00390 -0.0887 0.7275 0.3655
-0.750 0.2832 0.01222 0.00386 -0.0881 0.7187 0.3724
-0.500 0.3084 0.01225 0.00380 -0.0874 0.7090 0.3795
-0.250 0.3331 0.01223 0.00378 -0.0866 0.6999 0.3851
0.000 0.3593 0.01225 0.00374 -0.0861 0.6920 0.3913
0.250 0.3841 0.01226 0.00373 -0.0854 0.6840 0.3968
0.500 0.4102 0.01227 0.00372 -0.0849 0.6765 0.4027
0.750 0.4348 0.01232 0.00374 -0.0842 0.6686 0.4100
1.000 0.4604 0.01233 0.00375 -0.0836 0.6609 0.4166
1.250 0.4847 0.01237 0.00379 -0.0828 0.6526 0.4240
1.750 0.5337 0.01243 0.00387 -0.0813 0.6356 0.4367
2.000 0.5591 0.01249 0.00391 -0.0807 0.6278 0.4428
2.250 0.5820 0.01250 0.00399 -0.0796 0.6188 0.4495
2.500 0.6061 0.01257 0.00406 -0.0787 0.6100 0.4573
2.750 0.6282 0.01259 0.00414 -0.0775 0.5997 0.4646
3.000 0.6506 0.01264 0.00424 -0.0763 0.5894 0.4730
3.250 0.6726 0.01267 0.00432 -0.0750 0.5789 0.4827
3.500 0.6932 0.01269 0.00442 -0.0735 0.5667 0.4932
3.750 0.7132 0.01271 0.00453 -0.0718 0.5530 0.5058
4.000 0.7333 0.01271 0.00464 -0.0701 0.5386 0.5273
4.250 0.8879 0.01256 0.00553 -0.0982 0.5071 0.9891
4.500 0.9276 0.01287 0.00576 -0.1010 0.4901 1.0000
4.750 0.9452 0.01312 0.00596 -0.0988 0.4773 1.0000
5.000 0.9622 0.01340 0.00616 -0.0966 0.4646 1.0000
5.250 0.9790 0.01371 0.00640 -0.0943 0.4524 1.0000
5.500 0.9961 0.01405 0.00668 -0.0921 0.4420 1.0000
5.750 1.0155 0.01432 0.00697 -0.0905 0.4340 1.0000
6.000 1.0346 0.01465 0.00727 -0.0887 0.4270 1.0000
6.250 1.0542 0.01491 0.00758 -0.0871 0.4199 1.0000
6.500 1.0715 0.01529 0.00791 -0.0850 0.4106 1.0000
6.750 1.0851 0.01562 0.00826 -0.0822 0.3959 1.0000
7.000 1.0954 0.01598 0.00858 -0.0787 0.3783 1.0000
7.250 1.1036 0.01625 0.00886 -0.0747 0.3599 1.0000
7.500 1.1132 0.01653 0.00915 -0.0712 0.3412 1.0000
7.750 1.1212 0.01687 0.00947 -0.0673 0.3175 1.0000
8.000 1.1257 0.01737 0.00984 -0.0630 0.2834 1.0000
8.250 1.1245 0.01818 0.01042 -0.0579 0.2401 1.0000
8.500 1.1221 0.01923 0.01122 -0.0529 0.1976 1.0000
8.750 1.1195 0.02046 0.01219 -0.0482 0.1555 1.0000
9.000 1.1166 0.02180 0.01329 -0.0437 0.1127 1.0000
9.250 1.1128 0.02330 0.01454 -0.0394 0.0747 1.0000
9.500 1.1103 0.02482 0.01589 -0.0355 0.0473 1.0000
9.750 1.1127 0.02614 0.01717 -0.0324 0.0371 1.0000
10.000 1.1166 0.02745 0.01849 -0.0296 0.0318 1.0000
10.250 1.1223 0.02869 0.01982 -0.0272 0.0287 1.0000
10.500 1.1257 0.03015 0.02133 -0.0248 0.0265 1.0000
10.750 1.1311 0.03153 0.02280 -0.0227 0.0249 1.0000
11.000 1.1359 0.03302 0.02439 -0.0207 0.0237 1.0000
11.250 1.1395 0.03464 0.02611 -0.0187 0.0226 1.0000
11.500 1.1428 0.03635 0.02791 -0.0170 0.0217 1.0000
11.750 1.1416 0.03851 0.03014 -0.0151 0.0207 1.0000
12.000 1.1416 0.04066 0.03238 -0.0136 0.0200 1.0000
12.250 1.1425 0.04281 0.03463 -0.0122 0.0196 1.0000
12.500 1.1462 0.04477 0.03672 -0.0111 0.0187 1.0000
12.750 1.1468 0.04709 0.03914 -0.0100 0.0180 1.0000
13.000 1.1471 0.04951 0.04165 -0.0091 0.0177 1.0000
13.250 1.1475 0.05198 0.04421 -0.0083 0.0171 1.0000
13.500 1.1479 0.05452 0.04683 -0.0076 0.0168 1.0000
13.750 1.1481 0.05712 0.04951 -0.0069 0.0165 1.0000
14.000 1.1469 0.05991 0.05236 -0.0064 0.0160 1.0000
14.250 1.1465 0.06264 0.05514 -0.0058 0.0157 1.0000
14.500 1.1467 0.06531 0.05785 -0.0052 0.0154 1.0000
14.750 1.1494 0.06781 0.06046 -0.0048 0.0150 1.0000
15.000 1.1521 0.07036 0.06315 -0.0045 0.0146 1.0000
15.250 1.1546 0.07295 0.06586 -0.0043 0.0143 1.0000
15.500 1.1566 0.07568 0.06870 -0.0042 0.0139 1.0000
15.750 1.1585 0.07842 0.07156 -0.0042 0.0135 1.0000
16.000 1.1604 0.08120 0.07444 -0.0040 0.0133 1.0000
16.250 1.1613 0.08416 0.07752 -0.0042 0.0131 1.0000
16.500 1.1613 0.08729 0.08076 -0.0045 0.0128 1.0000
16.750 1.1615 0.09046 0.08404 -0.0048 0.0126 1.0000
17.000 1.1606 0.09383 0.08751 -0.0053 0.0124 1.0000
17.250 1.1592 0.09733 0.09113 -0.0060 0.0122 1.0000
17.500 1.1572 0.10094 0.09486 -0.0068 0.0121 1.0000
17.750 1.1546 0.10470 0.09874 -0.0079 0.0119 1.0000
18.000 1.1512 0.10864 0.10280 -0.0090 0.0118 1.0000
18.250 1.1467 0.11280 0.10707 -0.0103 0.0117 1.0000
18.500 1.1408 0.11732 0.11173 -0.0118 0.0116 1.0000
19.000 1.1221 0.12799 0.12273 -0.0165 0.0114 1.0000
19.250 1.1111 0.13396 0.12888 -0.0196 0.0114 1.0000
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Polar data table (+)
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