davissm (davissm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: davissm (davissm-il) Reynolds number: 500,000 Max Cl/Cd: 131.74 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-davissm-il-500000.txt Download as CSV file: xf-davissm-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3158 0.11401 0.11170 -0.0329 1.0000 0.0136
-9.000 -0.3199 0.11253 0.11027 -0.0313 1.0000 0.0140
-8.750 -0.3271 0.11156 0.10935 -0.0295 0.9995 0.0142
-8.500 -0.3118 0.10808 0.10587 -0.0348 0.9972 0.0143
-8.250 -0.2975 0.10460 0.10238 -0.0401 0.9939 0.0143
-8.000 -0.2831 0.10111 0.09890 -0.0453 0.9886 0.0144
-7.750 -0.2683 0.09587 0.09366 -0.0487 0.9848 0.0145
-7.500 -0.2541 0.09173 0.08951 -0.0493 0.9824 0.0149
-7.250 -0.2340 0.08795 0.08572 -0.0535 0.9795 0.0151
-7.000 -0.2116 0.08419 0.08196 -0.0586 0.9772 0.0155
-6.750 -0.1896 0.08055 0.07831 -0.0638 0.9732 0.0159
-6.500 -0.1629 0.07661 0.07434 -0.0702 0.9706 0.0165
-6.250 -0.1318 0.07243 0.07013 -0.0777 0.9686 0.0173
-6.000 -0.0895 0.06788 0.06553 -0.0889 0.9666 0.0189
-5.750 -0.0387 0.06313 0.06071 -0.1030 0.9623 0.0193
-5.500 0.0008 0.05857 0.05607 -0.1117 0.9578 0.0194
-5.250 0.0267 0.05284 0.05031 -0.1172 0.9541 0.0201
-5.000 0.0521 0.05030 0.04773 -0.1199 0.9489 0.0209
-4.750 0.0831 0.04755 0.04491 -0.1244 0.9427 0.0223
-4.500 0.1237 0.04395 0.04120 -0.1315 0.9380 0.0241
-4.250 0.1778 0.04038 0.03744 -0.1405 0.9318 0.0262
-4.000 0.2188 0.03652 0.03339 -0.1461 0.9266 0.0264
-3.750 0.2543 0.03043 0.02711 -0.1522 0.9218 0.0277
-3.500 0.2813 0.02882 0.02544 -0.1537 0.9155 0.0289
-3.250 0.3129 0.02708 0.02356 -0.1557 0.9105 0.0317
-3.000 0.3531 0.02563 0.02178 -0.1575 0.9050 0.0360
-2.250 0.4489 0.01780 0.01326 -0.1634 0.8880 0.0415
-2.000 0.4784 0.01859 0.01381 -0.1627 0.8821 0.0485
-1.750 0.5147 0.01377 0.00828 -0.1645 0.8770 0.0372
-1.500 0.5434 0.01304 0.00739 -0.1645 0.8706 0.0367
-1.250 0.5725 0.01193 0.00606 -0.1648 0.8652 0.0369
-1.000 0.6005 0.01096 0.00499 -0.1649 0.8581 0.0393
-0.750 0.6287 0.01046 0.00440 -0.1648 0.8521 0.0407
-0.500 0.6563 0.01009 0.00400 -0.1647 0.8442 0.0426
-0.250 0.6843 0.00980 0.00365 -0.1646 0.8377 0.0449
0.000 0.7117 0.00960 0.00345 -0.1645 0.8295 0.0476
0.250 0.7397 0.00929 0.00309 -0.1644 0.8227 0.0516
0.500 0.7672 0.00911 0.00292 -0.1643 0.8140 0.0563
0.750 0.7949 0.00902 0.00280 -0.1642 0.8060 0.0617
1.000 0.8225 0.00886 0.00268 -0.1641 0.7970 0.0814
1.250 0.8490 0.00712 0.00280 -0.1644 0.7880 1.0000
1.500 0.8764 0.00720 0.00278 -0.1642 0.7787 1.0000
1.750 0.9033 0.00728 0.00277 -0.1639 0.7662 1.0000
2.000 0.9297 0.00736 0.00279 -0.1635 0.7500 1.0000
2.250 0.9563 0.00746 0.00282 -0.1631 0.7350 1.0000
2.500 0.9827 0.00757 0.00287 -0.1628 0.7193 1.0000
2.750 1.0089 0.00771 0.00294 -0.1624 0.7014 1.0000
3.000 1.0346 0.00788 0.00304 -0.1618 0.6811 1.0000
3.250 1.0605 0.00805 0.00315 -0.1614 0.6611 1.0000
3.500 1.0858 0.00827 0.00329 -0.1608 0.6388 1.0000
3.750 1.1100 0.00856 0.00344 -0.1600 0.6072 1.0000
4.000 1.1338 0.00889 0.00366 -0.1592 0.5722 1.0000
4.250 1.1560 0.00936 0.00391 -0.1581 0.5247 1.0000
4.500 1.1769 0.00998 0.00424 -0.1568 0.4658 1.0000
4.750 1.1960 0.01081 0.00468 -0.1552 0.3904 1.0000
5.000 1.2097 0.01226 0.00542 -0.1529 0.2624 1.0000
5.250 1.2164 0.01457 0.00671 -0.1495 0.0835 1.0000
5.500 1.2384 0.01515 0.00728 -0.1485 0.0682 1.0000
5.750 1.2604 0.01572 0.00782 -0.1475 0.0572 1.0000
6.000 1.2814 0.01636 0.00844 -0.1463 0.0466 1.0000
6.250 1.3043 0.01677 0.00886 -0.1455 0.0399 1.0000
6.500 1.3240 0.01749 0.00962 -0.1440 0.0334 1.0000
6.750 1.3450 0.01804 0.01017 -0.1428 0.0289 1.0000
7.000 1.3611 0.01900 0.01120 -0.1407 0.0252 1.0000
7.250 1.3800 0.01965 0.01192 -0.1390 0.0233 1.0000
7.500 1.3975 0.02038 0.01270 -0.1372 0.0215 1.0000
7.750 1.4117 0.02132 0.01369 -0.1348 0.0200 1.0000
8.000 1.4160 0.02306 0.01558 -0.1305 0.0188 1.0000
8.250 1.4261 0.02433 0.01696 -0.1274 0.0181 1.0000
8.500 1.4408 0.02511 0.01782 -0.1251 0.0173 1.0000
8.750 1.4524 0.02602 0.01882 -0.1223 0.0164 1.0000
9.000 1.4623 0.02720 0.02009 -0.1193 0.0157 1.0000
9.250 1.4730 0.02840 0.02139 -0.1165 0.0151 1.0000
9.500 1.4838 0.02971 0.02280 -0.1138 0.0146 1.0000
9.750 1.4944 0.03106 0.02423 -0.1113 0.0140 1.0000
10.000 1.5051 0.03310 0.02638 -0.1089 0.0134 1.0000
10.250 1.5211 0.03637 0.02991 -0.1074 0.0126 1.0000
10.500 1.5300 0.03740 0.03110 -0.1046 0.0121 1.0000
10.750 1.5406 0.03940 0.03331 -0.1022 0.0117 1.0000
11.000 1.5488 0.04175 0.03589 -0.0996 0.0114 1.0000
11.250 1.5536 0.04423 0.03862 -0.0967 0.0110 1.0000
11.500 1.5546 0.04702 0.04166 -0.0935 0.0107 1.0000
11.750 1.5512 0.05029 0.04523 -0.0901 0.0106 1.0000
12.000 1.5432 0.05393 0.04916 -0.0865 0.0104 1.0000
12.250 1.5312 0.05795 0.05346 -0.0829 0.0103 1.0000
12.500 1.5094 0.06357 0.05945 -0.0791 0.0104 1.0000
12.750 1.4803 0.07023 0.06648 -0.0758 0.0106 1.0000
13.000 1.4505 0.07699 0.07355 -0.0737 0.0108 1.0000
13.250 1.4209 0.08396 0.08076 -0.0728 0.0110 1.0000
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Polar data table (+)
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