davissm (davissm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: davissm (davissm-il) Reynolds number: 100,000 Max Cl/Cd: 69.38 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-davissm-il-100000-n5.txt Download as CSV file: xf-davissm-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3298 0.10786 0.10307 -0.0266 1.0000 0.0326
-7.500 -0.3402 0.10686 0.10215 -0.0237 1.0000 0.0330
-7.250 -0.3507 0.10585 0.10123 -0.0210 1.0000 0.0334
-7.000 -0.3305 0.10266 0.09802 -0.0278 0.9951 0.0349
-6.750 -0.2980 0.10024 0.09557 -0.0414 0.9876 0.0359
-6.500 -0.2656 0.09684 0.09212 -0.0521 0.9814 0.0362
-6.250 -0.2536 0.09070 0.08600 -0.0525 0.9785 0.0368
-6.000 -0.2422 0.08612 0.08143 -0.0513 0.9750 0.0377
-5.750 -0.2223 0.08221 0.07748 -0.0541 0.9705 0.0388
-5.500 -0.1948 0.07823 0.07346 -0.0596 0.9670 0.0403
-5.250 -0.1671 0.07448 0.06967 -0.0654 0.9620 0.0421
-5.000 -0.1338 0.07059 0.06571 -0.0726 0.9572 0.0443
-4.750 -0.0621 0.06641 0.06126 -0.0917 0.9539 0.0482
-4.500 -0.0144 0.06108 0.05578 -0.1019 0.9519 0.0491
-4.250 -0.0127 0.05785 0.05265 -0.0978 0.9455 0.0515
-4.000 0.0228 0.05447 0.04919 -0.1029 0.9421 0.0559
-3.750 0.1075 0.05036 0.04449 -0.1208 0.9404 0.0623
-3.500 0.1401 0.04537 0.03951 -0.1250 0.9386 0.0636
-3.250 0.1826 0.04092 0.03478 -0.1300 0.9339 0.0474
-2.750 0.2709 0.03379 0.02706 -0.1406 0.9276 0.0461
-2.500 0.3168 0.03050 0.02339 -0.1456 0.9254 0.0443
-2.250 0.3606 0.02769 0.02010 -0.1495 0.9225 0.0438
-2.000 0.3957 0.02594 0.01786 -0.1511 0.9163 0.0470
-1.750 0.4350 0.02421 0.01562 -0.1535 0.9127 0.0479
-1.500 0.4747 0.02271 0.01369 -0.1559 0.9099 0.0485
-1.250 0.5040 0.02153 0.01227 -0.1563 0.9028 0.0496
-1.000 0.5381 0.02067 0.01133 -0.1578 0.8980 0.0541
-0.750 0.5727 0.01992 0.01041 -0.1591 0.8935 0.0583
-0.500 0.6010 0.01936 0.00973 -0.1590 0.8858 0.0605
-0.250 0.6355 0.01865 0.00895 -0.1602 0.8812 0.0636
0.000 0.6621 0.01835 0.00871 -0.1600 0.8727 0.0715
0.250 0.6958 0.01791 0.00820 -0.1610 0.8672 0.0792
0.500 0.7235 0.01773 0.00798 -0.1608 0.8585 0.0891
0.750 0.7569 0.01732 0.00767 -0.1618 0.8525 0.1243
1.000 0.7815 0.01570 0.00775 -0.1613 0.8434 1.0000
1.250 0.8120 0.01570 0.00757 -0.1615 0.8363 1.0000
1.500 0.8385 0.01580 0.00757 -0.1611 0.8264 1.0000
1.750 0.8657 0.01589 0.00759 -0.1607 0.8168 1.0000
2.000 0.8956 0.01587 0.00752 -0.1608 0.8088 1.0000
2.250 0.9211 0.01601 0.00764 -0.1602 0.7976 1.0000
2.500 0.9477 0.01611 0.00774 -0.1597 0.7870 1.0000
2.750 0.9752 0.01618 0.00780 -0.1594 0.7767 1.0000
3.000 1.0032 0.01622 0.00785 -0.1592 0.7663 1.0000
3.250 1.0291 0.01635 0.00806 -0.1586 0.7537 1.0000
3.500 1.0553 0.01645 0.00820 -0.1580 0.7402 1.0000
3.750 1.0820 0.01646 0.00821 -0.1572 0.7230 1.0000
4.000 1.1061 0.01651 0.00827 -0.1560 0.6980 1.0000
4.250 1.1305 0.01659 0.00837 -0.1548 0.6714 1.0000
4.500 1.1547 0.01675 0.00852 -0.1536 0.6447 1.0000
4.750 1.1780 0.01698 0.00869 -0.1523 0.6117 1.0000
5.000 1.2002 0.01730 0.00894 -0.1508 0.5733 1.0000
5.250 1.2203 0.01779 0.00925 -0.1489 0.5240 1.0000
5.500 1.2366 0.01856 0.00974 -0.1463 0.4538 1.0000
5.750 1.2462 0.01992 0.01047 -0.1429 0.3465 1.0000
6.250 1.2501 0.02492 0.01358 -0.1349 0.0872 1.0000
6.500 1.2636 0.02625 0.01493 -0.1325 0.0733 1.0000
6.750 1.2779 0.02740 0.01621 -0.1302 0.0636 1.0000
7.000 1.2878 0.02882 0.01776 -0.1272 0.0573 1.0000
7.250 1.2998 0.02997 0.01905 -0.1246 0.0506 1.0000
7.500 1.3055 0.03155 0.02065 -0.1211 0.0462 1.0000
7.750 1.3146 0.03289 0.02218 -0.1180 0.0432 1.0000
8.000 1.3229 0.03426 0.02366 -0.1148 0.0398 1.0000
8.250 1.3313 0.03569 0.02510 -0.1120 0.0365 1.0000
8.500 1.3418 0.03743 0.02692 -0.1095 0.0341 1.0000
8.750 1.3588 0.03920 0.02889 -0.1077 0.0320 1.0000
9.000 1.3799 0.04114 0.03097 -0.1066 0.0301 1.0000
9.250 1.3996 0.04302 0.03298 -0.1056 0.0283 1.0000
9.500 1.4151 0.04500 0.03499 -0.1043 0.0264 1.0000
9.750 1.4370 0.04751 0.03782 -0.1035 0.0246 1.0000
10.000 1.4595 0.05068 0.04139 -0.1028 0.0236 1.0000
10.250 1.4730 0.05396 0.04513 -0.1009 0.0228 1.0000
10.500 1.4790 0.05727 0.04883 -0.0980 0.0223 1.0000
10.750 1.4789 0.06057 0.05251 -0.0945 0.0219 1.0000
11.000 1.4741 0.06370 0.05597 -0.0907 0.0214 1.0000
11.250 1.4670 0.06665 0.05920 -0.0871 0.0209 1.0000
11.500 1.4592 0.06946 0.06223 -0.0839 0.0203 1.0000
11.750 1.4496 0.07246 0.06546 -0.0811 0.0198 1.0000
12.000 1.4384 0.07578 0.06899 -0.0786 0.0195 1.0000
12.250 1.4257 0.07944 0.07286 -0.0766 0.0192 1.0000
12.500 1.4112 0.08352 0.07714 -0.0751 0.0189 1.0000
12.750 1.3941 0.08823 0.08209 -0.0741 0.0188 1.0000
13.000 1.3754 0.09339 0.08748 -0.0737 0.0187 1.0000
13.250 1.3558 0.09895 0.09328 -0.0742 0.0186 1.0000
13.500 1.3356 0.10501 0.09957 -0.0756 0.0186 1.0000
13.750 1.3147 0.11166 0.10645 -0.0780 0.0187 1.0000
14.000 1.2914 0.11959 0.11464 -0.0820 0.0189 1.0000
14.250 1.2602 0.13101 0.12634 -0.0891 0.0194 1.0000
14.500 0.9910 0.12941 0.12508 -0.0703 0.0242 1.0000
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Polar data table (+)
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