USA 28 AIRFOIL (usa28-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 28 AIRFOIL (usa28-il) Reynolds number: 500,000 Max Cl/Cd: 87.81 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa28-il-500000-n5.txt Download as CSV file: xf-usa28-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7402 0.11507 0.11228 -0.0439 1.0000 0.0146
-16.500 -0.7695 0.10598 0.10309 -0.0483 1.0000 0.0145
-16.250 -0.7936 0.09821 0.09523 -0.0521 1.0000 0.0146
-16.000 -0.8174 0.09072 0.08766 -0.0558 1.0000 0.0148
-15.750 -0.8391 0.08385 0.08070 -0.0592 1.0000 0.0149
-15.500 -0.8632 0.07683 0.07360 -0.0626 1.0000 0.0150
-15.250 -0.8863 0.07051 0.06717 -0.0656 1.0000 0.0149
-15.000 -0.9114 0.06420 0.06078 -0.0685 1.0000 0.0150
-14.750 -0.9421 0.05763 0.05410 -0.0714 1.0000 0.0147
-14.500 -0.9712 0.05159 0.04797 -0.0738 1.0000 0.0147
-14.250 -1.0090 0.04486 0.04114 -0.0766 1.0000 0.0146
-14.000 -1.0598 0.03572 0.03177 -0.0823 1.0000 0.0142
-13.750 -1.0796 0.03293 0.02882 -0.0793 1.0000 0.0143
-13.500 -1.0747 0.03078 0.02655 -0.0791 0.9984 0.0147
-13.250 -1.0526 0.02932 0.02501 -0.0807 0.9960 0.0156
-13.000 -1.0290 0.02803 0.02362 -0.0821 0.9938 0.0165
-12.750 -1.0080 0.02678 0.02224 -0.0827 0.9907 0.0173
-12.500 -0.9831 0.02571 0.02102 -0.0836 0.9879 0.0182
-12.250 -0.9566 0.02467 0.01990 -0.0849 0.9857 0.0191
-12.000 -0.9340 0.02387 0.01904 -0.0850 0.9823 0.0200
-11.750 -0.9097 0.02314 0.01823 -0.0852 0.9787 0.0209
-11.500 -0.8816 0.02246 0.01745 -0.0861 0.9762 0.0220
-11.250 -0.8602 0.02178 0.01666 -0.0855 0.9711 0.0228
-11.000 -0.8353 0.02115 0.01589 -0.0856 0.9665 0.0234
-10.750 -0.8178 0.02027 0.01497 -0.0843 0.9588 0.0244
-10.250 -0.7750 0.01917 0.01377 -0.0826 0.9418 0.0262
-10.000 -0.7508 0.01864 0.01316 -0.0823 0.9344 0.0271
-9.750 -0.7242 0.01807 0.01249 -0.0824 0.9284 0.0281
-9.500 -0.6945 0.01749 0.01181 -0.0832 0.9241 0.0288
-9.250 -0.6644 0.01701 0.01123 -0.0839 0.9185 0.0294
-9.000 -0.6343 0.01612 0.01027 -0.0850 0.9137 0.0309
-8.750 -0.5987 0.01550 0.00959 -0.0870 0.9101 0.0320
-8.500 -0.5630 0.01501 0.00902 -0.0890 0.9049 0.0332
-8.250 -0.5242 0.01452 0.00845 -0.0917 0.9000 0.0344
-8.000 -0.4824 0.01400 0.00783 -0.0950 0.8952 0.0354
-7.750 -0.4409 0.01357 0.00729 -0.0983 0.8876 0.0363
-7.250 -0.3622 0.01262 0.00611 -0.1039 0.8671 0.0388
-7.000 -0.3314 0.01228 0.00569 -0.1047 0.8568 0.0403
-6.500 -0.2768 0.01177 0.00501 -0.1047 0.8395 0.0432
-6.000 -0.2256 0.01136 0.00443 -0.1038 0.8220 0.0467
-5.750 -0.2009 0.01111 0.00414 -0.1032 0.8133 0.0504
-5.500 -0.1768 0.01092 0.00390 -0.1024 0.8046 0.0538
-5.250 -0.1520 0.01074 0.00366 -0.1017 0.7973 0.0588
-5.000 -0.1284 0.01052 0.00343 -0.1009 0.7891 0.0661
-4.750 -0.1045 0.01030 0.00318 -0.1000 0.7808 0.0763
-4.500 -0.0827 0.00992 0.00297 -0.0989 0.7715 0.1186
-4.250 -0.0585 0.00980 0.00285 -0.0981 0.7617 0.1363
-4.000 -0.0344 0.00972 0.00273 -0.0972 0.7508 0.1462
-3.750 -0.0105 0.00966 0.00261 -0.0963 0.7389 0.1520
-3.500 0.0133 0.00956 0.00249 -0.0953 0.7274 0.1595
-3.250 0.0375 0.00952 0.00239 -0.0944 0.7167 0.1648
-3.000 0.0610 0.00944 0.00228 -0.0935 0.7060 0.1720
-2.750 0.0851 0.00938 0.00218 -0.0926 0.6954 0.1782
-2.500 0.1087 0.00931 0.00209 -0.0916 0.6853 0.1872
-2.250 0.1318 0.00923 0.00201 -0.0906 0.6748 0.2014
-2.000 0.1555 0.00912 0.00194 -0.0897 0.6660 0.2223
-1.750 0.1790 0.00902 0.00191 -0.0887 0.6587 0.2525
-1.500 0.2034 0.00896 0.00190 -0.0880 0.6519 0.2776
-1.000 0.2528 0.00897 0.00192 -0.0865 0.6385 0.3098
-0.750 0.2779 0.00899 0.00193 -0.0858 0.6326 0.3204
-0.500 0.3029 0.00903 0.00194 -0.0851 0.6268 0.3294
-0.250 0.3278 0.00905 0.00196 -0.0844 0.6199 0.3365
0.000 0.3525 0.00910 0.00198 -0.0836 0.6137 0.3430
0.250 0.3777 0.00913 0.00200 -0.0830 0.6078 0.3496
0.500 0.4024 0.00915 0.00203 -0.0822 0.6016 0.3554
0.750 0.4268 0.00921 0.00206 -0.0814 0.5957 0.3608
1.000 0.4518 0.00922 0.00209 -0.0807 0.5892 0.3657
1.250 0.4755 0.00926 0.00213 -0.0798 0.5817 0.3715
1.500 0.4995 0.00930 0.00217 -0.0789 0.5732 0.3762
1.750 0.5223 0.00935 0.00220 -0.0777 0.5633 0.3800
2.000 0.5447 0.00938 0.00225 -0.0765 0.5507 0.3848
2.250 0.5662 0.00944 0.00229 -0.0750 0.5355 0.3891
2.500 0.5852 0.00954 0.00233 -0.0730 0.5118 0.3926
2.750 0.5998 0.00971 0.00237 -0.0702 0.4832 0.3957
3.000 0.6161 0.00987 0.00247 -0.0677 0.4636 0.3991
3.250 0.6346 0.01003 0.00258 -0.0657 0.4508 0.4037
3.500 0.6541 0.01019 0.00270 -0.0639 0.4415 0.4084
3.750 0.6750 0.01030 0.00283 -0.0624 0.4339 0.4134
4.000 0.6949 0.01045 0.00298 -0.0608 0.4271 0.4183
4.250 0.7167 0.01056 0.00311 -0.0595 0.4219 0.4233
4.500 0.7378 0.01068 0.00326 -0.0581 0.4164 0.4281
4.750 0.7571 0.01086 0.00345 -0.0563 0.4094 0.4347
5.250 0.7980 0.01113 0.00379 -0.0533 0.3959 0.4497
5.750 0.8411 0.01132 0.00413 -0.0508 0.3875 0.4687
6.000 0.8608 0.01143 0.00432 -0.0492 0.3816 0.4882
6.250 0.8785 0.01144 0.00453 -0.0472 0.3762 0.5461
6.750 1.0739 0.01223 0.00601 -0.0797 0.2831 0.9977
7.250 1.0924 0.01389 0.00709 -0.0733 0.1820 1.0000
7.500 1.0962 0.01466 0.00766 -0.0689 0.1446 1.0000
7.750 1.0995 0.01548 0.00827 -0.0645 0.1072 1.0000
8.000 1.1024 0.01635 0.00895 -0.0602 0.0742 1.0000
8.250 1.1031 0.01736 0.00977 -0.0556 0.0400 1.0000
8.500 1.1122 0.01802 0.01039 -0.0525 0.0300 1.0000
8.750 1.1223 0.01866 0.01102 -0.0496 0.0241 1.0000
9.000 1.1330 0.01930 0.01166 -0.0469 0.0209 1.0000
9.250 1.1449 0.01989 0.01229 -0.0445 0.0191 1.0000
9.500 1.1560 0.02055 0.01299 -0.0420 0.0175 1.0000
9.750 1.1663 0.02128 0.01376 -0.0396 0.0164 1.0000
10.000 1.1758 0.02210 0.01461 -0.0371 0.0150 1.0000
10.250 1.1864 0.02288 0.01545 -0.0349 0.0145 1.0000
10.500 1.1963 0.02374 0.01637 -0.0327 0.0139 1.0000
10.750 1.2058 0.02466 0.01735 -0.0306 0.0133 1.0000
11.000 1.2140 0.02570 0.01845 -0.0285 0.0129 1.0000
11.250 1.2215 0.02683 0.01962 -0.0264 0.0122 1.0000
11.500 1.2274 0.02813 0.02099 -0.0243 0.0118 1.0000
11.750 1.2309 0.02966 0.02260 -0.0222 0.0114 1.0000
12.000 1.2394 0.03087 0.02387 -0.0206 0.0110 1.0000
12.250 1.2456 0.03229 0.02536 -0.0189 0.0107 1.0000
12.500 1.2504 0.03389 0.02705 -0.0173 0.0105 1.0000
12.750 1.2556 0.03550 0.02872 -0.0159 0.0100 1.0000
13.000 1.2597 0.03726 0.03056 -0.0145 0.0098 1.0000
13.250 1.2639 0.03910 0.03246 -0.0133 0.0095 1.0000
13.500 1.2669 0.04109 0.03454 -0.0122 0.0094 1.0000
13.750 1.2676 0.04338 0.03692 -0.0112 0.0093 1.0000
14.000 1.2687 0.04570 0.03931 -0.0103 0.0089 1.0000
14.250 1.2674 0.04837 0.04205 -0.0095 0.0088 1.0000
14.500 1.2660 0.05110 0.04487 -0.0089 0.0087 1.0000
14.750 1.2621 0.05418 0.04803 -0.0084 0.0084 1.0000
15.000 1.2623 0.05691 0.05086 -0.0080 0.0083 1.0000
15.250 1.2605 0.05991 0.05395 -0.0078 0.0082 1.0000
15.500 1.2627 0.06251 0.05665 -0.0077 0.0081 1.0000
15.750 1.2610 0.06563 0.05986 -0.0077 0.0080 1.0000
16.000 1.2617 0.06855 0.06287 -0.0078 0.0077 1.0000
16.250 1.2581 0.07205 0.06647 -0.0080 0.0077 1.0000
16.500 1.2568 0.07535 0.06987 -0.0084 0.0075 1.0000
16.750 1.2542 0.07885 0.07347 -0.0089 0.0074 1.0000
17.000 1.2515 0.08247 0.07717 -0.0095 0.0073 1.0000
17.250 1.2491 0.08610 0.08089 -0.0103 0.0071 1.0000
17.500 1.2448 0.08999 0.08488 -0.0110 0.0071 1.0000
17.750 1.2434 0.09356 0.08853 -0.0120 0.0069 1.0000
18.000 1.2390 0.09754 0.09260 -0.0129 0.0069 1.0000
18.250 1.2356 0.10148 0.09662 -0.0141 0.0068 1.0000
18.500 1.2314 0.10552 0.10076 -0.0152 0.0067 1.0000
18.750 1.2284 0.10945 0.10476 -0.0165 0.0066 1.0000
19.000 1.2229 0.11377 0.10916 -0.0179 0.0065 1.0000
19.250 1.2181 0.11801 0.11349 -0.0194 0.0065 1.0000
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