SIKORSKY SC1094R8 AIRFOIL (sc1095r8-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY SC1094R8 AIRFOIL (sc1095r8-il) Reynolds number: 100,000 Max Cl/Cd: 33.59 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc1095r8-il-100000.txt Download as CSV file: xf-sc1095r8-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SC1094R8 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.4834 0.09762 0.09272 -0.0045 1.0000 0.0971
-7.000 -0.4881 0.09396 0.08913 -0.0092 1.0000 0.1005
-6.750 -0.5144 0.08981 0.08487 -0.0244 1.0000 0.1026
-6.500 -0.5010 0.08416 0.07935 -0.0223 1.0000 0.1042
-6.250 -0.4824 0.08136 0.07664 -0.0175 1.0000 0.1070
-6.000 -0.4735 0.07812 0.07343 -0.0183 1.0000 0.1115
-5.750 -0.4860 0.07475 0.06957 -0.0301 1.0000 0.1187
-5.500 -0.4665 0.06936 0.06454 -0.0261 1.0000 0.1213
-5.250 -0.4527 0.06657 0.06180 -0.0248 1.0000 0.1260
-5.000 -0.4491 0.06290 0.05778 -0.0297 1.0000 0.1361
-4.750 -0.4339 0.05938 0.05445 -0.0276 1.0000 0.1393
-4.500 -0.4249 0.05737 0.05205 -0.0296 1.0000 0.1525
-4.250 -0.4108 0.05340 0.04833 -0.0276 1.0000 0.1558
-4.000 -0.4000 0.05129 0.04598 -0.0277 1.0000 0.1703
-3.750 -0.3867 0.04825 0.04312 -0.0256 1.0000 0.1755
-3.500 -0.3751 0.04583 0.04062 -0.0246 1.0000 0.1905
-3.250 -0.3631 0.04362 0.03838 -0.0233 1.0000 0.2074
-3.000 -0.3509 0.04148 0.03626 -0.0216 1.0000 0.2257
-2.750 -0.3384 0.03950 0.03434 -0.0196 1.0000 0.2465
-2.250 -0.2615 0.03121 0.02350 -0.0201 1.0000 0.1032
-2.000 -0.2406 0.02800 0.02031 -0.0192 1.0000 0.0970
-1.750 -0.2146 0.02621 0.01788 -0.0174 1.0000 0.0874
-1.500 -0.1913 0.02440 0.01593 -0.0164 1.0000 0.0859
-1.250 -0.1672 0.02305 0.01439 -0.0153 1.0000 0.0853
-1.000 -0.1433 0.02222 0.01335 -0.0143 1.0000 0.0873
-0.750 -0.1186 0.02112 0.01217 -0.0135 1.0000 0.0896
-0.500 -0.0933 0.02012 0.01123 -0.0129 1.0000 0.0921
-0.250 -0.0688 0.01949 0.01064 -0.0123 1.0000 0.0962
0.000 -0.0230 0.01860 0.00986 -0.0153 0.9931 0.1065
0.250 0.0314 0.01760 0.00907 -0.0196 0.9813 0.1258
0.500 0.0743 0.01414 0.00836 -0.0216 0.9730 0.7269
0.750 0.1590 0.01368 0.00790 -0.0279 0.9563 1.0000
1.000 0.2234 0.01338 0.00744 -0.0332 0.9343 1.0000
1.250 0.2641 0.01312 0.00707 -0.0341 0.9064 1.0000
1.500 0.2944 0.01287 0.00672 -0.0328 0.8751 1.0000
1.750 0.3182 0.01266 0.00639 -0.0303 0.8399 1.0000
2.000 0.3395 0.01250 0.00606 -0.0273 0.8006 1.0000
2.250 0.3598 0.01243 0.00580 -0.0243 0.7519 1.0000
2.500 0.3804 0.01248 0.00557 -0.0215 0.6944 1.0000
2.750 0.4013 0.01269 0.00540 -0.0189 0.6270 1.0000
3.000 0.4226 0.01309 0.00535 -0.0167 0.5565 1.0000
3.250 0.4445 0.01364 0.00544 -0.0149 0.4916 1.0000
3.500 0.4669 0.01427 0.00563 -0.0134 0.4338 1.0000
3.750 0.4898 0.01495 0.00591 -0.0122 0.3840 1.0000
4.000 0.5132 0.01568 0.00626 -0.0110 0.3438 1.0000
4.250 0.5372 0.01639 0.00666 -0.0101 0.3122 1.0000
4.500 0.5622 0.01705 0.00715 -0.0092 0.2870 1.0000
4.750 0.5873 0.01772 0.00762 -0.0083 0.2678 1.0000
5.000 0.6127 0.01837 0.00814 -0.0076 0.2520 1.0000
5.250 0.6382 0.01906 0.00871 -0.0068 0.2390 1.0000
5.500 0.6639 0.01986 0.00930 -0.0061 0.2291 1.0000
5.750 0.6900 0.02054 0.01003 -0.0054 0.2194 1.0000
6.000 0.7159 0.02141 0.01077 -0.0047 0.2118 1.0000
6.250 0.7418 0.02214 0.01155 -0.0040 0.2039 1.0000
6.500 0.7678 0.02317 0.01239 -0.0035 0.1980 1.0000
6.750 0.7936 0.02406 0.01349 -0.0028 0.1927 1.0000
7.000 0.8193 0.02501 0.01450 -0.0021 0.1879 1.0000
7.250 0.8451 0.02612 0.01551 -0.0016 0.1839 1.0000
7.500 0.8696 0.02741 0.01699 -0.0009 0.1801 1.0000
7.750 0.8937 0.02856 0.01837 -0.0001 0.1759 1.0000
8.000 0.9181 0.02973 0.01962 0.0006 0.1723 1.0000
8.250 0.9423 0.03105 0.02102 0.0012 0.1696 1.0000
8.500 0.9659 0.03298 0.02295 0.0017 0.1674 1.0000
8.750 0.9860 0.03488 0.02523 0.0026 0.1657 1.0000
9.000 1.0043 0.03701 0.02776 0.0036 0.1639 1.0000
9.250 1.0210 0.03935 0.03049 0.0046 0.1618 1.0000
9.500 1.0363 0.04180 0.03327 0.0055 0.1598 1.0000
9.750 1.0497 0.04456 0.03633 0.0064 0.1583 1.0000
10.000 1.0581 0.04810 0.04023 0.0073 0.1577 1.0000
10.250 1.0569 0.05293 0.04550 0.0080 0.1580 1.0000
10.500 1.0329 0.06064 0.05375 0.0079 0.1603 1.0000
10.750 0.9979 0.06934 0.06279 0.0064 0.1636 1.0000
11.000 0.9842 0.07527 0.06883 0.0056 0.1656 1.0000
11.250 0.9860 0.08005 0.07367 0.0051 0.1678 1.0000
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Polar data table (+)
Polar graphs
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