davissm (davissm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: davissm (davissm-il) Reynolds number: 200,000 Max Cl/Cd: 92.47 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-davissm-il-200000-n5.txt Download as CSV file: xf-davissm-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3202 0.11623 0.11263 -0.0345 1.0000 0.0193
-8.750 -0.3263 0.11490 0.11137 -0.0329 1.0000 0.0193
-8.500 -0.3262 0.11289 0.10940 -0.0332 0.9985 0.0193
-8.250 -0.3135 0.10948 0.10599 -0.0375 0.9936 0.0194
-8.000 -0.3003 0.10601 0.10252 -0.0418 0.9867 0.0194
-7.750 -0.2824 0.10201 0.09852 -0.0470 0.9807 0.0194
-7.500 -0.2619 0.09781 0.09431 -0.0525 0.9768 0.0195
-7.250 -0.2500 0.09272 0.08923 -0.0526 0.9735 0.0197
-7.000 -0.2344 0.08855 0.08505 -0.0538 0.9705 0.0201
-6.750 -0.2137 0.08473 0.08121 -0.0578 0.9677 0.0206
-6.500 -0.1893 0.08087 0.07732 -0.0633 0.9653 0.0212
-6.250 -0.1664 0.07729 0.07372 -0.0683 0.9600 0.0220
-6.000 -0.1378 0.07341 0.06980 -0.0750 0.9563 0.0233
-5.750 -0.0755 0.06912 0.06537 -0.0941 0.9529 0.0263
-5.500 -0.0409 0.06489 0.06107 -0.1014 0.9483 0.0264
-5.250 -0.0064 0.06055 0.05665 -0.1081 0.9439 0.0264
-5.000 0.0314 0.05605 0.05205 -0.1152 0.9406 0.0264
-4.750 0.0715 0.05144 0.04732 -0.1225 0.9380 0.0265
-4.500 0.1047 0.04726 0.04302 -0.1275 0.9322 0.0264
-4.250 0.1253 0.04361 0.03936 -0.1293 0.9276 0.0248
-3.750 0.2238 0.03428 0.02949 -0.1450 0.9199 0.0261
-3.500 0.2624 0.03033 0.02529 -0.1497 0.9149 0.0257
-3.250 0.3054 0.02629 0.02084 -0.1543 0.9110 0.0260
-3.000 0.3381 0.02425 0.01857 -0.1567 0.9056 0.0283
-2.750 0.3708 0.02245 0.01652 -0.1584 0.8998 0.0297
-2.500 0.4074 0.01991 0.01351 -0.1605 0.8954 0.0298
-2.250 0.4386 0.01824 0.01147 -0.1613 0.8889 0.0306
-2.000 0.4697 0.01698 0.00987 -0.1620 0.8832 0.0319
-1.750 0.4995 0.01624 0.00883 -0.1622 0.8773 0.0348
-1.500 0.5284 0.01544 0.00778 -0.1623 0.8706 0.0356
-1.250 0.5579 0.01466 0.00680 -0.1625 0.8648 0.0366
-1.000 0.5854 0.01392 0.00599 -0.1625 0.8572 0.0385
-0.750 0.6140 0.01356 0.00559 -0.1626 0.8510 0.0415
-0.500 0.6412 0.01329 0.00529 -0.1624 0.8428 0.0452
-0.250 0.6696 0.01296 0.00490 -0.1624 0.8362 0.0475
0.000 0.6970 0.01265 0.00460 -0.1623 0.8279 0.0502
0.250 0.7249 0.01245 0.00440 -0.1623 0.8204 0.0559
0.500 0.7525 0.01232 0.00425 -0.1621 0.8117 0.0633
0.750 0.7801 0.01217 0.00412 -0.1620 0.8028 0.0747
1.000 0.8081 0.01195 0.00405 -0.1620 0.7944 0.1314
1.500 0.8617 0.01049 0.00412 -0.1618 0.7748 1.0000
1.750 0.8891 0.01057 0.00412 -0.1616 0.7650 1.0000
2.000 0.9160 0.01067 0.00418 -0.1613 0.7538 1.0000
2.250 0.9428 0.01078 0.00424 -0.1610 0.7421 1.0000
2.500 0.9696 0.01090 0.00431 -0.1606 0.7294 1.0000
2.750 0.9957 0.01102 0.00436 -0.1601 0.7121 1.0000
3.000 1.0212 0.01118 0.00445 -0.1594 0.6897 1.0000
3.250 1.0461 0.01137 0.00453 -0.1587 0.6640 1.0000
3.500 1.0711 0.01159 0.00467 -0.1579 0.6395 1.0000
3.750 1.0958 0.01185 0.00485 -0.1572 0.6142 1.0000
4.000 1.1193 0.01219 0.00505 -0.1562 0.5821 1.0000
4.250 1.1418 0.01259 0.00534 -0.1550 0.5445 1.0000
4.500 1.1634 0.01308 0.00566 -0.1538 0.5031 1.0000
4.750 1.1828 0.01374 0.00605 -0.1521 0.4483 1.0000
5.000 1.1990 0.01469 0.00660 -0.1500 0.3722 1.0000
5.250 1.2105 0.01615 0.00741 -0.1473 0.2601 1.0000
5.500 1.2134 0.01867 0.00890 -0.1435 0.0890 1.0000
5.750 1.2324 0.01951 0.00968 -0.1420 0.0709 1.0000
6.000 1.2522 0.02023 0.01043 -0.1407 0.0605 1.0000
6.250 1.2723 0.02087 0.01114 -0.1393 0.0521 1.0000
6.500 1.2906 0.02165 0.01194 -0.1377 0.0445 1.0000
6.750 1.3091 0.02235 0.01275 -0.1362 0.0385 1.0000
7.000 1.3250 0.02324 0.01367 -0.1342 0.0336 1.0000
7.250 1.3415 0.02401 0.01453 -0.1322 0.0297 1.0000
7.500 1.3546 0.02502 0.01558 -0.1298 0.0270 1.0000
7.750 1.3645 0.02624 0.01689 -0.1267 0.0252 1.0000
8.000 1.3754 0.02734 0.01812 -0.1238 0.0238 1.0000
8.250 1.3849 0.02841 0.01932 -0.1208 0.0221 1.0000
8.500 1.3954 0.02943 0.02041 -0.1181 0.0204 1.0000
8.750 1.4029 0.03077 0.02180 -0.1150 0.0191 1.0000
9.000 1.4082 0.03254 0.02366 -0.1116 0.0183 1.0000
9.250 1.4181 0.03402 0.02530 -0.1090 0.0177 1.0000
9.500 1.4287 0.03563 0.02707 -0.1066 0.0169 1.0000
9.750 1.4401 0.03734 0.02895 -0.1043 0.0162 1.0000
10.000 1.4523 0.03911 0.03091 -0.1022 0.0156 1.0000
10.250 1.4630 0.04069 0.03263 -0.1001 0.0147 1.0000
10.500 1.4717 0.04220 0.03426 -0.0980 0.0140 1.0000
10.750 1.4789 0.04397 0.03612 -0.0958 0.0133 1.0000
11.000 1.4868 0.04675 0.03910 -0.0937 0.0127 1.0000
11.250 1.4946 0.04916 0.04181 -0.0914 0.0124 1.0000
11.500 1.4993 0.05200 0.04499 -0.0890 0.0121 1.0000
11.750 1.5000 0.05523 0.04856 -0.0864 0.0118 1.0000
12.000 1.4962 0.05887 0.05256 -0.0836 0.0115 1.0000
12.250 1.4881 0.06283 0.05686 -0.0809 0.0113 1.0000
12.500 1.4765 0.06711 0.06150 -0.0785 0.0112 1.0000
12.750 1.4621 0.07170 0.06640 -0.0765 0.0110 1.0000
13.000 1.4459 0.07656 0.07155 -0.0750 0.0109 1.0000
13.250 1.4279 0.08185 0.07711 -0.0743 0.0107 1.0000
13.500 1.4082 0.08762 0.08313 -0.0743 0.0107 1.0000
13.750 1.3879 0.09379 0.08955 -0.0752 0.0106 1.0000
14.000 1.3662 0.10070 0.09669 -0.0771 0.0105 1.0000
14.250 1.3407 0.10906 0.10526 -0.0804 0.0107 1.0000
14.500 1.3164 0.11805 0.11447 -0.0849 0.0108 1.0000
14.750 1.2898 0.12879 0.12540 -0.0913 0.0111 1.0000
15.000 1.2642 0.14080 0.13758 -0.0993 0.0113 1.0000
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Polar data table (+)
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