RUTAN WING AIRFOIL (amsoil2-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RUTAN WING AIRFOIL (amsoil2-il) Reynolds number: 50,000 Max Cl/Cd: 25.34 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-amsoil2-il-50000-n5.txt Download as CSV file: xf-amsoil2-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6038 0.09792 0.08983 -0.0286 1.0000 0.0775
-10.250 -0.6157 0.09052 0.08243 -0.0338 1.0000 0.0774
-10.000 -0.6325 0.08367 0.07556 -0.0384 1.0000 0.0771
-9.750 -0.6530 0.07774 0.06957 -0.0414 1.0000 0.0768
-9.500 -0.6743 0.07279 0.06452 -0.0422 1.0000 0.0767
-9.250 -0.6907 0.06797 0.05951 -0.0425 1.0000 0.0766
-9.000 -0.7024 0.06342 0.05470 -0.0422 1.0000 0.0767
-8.750 -0.7111 0.05902 0.04995 -0.0413 1.0000 0.0772
-8.500 -0.7146 0.05511 0.04566 -0.0400 1.0000 0.0781
-8.250 -0.7003 0.05333 0.04392 -0.0391 1.0000 0.0798
-8.000 -0.6916 0.05100 0.04143 -0.0378 1.0000 0.0815
-7.750 -0.6848 0.04838 0.03855 -0.0361 1.0000 0.0830
-7.500 -0.6777 0.04573 0.03558 -0.0342 1.0000 0.0842
-7.250 -0.6697 0.04326 0.03271 -0.0321 1.0000 0.0861
-7.000 -0.6609 0.04088 0.02982 -0.0299 1.0000 0.0885
-6.750 -0.6464 0.03943 0.02838 -0.0284 1.0000 0.0906
-6.500 -0.6319 0.03796 0.02680 -0.0267 1.0000 0.0928
-6.250 -0.6167 0.03639 0.02500 -0.0250 1.0000 0.0952
-6.000 -0.6008 0.03489 0.02316 -0.0233 1.0000 0.0988
-5.750 -0.5837 0.03357 0.02172 -0.0219 1.0000 0.1020
-5.500 -0.5657 0.03249 0.02061 -0.0206 1.0000 0.1053
-5.250 -0.5468 0.03142 0.01938 -0.0192 1.0000 0.1094
-5.000 -0.5271 0.03041 0.01818 -0.0180 1.0000 0.1143
-4.750 -0.5076 0.02955 0.01740 -0.0168 1.0000 0.1190
-4.500 -0.4871 0.02879 0.01653 -0.0156 1.0000 0.1251
-4.250 -0.4667 0.02804 0.01579 -0.0145 1.0000 0.1316
-4.000 -0.4464 0.02743 0.01516 -0.0133 1.0000 0.1394
-3.750 -0.4261 0.02681 0.01456 -0.0122 1.0000 0.1480
-3.500 -0.4005 0.02626 0.01394 -0.0121 0.9980 0.1600
-3.250 -0.3681 0.02559 0.01334 -0.0135 0.9936 0.1759
-3.000 -0.3374 0.02488 0.01277 -0.0147 0.9886 0.1966
-2.750 -0.3058 0.02410 0.01219 -0.0162 0.9839 0.2288
-2.500 -0.2777 0.02291 0.01160 -0.0174 0.9787 0.3004
-2.250 -0.2610 0.02155 0.01213 -0.0145 0.9742 0.6198
-2.000 -0.2375 0.02190 0.01266 -0.0119 0.9689 0.7465
-1.750 -0.2152 0.02230 0.01309 -0.0092 0.9625 0.8112
-1.500 -0.1862 0.02275 0.01349 -0.0077 0.9580 0.8627
-1.250 -0.1506 0.02317 0.01382 -0.0077 0.9541 0.9070
-1.000 -0.0634 0.02387 0.01435 -0.0171 0.9575 0.9603
-0.750 0.0162 0.02405 0.01438 -0.0274 0.9582 0.9847
-0.500 0.0607 0.02406 0.01430 -0.0317 0.9532 0.9937
-0.250 0.1010 0.02408 0.01426 -0.0353 0.9472 1.0000
0.000 0.1318 0.02413 0.01426 -0.0370 0.9410 1.0000
0.250 0.1512 0.02423 0.01434 -0.0366 0.9318 1.0000
0.500 0.1838 0.02434 0.01443 -0.0385 0.9261 1.0000
0.750 0.1975 0.02451 0.01460 -0.0370 0.9161 1.0000
1.000 0.2289 0.02467 0.01478 -0.0385 0.9101 1.0000
1.250 0.2412 0.02490 0.01502 -0.0365 0.9001 1.0000
1.500 0.2704 0.02510 0.01526 -0.0375 0.8934 1.0000
1.750 0.2827 0.02539 0.01558 -0.0354 0.8834 1.0000
2.000 0.3149 0.02557 0.01582 -0.0366 0.8756 1.0000
2.250 0.3443 0.02554 0.01586 -0.0366 0.8600 1.0000
2.500 0.3953 0.02476 0.01518 -0.0386 0.8357 1.0000
2.750 0.4256 0.02407 0.01458 -0.0371 0.8085 1.0000
3.000 0.4583 0.02315 0.01372 -0.0356 0.7805 1.0000
3.250 0.4823 0.02231 0.01293 -0.0326 0.7480 1.0000
3.500 0.4999 0.02175 0.01240 -0.0291 0.7107 1.0000
3.750 0.5151 0.02142 0.01213 -0.0257 0.6643 1.0000
4.000 0.5330 0.02103 0.01166 -0.0223 0.5830 1.0000
4.250 0.5473 0.02166 0.01065 -0.0175 0.3310 1.0000
4.500 0.5540 0.02335 0.01156 -0.0147 0.2479 1.0000
4.750 0.5674 0.02461 0.01246 -0.0128 0.2132 1.0000
5.000 0.5837 0.02571 0.01334 -0.0113 0.1914 1.0000
5.250 0.6024 0.02673 0.01420 -0.0101 0.1752 1.0000
5.500 0.6235 0.02766 0.01509 -0.0091 0.1615 1.0000
5.750 0.6474 0.02859 0.01601 -0.0084 0.1502 1.0000
6.000 0.6731 0.02958 0.01691 -0.0081 0.1408 1.0000
6.250 0.7011 0.03053 0.01791 -0.0079 0.1320 1.0000
6.500 0.7300 0.03163 0.01898 -0.0079 0.1248 1.0000
6.750 0.7585 0.03276 0.02018 -0.0079 0.1182 1.0000
7.000 0.7865 0.03407 0.02141 -0.0080 0.1129 1.0000
7.250 0.8131 0.03547 0.02304 -0.0077 0.1074 1.0000
7.500 0.8387 0.03691 0.02453 -0.0075 0.1033 1.0000
7.750 0.8631 0.03856 0.02626 -0.0073 0.0995 1.0000
8.000 0.8851 0.04041 0.02846 -0.0066 0.0956 1.0000
8.250 0.9068 0.04228 0.03052 -0.0060 0.0926 1.0000
8.500 0.9282 0.04402 0.03229 -0.0056 0.0898 1.0000
8.750 0.9438 0.04645 0.03510 -0.0044 0.0871 1.0000
9.000 0.9566 0.04915 0.03823 -0.0031 0.0848 1.0000
9.250 0.9681 0.05183 0.04124 -0.0018 0.0828 1.0000
9.500 0.9801 0.05418 0.04379 -0.0007 0.0809 1.0000
9.750 0.9955 0.05623 0.04587 0.0001 0.0790 1.0000
10.000 0.9945 0.05968 0.04973 0.0020 0.0776 1.0000
10.250 0.9860 0.06358 0.05407 0.0042 0.0767 1.0000
10.500 0.9736 0.06760 0.05846 0.0063 0.0762 1.0000
10.750 0.9539 0.07166 0.06280 0.0085 0.0759 1.0000
11.000 0.9287 0.07626 0.06764 0.0097 0.0758 1.0000
11.250 0.8993 0.08190 0.07349 0.0092 0.0760 1.0000
11.500 0.8665 0.08898 0.08074 0.0065 0.0763 1.0000
11.750 0.8330 0.09783 0.08970 0.0015 0.0768 1.0000
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Polar data table (+)
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