USA 28 AIRFOIL (usa28-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 28 AIRFOIL (usa28-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.54 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa28-il-1000000.txt Download as CSV file: xf-usa28-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.7792 0.12654 0.12439 -0.0378 1.0000 0.0138
-17.750 -0.8038 0.11800 0.11575 -0.0421 1.0000 0.0139
-17.500 -0.8223 0.11102 0.10869 -0.0455 1.0000 0.0140
-17.250 -0.8460 0.10348 0.10105 -0.0493 1.0000 0.0142
-17.000 -0.8673 0.09651 0.09401 -0.0528 1.0000 0.0144
-16.750 -0.8882 0.08976 0.08719 -0.0562 1.0000 0.0145
-16.500 -0.9066 0.08357 0.08093 -0.0592 1.0000 0.0146
-16.250 -0.9292 0.07695 0.07423 -0.0625 1.0000 0.0147
-16.000 -0.9511 0.07070 0.06790 -0.0655 1.0000 0.0148
-15.750 -0.9761 0.06453 0.06164 -0.0683 1.0000 0.0148
-15.500 -1.0066 0.05794 0.05497 -0.0713 1.0000 0.0149
-15.250 -1.0403 0.05141 0.04833 -0.0741 1.0000 0.0147
-15.000 -1.0822 0.04422 0.04102 -0.0771 1.0000 0.0146
-14.750 -1.1299 0.03503 0.03163 -0.0836 1.0000 0.0141
-14.500 -1.1527 0.03106 0.02747 -0.0822 1.0000 0.0142
-14.250 -1.1722 0.02914 0.02545 -0.0771 1.0000 0.0145
-14.000 -1.1757 0.02761 0.02384 -0.0737 1.0000 0.0147
-13.750 -1.1610 0.02644 0.02261 -0.0731 0.9992 0.0152
-13.500 -1.1326 0.02558 0.02169 -0.0747 0.9974 0.0158
-13.250 -1.1043 0.02466 0.02069 -0.0762 0.9955 0.0162
-13.000 -1.0732 0.02400 0.01995 -0.0780 0.9943 0.0169
-12.750 -1.0452 0.02340 0.01926 -0.0788 0.9918 0.0173
-12.500 -1.0227 0.02188 0.01764 -0.0796 0.9886 0.0182
-12.250 -0.9928 0.02116 0.01689 -0.0809 0.9868 0.0189
-12.000 -0.9613 0.02062 0.01630 -0.0824 0.9855 0.0195
-11.750 -0.9281 0.02018 0.01581 -0.0841 0.9847 0.0203
-11.500 -0.9043 0.01957 0.01514 -0.0838 0.9806 0.0209
-11.250 -0.8742 0.01912 0.01461 -0.0847 0.9779 0.0214
-11.000 -0.8482 0.01794 0.01333 -0.0854 0.9754 0.0224
-10.750 -0.8159 0.01738 0.01276 -0.0869 0.9741 0.0232
-10.500 -0.7933 0.01690 0.01224 -0.0861 0.9689 0.0239
-10.250 -0.7647 0.01651 0.01182 -0.0865 0.9652 0.0248
-10.000 -0.7335 0.01610 0.01135 -0.0875 0.9630 0.0256
-9.750 -0.7087 0.01572 0.01091 -0.0870 0.9577 0.0261
-9.500 -0.6870 0.01492 0.01004 -0.0862 0.9508 0.0270
-9.250 -0.6680 0.01421 0.00928 -0.0846 0.9416 0.0280
-9.000 -0.6397 0.01373 0.00877 -0.0849 0.9365 0.0289
-8.750 -0.6099 0.01329 0.00829 -0.0855 0.9305 0.0298
-8.500 -0.5740 0.01286 0.00781 -0.0874 0.9249 0.0308
-8.250 -0.5328 0.01245 0.00734 -0.0904 0.9208 0.0317
-8.000 -0.4915 0.01202 0.00684 -0.0935 0.9145 0.0323
-7.750 -0.4490 0.01118 0.00590 -0.0972 0.9082 0.0344
-7.500 -0.4037 0.01080 0.00545 -0.1013 0.9001 0.0357
-7.250 -0.3568 0.01049 0.00506 -0.1057 0.8920 0.0373
-7.000 -0.3220 0.01026 0.00475 -0.1073 0.8810 0.0384
-6.750 -0.2905 0.01009 0.00449 -0.1082 0.8709 0.0391
-6.500 -0.2646 0.00973 0.00403 -0.1079 0.8607 0.0414
-6.250 -0.2401 0.00950 0.00376 -0.1072 0.8517 0.0436
-5.750 -0.1897 0.00920 0.00335 -0.1060 0.8353 0.0473
-5.250 -0.1421 0.00879 0.00287 -0.1042 0.8189 0.0571
-4.750 -0.0974 0.00817 0.00236 -0.1019 0.8023 0.0983
-4.500 -0.0740 0.00794 0.00226 -0.1010 0.7941 0.1392
-4.250 -0.0496 0.00788 0.00218 -0.1001 0.7853 0.1483
-4.000 -0.0254 0.00780 0.00208 -0.0993 0.7767 0.1564
-3.750 -0.0013 0.00774 0.00199 -0.0983 0.7668 0.1621
-3.500 0.0226 0.00770 0.00191 -0.0974 0.7559 0.1662
-3.250 0.0456 0.00764 0.00181 -0.0962 0.7439 0.1722
-3.000 0.0688 0.00760 0.00173 -0.0951 0.7316 0.1779
-2.750 0.0922 0.00754 0.00165 -0.0941 0.7190 0.1848
-2.500 0.1156 0.00749 0.00157 -0.0930 0.7068 0.1917
-2.250 0.1385 0.00744 0.00150 -0.0918 0.6947 0.2030
-2.000 0.1610 0.00735 0.00144 -0.0906 0.6837 0.2246
-1.750 0.1837 0.00719 0.00141 -0.0896 0.6744 0.2708
-1.500 0.2075 0.00714 0.00142 -0.0886 0.6668 0.3024
-1.250 0.2325 0.00714 0.00144 -0.0879 0.6595 0.3211
-1.000 0.2572 0.00719 0.00146 -0.0871 0.6525 0.3318
-0.750 0.2829 0.00719 0.00147 -0.0866 0.6465 0.3390
-0.500 0.3080 0.00723 0.00149 -0.0859 0.6403 0.3460
-0.250 0.3335 0.00728 0.00150 -0.0853 0.6347 0.3513
0.000 0.3589 0.00728 0.00152 -0.0847 0.6292 0.3568
0.250 0.3838 0.00733 0.00154 -0.0839 0.6233 0.3619
0.500 0.4094 0.00737 0.00156 -0.0834 0.6182 0.3659
0.750 0.4345 0.00737 0.00158 -0.0827 0.6126 0.3703
1.000 0.4587 0.00742 0.00161 -0.0818 0.6065 0.3746
1.250 0.4838 0.00744 0.00164 -0.0811 0.6002 0.3793
1.500 0.5082 0.00749 0.00167 -0.0803 0.5930 0.3830
1.750 0.5316 0.00750 0.00170 -0.0792 0.5857 0.3880
2.000 0.5547 0.00752 0.00173 -0.0781 0.5766 0.3922
2.250 0.5770 0.00756 0.00176 -0.0768 0.5659 0.3956
2.500 0.5977 0.00761 0.00178 -0.0752 0.5513 0.3996
2.750 0.6162 0.00768 0.00180 -0.0731 0.5289 0.4035
3.000 0.6318 0.00786 0.00186 -0.0704 0.4931 0.4073
3.250 0.6481 0.00812 0.00197 -0.0679 0.4640 0.4104
3.500 0.6676 0.00831 0.00209 -0.0661 0.4491 0.4135
3.750 0.6882 0.00843 0.00220 -0.0646 0.4388 0.4178
4.000 0.7089 0.00856 0.00233 -0.0630 0.4299 0.4224
4.250 0.7293 0.00872 0.00247 -0.0614 0.4209 0.4277
4.500 0.7507 0.00883 0.00259 -0.0601 0.4149 0.4327
4.750 0.7727 0.00890 0.00271 -0.0588 0.4104 0.4399
5.000 0.7939 0.00902 0.00285 -0.0574 0.4058 0.4462
5.250 0.8146 0.00913 0.00299 -0.0559 0.3998 0.4555
5.500 0.8366 0.00919 0.00311 -0.0547 0.3933 0.4670
5.750 0.8554 0.00932 0.00328 -0.0529 0.3859 0.4884
6.000 0.8704 0.00900 0.00343 -0.0503 0.3779 0.6611
6.250 1.0827 0.00952 0.00455 -0.0924 0.3382 0.9959
6.500 1.1408 0.00996 0.00482 -0.0996 0.2962 1.0000
6.750 1.1458 0.01051 0.00513 -0.0950 0.2527 1.0000
7.000 1.1447 0.01119 0.00556 -0.0892 0.2061 1.0000
7.250 1.1431 0.01197 0.00607 -0.0834 0.1586 1.0000
7.500 1.1437 0.01271 0.00657 -0.0781 0.1181 1.0000
7.750 1.1399 0.01368 0.00725 -0.0721 0.0691 1.0000
8.000 1.1384 0.01461 0.00797 -0.0667 0.0336 1.0000
8.250 1.1477 0.01516 0.00849 -0.0633 0.0254 1.0000
8.500 1.1593 0.01562 0.00895 -0.0604 0.0226 1.0000
8.750 1.1707 0.01612 0.00947 -0.0574 0.0205 1.0000
9.000 1.1836 0.01656 0.00993 -0.0549 0.0192 1.0000
9.250 1.1954 0.01707 0.01047 -0.0522 0.0181 1.0000
9.500 1.2032 0.01780 0.01123 -0.0489 0.0168 1.0000
9.750 1.2168 0.01826 0.01173 -0.0467 0.0161 1.0000
10.000 1.2282 0.01886 0.01237 -0.0442 0.0157 1.0000
10.250 1.2392 0.01951 0.01305 -0.0417 0.0150 1.0000
10.500 1.2490 0.02025 0.01383 -0.0392 0.0145 1.0000
10.750 1.2574 0.02111 0.01473 -0.0366 0.0140 1.0000
11.000 1.2592 0.02240 0.01610 -0.0333 0.0134 1.0000
11.250 1.2666 0.02341 0.01717 -0.0309 0.0132 1.0000
11.500 1.2767 0.02431 0.01813 -0.0290 0.0128 1.0000
11.750 1.2863 0.02527 0.01913 -0.0271 0.0125 1.0000
12.000 1.2924 0.02651 0.02043 -0.0249 0.0123 1.0000
12.250 1.3022 0.02754 0.02150 -0.0233 0.0119 1.0000
12.500 1.3100 0.02874 0.02275 -0.0216 0.0115 1.0000
12.750 1.3152 0.03018 0.02424 -0.0197 0.0112 1.0000
13.000 1.3176 0.03192 0.02604 -0.0179 0.0110 1.0000
13.250 1.3185 0.03383 0.02802 -0.0161 0.0107 1.0000
13.500 1.3116 0.03651 0.03079 -0.0141 0.0106 1.0000
13.750 1.3088 0.03897 0.03335 -0.0125 0.0103 1.0000
14.000 1.3127 0.04090 0.03535 -0.0115 0.0102 1.0000
14.250 1.3179 0.04276 0.03728 -0.0106 0.0101 1.0000
14.500 1.3215 0.04485 0.03945 -0.0098 0.0099 1.0000
14.750 1.3217 0.04732 0.04199 -0.0090 0.0099 1.0000
15.000 1.3230 0.04976 0.04451 -0.0084 0.0096 1.0000
15.250 1.3233 0.05233 0.04715 -0.0078 0.0096 1.0000
15.500 1.3282 0.05450 0.04939 -0.0075 0.0092 1.0000
15.750 1.3243 0.05764 0.05262 -0.0071 0.0092 1.0000
16.000 1.3242 0.06045 0.05549 -0.0069 0.0091 1.0000
16.250 1.3245 0.06328 0.05839 -0.0068 0.0089 1.0000
16.500 1.3217 0.06650 0.06170 -0.0068 0.0089 1.0000
16.750 1.3196 0.06974 0.06501 -0.0070 0.0087 1.0000
17.000 1.3196 0.07282 0.06816 -0.0073 0.0086 1.0000
17.250 1.3150 0.07643 0.07186 -0.0076 0.0086 1.0000
17.500 1.3146 0.07969 0.07517 -0.0083 0.0084 1.0000
17.750 1.3096 0.08349 0.07904 -0.0088 0.0083 1.0000
18.000 1.3047 0.08735 0.08297 -0.0096 0.0081 1.0000
18.250 1.2984 0.09127 0.08697 -0.0101 0.0081 1.0000
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