RUTAN CANARD AIRFOIL (amsoil1-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RUTAN CANARD AIRFOIL (amsoil1-il) Reynolds number: 50,000 Max Cl/Cd: 33.02 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-amsoil1-il-50000.txt Download as CSV file: xf-amsoil1-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RUTAN CANARD 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4602 0.12897 0.12133 -0.0120 1.0000 0.2218
-10.250 -0.4441 0.12517 0.11751 -0.0116 1.0000 0.2324
-10.000 -0.4748 0.12519 0.11770 -0.0154 1.0000 0.2381
-9.750 -0.4330 0.11848 0.11090 -0.0127 1.0000 0.2496
-9.500 -0.4556 0.11725 0.10980 -0.0155 1.0000 0.2575
-9.250 -0.4242 0.11212 0.10462 -0.0138 1.0000 0.2690
-9.000 -0.4272 0.10913 0.10171 -0.0147 1.0000 0.2790
-8.750 -0.4384 0.10773 0.10041 -0.0156 1.0000 0.2932
-8.500 -0.4147 0.10332 0.09599 -0.0142 1.0000 0.3092
-8.250 -0.4033 0.09993 0.09264 -0.0135 1.0000 0.3251
-8.000 -0.3958 0.09689 0.08965 -0.0129 1.0000 0.3419
-7.750 -0.3894 0.09404 0.08686 -0.0122 1.0000 0.3605
-7.500 -0.3879 0.09170 0.08459 -0.0111 1.0000 0.3823
-7.250 -0.4105 0.09099 0.08406 -0.0093 1.0000 0.4041
-7.000 -0.3722 0.08687 0.07989 -0.0070 1.0000 0.4380
-6.750 -0.3514 0.08393 0.07696 -0.0048 1.0000 0.4716
-6.500 -0.3350 0.08133 0.07441 -0.0025 1.0000 0.5064
-6.250 -0.3259 0.07948 0.07262 0.0006 1.0000 0.5455
-6.000 -0.2948 0.07621 0.06935 0.0022 1.0000 0.5912
-5.000 -0.5229 0.05437 0.04637 -0.0237 1.0000 0.2193
-4.750 -0.5037 0.04969 0.04132 -0.0244 1.0000 0.1984
-4.500 -0.4855 0.04607 0.03743 -0.0245 1.0000 0.1892
-4.250 -0.4625 0.04340 0.03387 -0.0252 1.0000 0.1816
-4.000 -0.4413 0.04104 0.03116 -0.0250 1.0000 0.1814
-3.750 -0.4186 0.03884 0.02862 -0.0250 1.0000 0.1810
-3.500 -0.3941 0.03713 0.02647 -0.0249 1.0000 0.1822
-3.250 -0.3713 0.03513 0.02450 -0.0249 1.0000 0.1870
-3.000 -0.3470 0.03377 0.02293 -0.0247 1.0000 0.1914
-2.750 -0.3219 0.03263 0.02148 -0.0245 1.0000 0.1970
-2.500 -0.2974 0.03146 0.02016 -0.0243 1.0000 0.2048
-2.250 -0.2733 0.03057 0.01919 -0.0239 1.0000 0.2142
-2.000 -0.2492 0.02970 0.01829 -0.0235 1.0000 0.2264
-1.750 -0.2253 0.02900 0.01758 -0.0229 1.0000 0.2416
-1.500 -0.2010 0.02835 0.01700 -0.0224 1.0000 0.2620
-1.250 -0.1759 0.02771 0.01648 -0.0221 1.0000 0.2920
-1.000 -0.1492 0.02670 0.01597 -0.0225 1.0000 0.3494
-0.750 -0.1404 0.02423 0.01632 -0.0145 1.0000 1.0000
-0.500 -0.1195 0.02461 0.01606 -0.0138 1.0000 1.0000
-0.250 -0.0996 0.02499 0.01609 -0.0134 1.0000 1.0000
0.000 -0.0794 0.02542 0.01626 -0.0132 1.0000 1.0000
0.250 -0.0590 0.02589 0.01651 -0.0131 1.0000 1.0000
0.500 -0.0384 0.02641 0.01684 -0.0131 1.0000 1.0000
0.750 -0.0176 0.02697 0.01725 -0.0131 1.0000 1.0000
1.000 0.0031 0.02758 0.01772 -0.0132 1.0000 1.0000
1.250 0.0238 0.02823 0.01825 -0.0133 1.0000 1.0000
1.500 0.0444 0.02892 0.01885 -0.0135 1.0000 1.0000
1.750 0.0649 0.02966 0.01951 -0.0137 1.0000 1.0000
2.000 0.0853 0.03045 0.02022 -0.0139 1.0000 1.0000
2.250 0.1054 0.03127 0.02100 -0.0141 1.0000 1.0000
2.500 0.1253 0.03215 0.02184 -0.0144 1.0000 1.0000
2.750 0.1634 0.03355 0.02322 -0.0181 0.9927 1.0000
3.000 0.2057 0.03510 0.02478 -0.0226 0.9815 1.0000
3.250 0.2459 0.03661 0.02632 -0.0266 0.9695 1.0000
3.500 0.2850 0.03811 0.02786 -0.0303 0.9560 1.0000
3.750 0.3222 0.03949 0.02932 -0.0335 0.9393 1.0000
4.000 0.3760 0.04095 0.03090 -0.0388 0.9126 1.0000
4.250 0.4373 0.04163 0.03173 -0.0434 0.8703 1.0000
4.500 0.5042 0.04137 0.03167 -0.0473 0.8274 1.0000
4.750 0.5619 0.04060 0.03114 -0.0492 0.7924 1.0000
5.000 0.6223 0.03887 0.02969 -0.0501 0.7581 1.0000
5.250 0.6952 0.03506 0.02627 -0.0499 0.7205 1.0000
5.500 0.7546 0.02969 0.02128 -0.0452 0.6713 1.0000
5.750 0.7892 0.02390 0.01511 -0.0346 0.4844 1.0000
6.000 0.7937 0.02580 0.01515 -0.0289 0.3352 1.0000
6.250 0.8112 0.02781 0.01650 -0.0271 0.2860 1.0000
6.500 0.8412 0.02959 0.01791 -0.0269 0.2532 1.0000
6.750 0.8739 0.03129 0.01945 -0.0271 0.2299 1.0000
7.000 0.9067 0.03312 0.02117 -0.0275 0.2129 1.0000
7.250 0.9377 0.03516 0.02320 -0.0277 0.2008 1.0000
7.500 0.9676 0.03735 0.02526 -0.0279 0.1901 1.0000
7.750 0.9899 0.03948 0.02780 -0.0270 0.1835 1.0000
8.000 1.0146 0.04173 0.03017 -0.0266 0.1767 1.0000
8.250 1.0365 0.04451 0.03310 -0.0260 0.1715 1.0000
8.500 1.0517 0.04726 0.03635 -0.0245 0.1686 1.0000
8.750 1.0648 0.05021 0.03971 -0.0230 0.1658 1.0000
9.000 1.0769 0.05321 0.04302 -0.0216 0.1627 1.0000
9.250 1.0897 0.05640 0.04645 -0.0204 0.1602 1.0000
9.500 1.0931 0.06022 0.05068 -0.0185 0.1601 1.0000
9.750 1.0861 0.06453 0.05546 -0.0162 0.1612 1.0000
10.000 1.0674 0.06940 0.06079 -0.0137 0.1632 1.0000
10.250 1.0395 0.07472 0.06646 -0.0115 0.1660 1.0000
10.500 1.0109 0.08003 0.07197 -0.0098 0.1687 1.0000
10.750 0.9908 0.08576 0.07780 -0.0095 0.1710 1.0000
11.000 0.9882 0.09148 0.08357 -0.0099 0.1728 1.0000
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Polar data table (+)
Polar graphs
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