davissm (davissm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: davissm (davissm-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.83 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-davissm-il-1000000-n5.txt Download as CSV file: xf-davissm-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: davissm
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1989 0.08749 0.08561 -0.0669 0.9390 0.0064
-7.750 -0.1900 0.08455 0.08264 -0.0688 0.9276 0.0066
-7.500 -0.1793 0.08147 0.07953 -0.0714 0.9183 0.0068
-7.250 -0.1656 0.07820 0.07622 -0.0747 0.9100 0.0067
-7.000 -0.1503 0.07473 0.07273 -0.0785 0.9024 0.0065
-6.500 -0.1127 0.06712 0.06503 -0.0881 0.8884 0.0065
-6.250 -0.0894 0.06270 0.06056 -0.0942 0.8818 0.0067
-6.000 -0.0586 0.05598 0.05377 -0.1040 0.8755 0.0075
-4.500 0.1999 0.01206 0.00757 -0.1597 0.8454 0.0137
-4.250 0.2284 0.01138 0.00669 -0.1601 0.8398 0.0142
-4.000 0.2571 0.01055 0.00563 -0.1605 0.8344 0.0146
-3.750 0.2857 0.00988 0.00479 -0.1608 0.8284 0.0153
-3.500 0.3138 0.00965 0.00448 -0.1610 0.8223 0.0158
-3.250 0.3421 0.00945 0.00422 -0.1611 0.8154 0.0164
-3.000 0.3701 0.00931 0.00401 -0.1611 0.8084 0.0172
-2.750 0.3983 0.00908 0.00371 -0.1613 0.8009 0.0180
-2.500 0.4263 0.00883 0.00337 -0.1613 0.7939 0.0187
-2.250 0.4545 0.00863 0.00310 -0.1614 0.7866 0.0191
-2.000 0.4825 0.00847 0.00287 -0.1615 0.7792 0.0194
-1.750 0.5106 0.00812 0.00244 -0.1616 0.7708 0.0206
-1.500 0.5385 0.00801 0.00230 -0.1616 0.7618 0.0217
-1.000 0.5940 0.00792 0.00214 -0.1616 0.7417 0.0244
-0.750 0.6218 0.00787 0.00203 -0.1616 0.7321 0.0254
-0.500 0.6494 0.00784 0.00195 -0.1615 0.7220 0.0261
-0.250 0.6771 0.00777 0.00183 -0.1615 0.7109 0.0276
0.000 0.7048 0.00773 0.00176 -0.1615 0.6992 0.0301
0.250 0.7322 0.00774 0.00175 -0.1614 0.6869 0.0328
0.500 0.7595 0.00778 0.00173 -0.1613 0.6739 0.0348
0.750 0.7868 0.00782 0.00173 -0.1612 0.6603 0.0362
1.000 0.8140 0.00785 0.00174 -0.1611 0.6464 0.0427
1.250 0.8403 0.00798 0.00179 -0.1608 0.6229 0.0504
1.500 0.8661 0.00814 0.00187 -0.1605 0.5903 0.0728
1.750 0.8926 0.00818 0.00197 -0.1603 0.5691 0.1492
2.000 0.9190 0.00818 0.00212 -0.1602 0.5488 0.2621
2.250 0.9443 0.00819 0.00234 -0.1599 0.5165 0.4368
2.750 0.9946 0.00772 0.00266 -0.1593 0.4572 1.0000
3.000 1.0203 0.00801 0.00283 -0.1589 0.4290 1.0000
3.250 1.0450 0.00841 0.00304 -0.1584 0.3914 1.0000
3.500 1.0686 0.00891 0.00330 -0.1578 0.3412 1.0000
3.750 1.0898 0.00970 0.00369 -0.1567 0.2652 1.0000
4.000 1.1032 0.01143 0.00456 -0.1544 0.0919 1.0000
4.250 1.1276 0.01182 0.00486 -0.1538 0.0705 1.0000
4.500 1.1527 0.01212 0.00511 -0.1534 0.0608 1.0000
4.750 1.1779 0.01240 0.00536 -0.1530 0.0527 1.0000
5.000 1.2028 0.01269 0.00561 -0.1525 0.0452 1.0000
5.250 1.2277 0.01297 0.00588 -0.1521 0.0396 1.0000
5.500 1.2523 0.01328 0.00616 -0.1516 0.0338 1.0000
5.750 1.2765 0.01361 0.00646 -0.1510 0.0278 1.0000
6.000 1.3005 0.01394 0.00677 -0.1504 0.0231 1.0000
6.250 1.3240 0.01433 0.00712 -0.1497 0.0184 1.0000
6.500 1.3477 0.01466 0.00748 -0.1491 0.0166 1.0000
6.750 1.3706 0.01505 0.00787 -0.1483 0.0145 1.0000
7.000 1.3931 0.01548 0.00831 -0.1474 0.0127 1.0000
7.250 1.4159 0.01585 0.00872 -0.1466 0.0119 1.0000
7.500 1.4379 0.01626 0.00918 -0.1456 0.0110 1.0000
7.750 1.4592 0.01671 0.00965 -0.1446 0.0102 1.0000
8.000 1.4794 0.01724 0.01019 -0.1433 0.0093 1.0000
8.250 1.4989 0.01779 0.01080 -0.1419 0.0086 1.0000
8.500 1.5188 0.01827 0.01133 -0.1406 0.0083 1.0000
8.750 1.5377 0.01879 0.01191 -0.1391 0.0080 1.0000
9.000 1.5557 0.01934 0.01253 -0.1374 0.0076 1.0000
9.250 1.5731 0.01991 0.01314 -0.1357 0.0072 1.0000
9.500 1.5896 0.02049 0.01376 -0.1338 0.0068 1.0000
9.750 1.6044 0.02116 0.01447 -0.1316 0.0064 1.0000
10.000 1.6148 0.02203 0.01542 -0.1286 0.0060 1.0000
10.250 1.6230 0.02291 0.01638 -0.1252 0.0058 1.0000
10.500 1.6341 0.02366 0.01722 -0.1224 0.0057 1.0000
10.750 1.6444 0.02450 0.01814 -0.1196 0.0056 1.0000
11.000 1.6546 0.02540 0.01912 -0.1170 0.0054 1.0000
11.250 1.6647 0.02635 0.02015 -0.1144 0.0052 1.0000
11.500 1.6741 0.02739 0.02127 -0.1119 0.0050 1.0000
11.750 1.6829 0.02852 0.02249 -0.1094 0.0049 1.0000
12.000 1.6914 0.02971 0.02377 -0.1070 0.0047 1.0000
12.250 1.6997 0.03094 0.02508 -0.1047 0.0045 1.0000
12.500 1.7074 0.03226 0.02651 -0.1025 0.0044 1.0000
12.750 1.7145 0.03368 0.02801 -0.1002 0.0042 1.0000
13.000 1.7209 0.03519 0.02960 -0.0981 0.0041 1.0000
13.250 1.7254 0.03690 0.03141 -0.0959 0.0039 1.0000
13.500 1.7272 0.03895 0.03356 -0.0935 0.0038 1.0000
13.750 1.7238 0.04156 0.03633 -0.0909 0.0036 1.0000
14.000 1.7282 0.04344 0.03831 -0.0892 0.0035 1.0000
14.250 1.7311 0.04552 0.04051 -0.0874 0.0035 1.0000
14.500 1.7344 0.04761 0.04270 -0.0859 0.0034 1.0000
14.750 1.7350 0.05007 0.04528 -0.0844 0.0034 1.0000
15.000 1.7351 0.05263 0.04797 -0.0830 0.0033 1.0000
15.250 1.7341 0.05541 0.05087 -0.0818 0.0032 1.0000
15.500 1.7316 0.05848 0.05409 -0.0807 0.0032 1.0000
15.750 1.7279 0.06181 0.05755 -0.0799 0.0031 1.0000
16.000 1.7236 0.06533 0.06122 -0.0792 0.0030 1.0000
16.250 1.7187 0.06903 0.06504 -0.0789 0.0030 1.0000
16.500 1.7125 0.07305 0.06921 -0.0787 0.0029 1.0000
16.750 1.7044 0.07750 0.07380 -0.0789 0.0029 1.0000
17.000 1.6960 0.08214 0.07858 -0.0794 0.0028 1.0000
17.250 1.6860 0.08715 0.08373 -0.0801 0.0028 1.0000
17.500 1.6756 0.09237 0.08909 -0.0812 0.0027 1.0000
17.750 1.6644 0.09786 0.09473 -0.0826 0.0027 1.0000
18.000 1.6498 0.10415 0.10117 -0.0846 0.0027 1.0000
18.250 1.6353 0.11060 0.10776 -0.0869 0.0027 1.0000
18.500 1.6199 0.11737 0.11468 -0.0896 0.0027 1.0000
18.750 1.6026 0.12472 0.12219 -0.0929 0.0026 1.0000
19.000 1.5845 0.13251 0.13012 -0.0967 0.0026 1.0000
19.250 1.5628 0.14144 0.13922 -0.1014 0.0026 1.0000
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Polar data table (+)
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