SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il) Reynolds number: 50,000 Max Cl/Cd: 27.15 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc1094r8-il-50000-n5.txt Download as CSV file: xf-sc1094r8-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SC1094 R8 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4143 0.10405 0.09732 -0.0028 1.0000 0.1384
-8.250 -0.4303 0.10082 0.09418 -0.0068 1.0000 0.1437
-8.000 -0.4323 0.09660 0.09004 -0.0086 1.0000 0.1452
-7.750 -0.4194 0.09254 0.08601 -0.0078 1.0000 0.1471
-7.500 -0.4159 0.08867 0.08220 -0.0086 1.0000 0.1489
-7.250 -0.4930 0.07879 0.07170 -0.0210 1.0000 0.0775
-7.000 -0.4836 0.07410 0.06697 -0.0221 1.0000 0.0702
-6.750 -0.4797 0.06853 0.06120 -0.0250 1.0000 0.0651
-6.500 -0.4679 0.06508 0.05769 -0.0253 1.0000 0.0635
-6.250 -0.4575 0.06115 0.05362 -0.0261 1.0000 0.0622
-6.000 -0.4461 0.05727 0.04953 -0.0268 1.0000 0.0615
-5.750 -0.4329 0.05372 0.04575 -0.0270 1.0000 0.0615
-5.500 -0.4183 0.05040 0.04218 -0.0269 1.0000 0.0616
-5.250 -0.4026 0.04722 0.03871 -0.0265 1.0000 0.0615
-5.000 -0.3857 0.04413 0.03528 -0.0259 1.0000 0.0610
-4.750 -0.3677 0.04119 0.03195 -0.0251 1.0000 0.0604
-4.500 -0.3486 0.03860 0.02900 -0.0242 1.0000 0.0601
-4.250 -0.3286 0.03633 0.02642 -0.0231 1.0000 0.0603
-4.000 -0.3081 0.03447 0.02434 -0.0221 1.0000 0.0614
-3.750 -0.2869 0.03271 0.02229 -0.0211 1.0000 0.0632
-3.500 -0.2645 0.03096 0.02014 -0.0200 1.0000 0.0650
-3.250 -0.2427 0.02958 0.01870 -0.0190 1.0000 0.0664
-3.000 -0.2201 0.02824 0.01720 -0.0179 1.0000 0.0678
-2.750 -0.1970 0.02705 0.01579 -0.0168 1.0000 0.0702
-2.500 -0.1746 0.02608 0.01483 -0.0159 1.0000 0.0735
-2.250 -0.1514 0.02518 0.01380 -0.0147 1.0000 0.0772
-2.000 -0.1285 0.02438 0.01304 -0.0137 1.0000 0.0805
-1.750 -0.1056 0.02374 0.01236 -0.0127 1.0000 0.0861
-1.500 -0.0832 0.02319 0.01178 -0.0118 1.0000 0.0928
-1.250 -0.0544 0.02259 0.01123 -0.0123 0.9962 0.1024
-1.000 -0.0055 0.02177 0.01054 -0.0166 0.9810 0.1256
-0.750 0.0416 0.02025 0.00975 -0.0209 0.9669 0.2269
-0.500 0.1015 0.01788 0.00974 -0.0238 0.9573 1.0000
-0.250 0.1519 0.01792 0.00947 -0.0279 0.9372 1.0000
0.000 0.1931 0.01789 0.00924 -0.0300 0.9117 1.0000
0.250 0.2343 0.01779 0.00897 -0.0317 0.8833 1.0000
0.500 0.2673 0.01767 0.00870 -0.0316 0.8471 1.0000
0.750 0.2967 0.01755 0.00841 -0.0306 0.8062 1.0000
1.000 0.3224 0.01749 0.00815 -0.0289 0.7606 1.0000
1.250 0.3464 0.01750 0.00792 -0.0270 0.7109 1.0000
1.500 0.3695 0.01761 0.00773 -0.0249 0.6568 1.0000
1.750 0.3918 0.01783 0.00759 -0.0229 0.5997 1.0000
2.000 0.4136 0.01819 0.00755 -0.0210 0.5430 1.0000
2.250 0.4354 0.01867 0.00762 -0.0194 0.4903 1.0000
2.500 0.4575 0.01921 0.00780 -0.0180 0.4431 1.0000
2.750 0.4799 0.01980 0.00807 -0.0169 0.4017 1.0000
3.000 0.5029 0.02043 0.00840 -0.0160 0.3661 1.0000
3.250 0.5266 0.02109 0.00880 -0.0153 0.3351 1.0000
3.500 0.5508 0.02175 0.00924 -0.0147 0.3088 1.0000
3.750 0.5753 0.02242 0.00975 -0.0142 0.2860 1.0000
4.000 0.6001 0.02310 0.01030 -0.0137 0.2673 1.0000
4.250 0.6249 0.02380 0.01086 -0.0132 0.2516 1.0000
4.750 0.6750 0.02524 0.01215 -0.0123 0.2266 1.0000
5.000 0.7001 0.02602 0.01285 -0.0119 0.2170 1.0000
5.250 0.7252 0.02681 0.01360 -0.0115 0.2082 1.0000
5.500 0.7503 0.02768 0.01442 -0.0111 0.2007 1.0000
5.750 0.7753 0.02856 0.01536 -0.0107 0.1936 1.0000
6.000 0.8002 0.02949 0.01615 -0.0103 0.1884 1.0000
6.250 0.8248 0.03057 0.01743 -0.0099 0.1823 1.0000
6.500 0.8490 0.03159 0.01848 -0.0095 0.1771 1.0000
6.750 0.8735 0.03264 0.01944 -0.0092 0.1732 1.0000
7.000 0.8966 0.03403 0.02110 -0.0088 0.1690 1.0000
7.250 0.9193 0.03539 0.02264 -0.0083 0.1649 1.0000
7.500 0.9421 0.03663 0.02395 -0.0079 0.1613 1.0000
7.750 0.9655 0.03787 0.02513 -0.0076 0.1584 1.0000
8.000 0.9843 0.03983 0.02747 -0.0070 0.1554 1.0000
8.250 1.0024 0.04184 0.02981 -0.0064 0.1526 1.0000
8.500 1.0202 0.04375 0.03196 -0.0058 0.1499 1.0000
8.750 1.0387 0.04546 0.03381 -0.0053 0.1474 1.0000
9.000 1.0586 0.04704 0.03542 -0.0048 0.1453 1.0000
9.250 1.0692 0.04979 0.03851 -0.0041 0.1433 1.0000
9.500 1.0722 0.05334 0.04254 -0.0032 0.1417 1.0000
9.750 1.0705 0.05722 0.04684 -0.0024 0.1401 1.0000
10.000 1.0631 0.06144 0.05141 -0.0017 0.1386 1.0000
10.250 1.0477 0.06621 0.05648 -0.0014 0.1373 1.0000
10.500 1.0125 0.07260 0.06313 -0.0018 0.1365 1.0000
10.750 0.9130 0.09201 0.08276 -0.0149 0.1365 1.0000
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Polar data table (+)
Polar graphs
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