RUTAN WING AIRFOIL (amsoil2-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RUTAN WING AIRFOIL (amsoil2-il) Reynolds number: 100,000 Max Cl/Cd: 38.67 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-amsoil2-il-100000.txt Download as CSV file: xf-amsoil2-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RUTAN WING AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5387 0.10505 0.09958 -0.0129 1.0000 0.1495
-9.500 -0.5431 0.10123 0.09581 -0.0156 1.0000 0.1564
-9.250 -0.6339 0.09307 0.08774 -0.0319 1.0000 0.1596
-9.000 -0.5435 0.09273 0.08738 -0.0187 1.0000 0.1653
-8.750 -0.5439 0.08900 0.08369 -0.0205 1.0000 0.1718
-8.500 -0.6481 0.08170 0.07625 -0.0341 1.0000 0.1768
-8.250 -0.5702 0.07847 0.07330 -0.0276 1.0000 0.1820
-8.000 -0.5736 0.07491 0.06975 -0.0286 1.0000 0.1880
-7.750 -0.6095 0.06947 0.06424 -0.0318 1.0000 0.1970
-7.500 -0.6762 0.05138 0.04469 -0.0332 1.0000 0.1119
-7.250 -0.6724 0.04809 0.04132 -0.0308 1.0000 0.1097
-7.000 -0.6714 0.04489 0.03786 -0.0280 1.0000 0.1080
-6.750 -0.6681 0.04170 0.03430 -0.0254 1.0000 0.1065
-6.500 -0.6609 0.03859 0.03078 -0.0230 1.0000 0.1051
-6.250 -0.6497 0.03588 0.02768 -0.0209 1.0000 0.1045
-6.000 -0.6352 0.03411 0.02567 -0.0193 1.0000 0.1062
-5.750 -0.6192 0.03244 0.02372 -0.0177 1.0000 0.1084
-5.500 -0.6014 0.03075 0.02170 -0.0163 1.0000 0.1102
-5.250 -0.5820 0.02930 0.01988 -0.0151 1.0000 0.1122
-5.000 -0.5619 0.02775 0.01816 -0.0142 1.0000 0.1154
-4.750 -0.5411 0.02674 0.01715 -0.0134 1.0000 0.1192
-4.500 -0.5191 0.02578 0.01606 -0.0126 1.0000 0.1230
-4.250 -0.4965 0.02512 0.01511 -0.0118 1.0000 0.1278
-4.000 -0.4734 0.02395 0.01410 -0.0115 1.0000 0.1336
-3.750 -0.4505 0.02331 0.01339 -0.0108 1.0000 0.1402
-3.500 -0.4275 0.02251 0.01264 -0.0103 1.0000 0.1478
-3.250 -0.4048 0.02202 0.01214 -0.0098 1.0000 0.1575
-3.000 -0.3819 0.02133 0.01161 -0.0093 1.0000 0.1684
-2.750 -0.3590 0.02078 0.01117 -0.0089 1.0000 0.1824
-2.500 -0.3240 0.02019 0.01078 -0.0108 0.9966 0.2061
-2.250 -0.2866 0.01946 0.01039 -0.0132 0.9932 0.2497
-2.000 -0.2643 0.01724 0.01067 -0.0119 0.9910 0.6940
-1.750 -0.2457 0.01785 0.01150 -0.0078 0.9857 0.8081
-1.500 -0.2251 0.01840 0.01205 -0.0047 0.9803 0.8586
-1.250 -0.2054 0.01885 0.01248 -0.0015 0.9744 0.8974
-1.000 -0.1710 0.01938 0.01295 -0.0012 0.9708 0.9353
-0.750 -0.1056 0.02007 0.01352 -0.0075 0.9696 0.9673
-0.500 0.0031 0.02079 0.01410 -0.0227 0.9724 0.9912
-0.250 0.0679 0.02099 0.01423 -0.0309 0.9703 1.0000
0.000 0.0902 0.02105 0.01426 -0.0314 0.9618 1.0000
0.250 0.1259 0.02118 0.01436 -0.0342 0.9561 1.0000
0.500 0.1443 0.02130 0.01447 -0.0338 0.9468 1.0000
0.750 0.1820 0.02151 0.01467 -0.0368 0.9415 1.0000
1.000 0.1912 0.02169 0.01485 -0.0346 0.9312 1.0000
1.250 0.2302 0.02181 0.01499 -0.0373 0.9213 1.0000
1.500 0.3448 0.02086 0.01413 -0.0512 0.9018 1.0000
1.750 0.4066 0.01997 0.01332 -0.0558 0.8840 1.0000
2.000 0.4442 0.01922 0.01262 -0.0559 0.8654 1.0000
2.250 0.4708 0.01850 0.01195 -0.0539 0.8458 1.0000
2.500 0.4924 0.01774 0.01121 -0.0508 0.8252 1.0000
2.750 0.5114 0.01699 0.01049 -0.0474 0.8043 1.0000
3.000 0.5286 0.01631 0.00982 -0.0437 0.7813 1.0000
3.250 0.5439 0.01567 0.00922 -0.0399 0.7517 1.0000
3.500 0.5584 0.01495 0.00848 -0.0356 0.7044 1.0000
3.750 0.5646 0.01460 0.00724 -0.0287 0.4842 1.0000
4.000 0.5579 0.01695 0.00790 -0.0232 0.2571 1.0000
4.250 0.5691 0.01807 0.00863 -0.0206 0.2172 1.0000
4.500 0.5852 0.01906 0.00933 -0.0187 0.1951 1.0000
4.750 0.6055 0.01997 0.01005 -0.0174 0.1785 1.0000
5.000 0.6284 0.02088 0.01084 -0.0166 0.1653 1.0000
5.250 0.6530 0.02195 0.01179 -0.0161 0.1551 1.0000
5.500 0.6783 0.02294 0.01265 -0.0157 0.1458 1.0000
5.750 0.7049 0.02411 0.01382 -0.0154 0.1384 1.0000
6.000 0.7311 0.02517 0.01486 -0.0151 0.1317 1.0000
6.250 0.7580 0.02665 0.01631 -0.0150 0.1259 1.0000
6.500 0.7842 0.02787 0.01769 -0.0146 0.1211 1.0000
6.750 0.8100 0.02918 0.01900 -0.0144 0.1164 1.0000
7.000 0.8351 0.03107 0.02098 -0.0142 0.1125 1.0000
7.250 0.8586 0.03273 0.02299 -0.0133 0.1095 1.0000
7.500 0.8815 0.03445 0.02494 -0.0126 0.1063 1.0000
7.750 0.9057 0.03606 0.02654 -0.0124 0.1029 1.0000
8.000 0.9274 0.03912 0.02966 -0.0121 0.1008 1.0000
8.250 0.9434 0.04144 0.03250 -0.0105 0.0995 1.0000
8.500 0.9567 0.04421 0.03578 -0.0088 0.0980 1.0000
8.750 0.9677 0.04745 0.03944 -0.0071 0.0970 1.0000
9.000 0.9752 0.05132 0.04371 -0.0053 0.0975 1.0000
9.250 0.9793 0.05544 0.04820 -0.0035 0.0982 1.0000
9.500 0.9807 0.05971 0.05278 -0.0018 0.0988 1.0000
9.750 0.9818 0.06414 0.05744 -0.0004 0.0996 1.0000
10.000 0.7344 0.10328 0.09796 -0.0191 0.1875 1.0000
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Polar data table (+)
Polar graphs
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