USA 28 AIRFOIL (usa28-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 28 AIRFOIL (usa28-il) Reynolds number: 500,000 Max Cl/Cd: 97.27 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa28-il-500000.txt Download as CSV file: xf-usa28-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7934 0.06924 0.06618 -0.0689 1.0000 0.0220
-14.000 -0.8216 0.06224 0.05905 -0.0729 1.0000 0.0220
-13.750 -0.8463 0.05611 0.05280 -0.0763 1.0000 0.0220
-13.500 -0.8648 0.05102 0.04763 -0.0789 1.0000 0.0222
-13.250 -0.8857 0.04524 0.04170 -0.0828 1.0000 0.0221
-13.000 -0.9040 0.03992 0.03624 -0.0873 1.0000 0.0223
-12.750 -0.9219 0.03762 0.03383 -0.0849 1.0000 0.0224
-12.500 -0.9380 0.03640 0.03257 -0.0802 1.0000 0.0226
-12.250 -0.9485 0.03523 0.03134 -0.0757 1.0000 0.0228
-12.000 -0.9545 0.03408 0.03012 -0.0718 1.0000 0.0231
-11.750 -0.9345 0.03310 0.02906 -0.0725 0.9981 0.0238
-11.500 -0.9063 0.03181 0.02762 -0.0748 0.9950 0.0248
-11.250 -0.8806 0.03027 0.02586 -0.0765 0.9911 0.0257
-11.000 -0.8512 0.02928 0.02463 -0.0783 0.9874 0.0264
-10.750 -0.8297 0.02651 0.02173 -0.0798 0.9847 0.0276
-10.500 -0.8043 0.02567 0.02085 -0.0803 0.9798 0.0285
-10.250 -0.7757 0.02475 0.01983 -0.0814 0.9763 0.0295
-10.000 -0.7441 0.02405 0.01901 -0.0830 0.9741 0.0308
-9.750 -0.7199 0.02327 0.01808 -0.0828 0.9686 0.0317
-9.500 -0.6954 0.02175 0.01638 -0.0831 0.9643 0.0328
-9.250 -0.6670 0.02045 0.01504 -0.0842 0.9619 0.0340
-9.000 -0.6449 0.01985 0.01442 -0.0834 0.9550 0.0352
-8.750 -0.6155 0.01919 0.01367 -0.0841 0.9514 0.0365
-8.500 -0.5840 0.01847 0.01286 -0.0852 0.9491 0.0378
-8.250 -0.5611 0.01794 0.01224 -0.0843 0.9420 0.0387
-8.000 -0.5346 0.01686 0.01106 -0.0844 0.9382 0.0399
-7.750 -0.5063 0.01582 0.00997 -0.0849 0.9356 0.0415
-7.500 -0.4823 0.01523 0.00934 -0.0843 0.9287 0.0427
-7.250 -0.4508 0.01462 0.00868 -0.0852 0.9245 0.0443
-7.000 -0.4142 0.01403 0.00801 -0.0871 0.9217 0.0461
-6.750 -0.3827 0.01356 0.00747 -0.0879 0.9153 0.0472
-6.500 -0.3472 0.01268 0.00650 -0.0898 0.9105 0.0496
-6.250 -0.3037 0.01208 0.00587 -0.0934 0.9067 0.0527
-6.000 -0.2670 0.01168 0.00539 -0.0954 0.8994 0.0555
-5.750 -0.2244 0.01119 0.00482 -0.0988 0.8938 0.0595
-5.500 -0.1886 0.01074 0.00433 -0.1007 0.8860 0.0660
-5.250 -0.1543 0.01028 0.00383 -0.1022 0.8778 0.0785
-5.000 -0.1268 0.00973 0.00356 -0.1024 0.8685 0.1397
-4.750 -0.0930 0.00961 0.00340 -0.1037 0.8601 0.1603
-4.500 -0.0676 0.00951 0.00327 -0.1032 0.8507 0.1709
-4.000 -0.0132 0.00930 0.00299 -0.1028 0.8336 0.1884
-3.750 0.0154 0.00923 0.00286 -0.1029 0.8254 0.1971
-3.500 0.0386 0.00911 0.00275 -0.1018 0.8156 0.2062
-3.250 0.0639 0.00900 0.00263 -0.1012 0.8065 0.2169
-3.000 0.0886 0.00890 0.00252 -0.1004 0.7965 0.2304
-2.750 0.1114 0.00876 0.00246 -0.0993 0.7867 0.2544
-2.500 0.1366 0.00867 0.00243 -0.0987 0.7779 0.2888
-2.250 0.1596 0.00865 0.00246 -0.0975 0.7680 0.3161
-2.000 0.1846 0.00869 0.00248 -0.0967 0.7589 0.3339
-1.750 0.2088 0.00872 0.00248 -0.0958 0.7492 0.3454
-1.500 0.2330 0.00875 0.00247 -0.0949 0.7397 0.3540
-1.250 0.2580 0.00880 0.00246 -0.0941 0.7308 0.3619
-1.000 0.2815 0.00882 0.00244 -0.0930 0.7206 0.3685
-0.750 0.3061 0.00884 0.00243 -0.0922 0.7120 0.3745
-0.500 0.3307 0.00889 0.00243 -0.0914 0.7035 0.3806
-0.250 0.3557 0.00890 0.00242 -0.0907 0.6960 0.3858
0.000 0.3804 0.00893 0.00243 -0.0899 0.6884 0.3914
0.250 0.4057 0.00900 0.00244 -0.0892 0.6814 0.3969
0.500 0.4302 0.00899 0.00244 -0.0884 0.6737 0.4015
0.750 0.4552 0.00903 0.00246 -0.0877 0.6665 0.4062
1.000 0.4796 0.00907 0.00248 -0.0869 0.6588 0.4111
1.250 0.5049 0.00912 0.00251 -0.0863 0.6520 0.4161
1.500 0.5286 0.00913 0.00255 -0.0853 0.6444 0.4215
1.750 0.5537 0.00921 0.00258 -0.0846 0.6370 0.4264
2.000 0.5765 0.00922 0.00263 -0.0835 0.6285 0.4313
2.250 0.6004 0.00927 0.00267 -0.0825 0.6203 0.4368
2.500 0.6225 0.00929 0.00272 -0.0812 0.6107 0.4417
2.750 0.6451 0.00934 0.00276 -0.0800 0.6014 0.4462
3.000 0.6659 0.00936 0.00282 -0.0784 0.5902 0.4524
3.250 0.6861 0.00939 0.00287 -0.0767 0.5773 0.4589
3.500 0.7049 0.00941 0.00291 -0.0747 0.5624 0.4666
3.750 0.7225 0.00945 0.00296 -0.0724 0.5447 0.4739
4.000 0.7370 0.00950 0.00300 -0.0694 0.5241 0.4829
4.250 0.7511 0.00959 0.00306 -0.0664 0.5026 0.4937
4.500 0.7644 0.00969 0.00317 -0.0633 0.4841 0.5134
4.750 0.7730 0.00953 0.00335 -0.0593 0.4698 0.6336
5.000 0.9999 0.01028 0.00471 -0.1045 0.4387 1.0000
5.250 1.0180 0.01053 0.00492 -0.1025 0.4277 1.0000
5.500 1.0350 0.01083 0.00514 -0.1002 0.4171 1.0000
5.750 1.0532 0.01102 0.00534 -0.0982 0.4059 1.0000
6.000 1.0711 0.01123 0.00554 -0.0961 0.3955 1.0000
6.250 1.0870 0.01149 0.00575 -0.0937 0.3852 1.0000
6.500 1.1054 0.01161 0.00593 -0.0917 0.3758 1.0000
6.750 1.1201 0.01179 0.00611 -0.0889 0.3655 1.0000
7.000 1.1331 0.01198 0.00628 -0.0859 0.3509 1.0000
7.250 1.1463 0.01219 0.00646 -0.0828 0.3311 1.0000
7.500 1.1560 0.01252 0.00670 -0.0792 0.3018 1.0000
7.750 1.1577 0.01318 0.00710 -0.0742 0.2539 1.0000
8.000 1.1535 0.01420 0.00778 -0.0684 0.1972 1.0000
8.250 1.1471 0.01544 0.00865 -0.0623 0.1373 1.0000
8.500 1.1362 0.01697 0.00975 -0.0558 0.0712 1.0000
8.750 1.1315 0.01830 0.01083 -0.0505 0.0374 1.0000
9.000 1.1377 0.01915 0.01168 -0.0470 0.0312 1.0000
9.250 1.1472 0.01987 0.01245 -0.0442 0.0287 1.0000
9.500 1.1518 0.02089 0.01350 -0.0408 0.0262 1.0000
9.750 1.1612 0.02169 0.01436 -0.0382 0.0249 1.0000
10.000 1.1698 0.02256 0.01530 -0.0356 0.0240 1.0000
10.250 1.1773 0.02355 0.01633 -0.0331 0.0227 1.0000
10.500 1.1812 0.02481 0.01764 -0.0303 0.0218 1.0000
10.750 1.1788 0.02655 0.01946 -0.0270 0.0209 1.0000
11.000 1.1875 0.02764 0.02062 -0.0251 0.0204 1.0000
11.250 1.1935 0.02897 0.02202 -0.0230 0.0199 1.0000
11.500 1.1982 0.03043 0.02356 -0.0210 0.0191 1.0000
11.750 1.2034 0.03192 0.02510 -0.0192 0.0186 1.0000
12.000 1.2056 0.03371 0.02696 -0.0173 0.0183 1.0000
12.250 1.2086 0.03549 0.02880 -0.0156 0.0179 1.0000
12.500 1.2079 0.03766 0.03101 -0.0139 0.0174 1.0000
12.750 1.2030 0.04027 0.03369 -0.0120 0.0170 1.0000
13.000 1.2022 0.04258 0.03607 -0.0104 0.0167 1.0000
13.250 1.2080 0.04437 0.03795 -0.0094 0.0165 1.0000
13.500 1.2119 0.04637 0.04004 -0.0083 0.0163 1.0000
13.750 1.2172 0.04830 0.04205 -0.0075 0.0159 1.0000
14.000 1.2221 0.05030 0.04412 -0.0067 0.0155 1.0000
14.250 1.2265 0.05237 0.04626 -0.0060 0.0150 1.0000
14.500 1.2301 0.05455 0.04851 -0.0052 0.0147 1.0000
14.750 1.2342 0.05669 0.05071 -0.0045 0.0146 1.0000
15.000 1.2377 0.05892 0.05301 -0.0039 0.0143 1.0000
15.250 1.2415 0.06114 0.05528 -0.0033 0.0141 1.0000
15.500 1.2456 0.06317 0.05730 -0.0021 0.0135 1.0000
15.750 1.2516 0.06514 0.05934 -0.0013 0.0135 1.0000
16.000 1.2583 0.06704 0.06132 0.0003 0.0133 1.0000
16.250 1.2567 0.07012 0.06456 0.0001 0.0131 1.0000
16.500 1.2587 0.07277 0.06733 0.0005 0.0131 1.0000
16.750 1.2566 0.07603 0.07075 0.0004 0.0129 1.0000
17.000 1.2540 0.07943 0.07429 0.0000 0.0128 1.0000
17.250 1.2518 0.08276 0.07776 0.0000 0.0128 1.0000
17.500 1.2456 0.08682 0.08199 -0.0009 0.0126 1.0000
17.750 1.2392 0.09098 0.08632 -0.0016 0.0126 1.0000
18.000 1.2314 0.09551 0.09100 -0.0030 0.0124 1.0000
18.250 1.2211 0.10046 0.09613 -0.0043 0.0124 1.0000
18.500 1.2120 0.10539 0.10121 -0.0062 0.0124 1.0000
18.750 1.2008 0.11085 0.10683 -0.0086 0.0121 1.0000
19.000 1.1871 0.11677 0.11293 -0.0109 0.0123 1.0000
19.250 1.1752 0.12271 0.11902 -0.0140 0.0119 1.0000
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Polar data table (+)
Polar graphs
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