SIKORSKY SC1094R8 AIRFOIL (sc1095r8-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: SIKORSKY SC1094R8 AIRFOIL (sc1095r8-il) Reynolds number: 50,000 Max Cl/Cd: 27.05 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc1095r8-il-50000-n5.txt Download as CSV file: xf-sc1095r8-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4887 0.11213 0.10503 0.0001 1.0000 0.1265
-7.750 -0.4880 0.10886 0.10182 -0.0019 1.0000 0.1304
-7.500 -0.5150 0.10671 0.09982 -0.0108 1.0000 0.1345
-7.250 -0.5050 0.10192 0.09508 -0.0106 1.0000 0.1358
-7.000 -0.4884 0.09777 0.09095 -0.0086 1.0000 0.1377
-6.750 -0.4811 0.09413 0.08735 -0.0091 1.0000 0.1398
-6.250 -0.4832 0.07866 0.07163 -0.0248 1.0000 0.0732
-5.750 -0.4764 0.06783 0.06040 -0.0308 1.0000 0.0635
-5.500 -0.4660 0.06415 0.05664 -0.0312 1.0000 0.0631
-5.250 -0.4551 0.06044 0.05278 -0.0316 1.0000 0.0629
-5.000 -0.4430 0.05685 0.04900 -0.0318 1.0000 0.0628
-4.750 -0.4294 0.05343 0.04538 -0.0317 1.0000 0.0626
-4.500 -0.4146 0.05020 0.04194 -0.0313 1.0000 0.0622
-4.250 -0.3988 0.04712 0.03862 -0.0307 1.0000 0.0615
-4.000 -0.3821 0.04419 0.03543 -0.0299 1.0000 0.0610
-3.750 -0.3644 0.04145 0.03239 -0.0289 1.0000 0.0607
-3.500 -0.3457 0.03891 0.02953 -0.0278 1.0000 0.0605
-3.250 -0.3261 0.03663 0.02691 -0.0266 1.0000 0.0611
-3.000 -0.3053 0.03459 0.02446 -0.0253 1.0000 0.0626
-2.750 -0.2837 0.03278 0.02221 -0.0239 1.0000 0.0640
-2.500 -0.2628 0.03106 0.02043 -0.0228 1.0000 0.0654
-2.250 -0.2411 0.02957 0.01882 -0.0215 1.0000 0.0665
-2.000 -0.2188 0.02825 0.01735 -0.0203 1.0000 0.0678
-1.750 -0.1964 0.02714 0.01612 -0.0190 1.0000 0.0707
-1.500 -0.1734 0.02616 0.01494 -0.0176 1.0000 0.0743
-1.250 -0.1507 0.02515 0.01393 -0.0164 1.0000 0.0773
-1.000 -0.1279 0.02433 0.01312 -0.0151 1.0000 0.0807
-0.750 -0.1051 0.02372 0.01242 -0.0138 1.0000 0.0865
-0.500 -0.0829 0.02309 0.01184 -0.0128 1.0000 0.0930
-0.250 -0.0558 0.02255 0.01123 -0.0125 0.9973 0.1021
0.000 -0.0062 0.02169 0.01051 -0.0164 0.9827 0.1256
0.250 0.0403 0.02019 0.00971 -0.0200 0.9680 0.2250
0.500 0.0996 0.01782 0.00970 -0.0221 0.9585 1.0000
0.750 0.1482 0.01786 0.00944 -0.0254 0.9373 1.0000
1.000 0.1918 0.01784 0.00921 -0.0274 0.9130 1.0000
1.250 0.2328 0.01774 0.00894 -0.0287 0.8845 1.0000
1.500 0.2657 0.01762 0.00867 -0.0282 0.8483 1.0000
1.750 0.2944 0.01751 0.00840 -0.0268 0.8067 1.0000
2.000 0.3204 0.01744 0.00813 -0.0249 0.7613 1.0000
2.250 0.3444 0.01745 0.00790 -0.0226 0.7117 1.0000
2.500 0.3673 0.01755 0.00771 -0.0203 0.6575 1.0000
2.750 0.3895 0.01778 0.00757 -0.0179 0.6003 1.0000
3.000 0.4111 0.01814 0.00753 -0.0158 0.5434 1.0000
3.250 0.4328 0.01861 0.00761 -0.0139 0.4904 1.0000
3.500 0.4546 0.01916 0.00778 -0.0123 0.4435 1.0000
3.750 0.4769 0.01974 0.00804 -0.0109 0.4018 1.0000
4.000 0.4997 0.02037 0.00838 -0.0097 0.3662 1.0000
4.250 0.5233 0.02101 0.00878 -0.0087 0.3347 1.0000
4.500 0.5471 0.02168 0.00921 -0.0078 0.3088 1.0000
4.750 0.5715 0.02235 0.00972 -0.0069 0.2858 1.0000
5.000 0.5960 0.02303 0.01025 -0.0061 0.2669 1.0000
5.250 0.6208 0.02372 0.01083 -0.0053 0.2513 1.0000
5.500 0.6457 0.02443 0.01144 -0.0045 0.2377 1.0000
5.750 0.6704 0.02516 0.01207 -0.0037 0.2262 1.0000
6.000 0.6953 0.02592 0.01277 -0.0030 0.2165 1.0000
6.250 0.7206 0.02675 0.01360 -0.0022 0.2082 1.0000
6.500 0.7453 0.02756 0.01434 -0.0015 0.2005 1.0000
6.750 0.7701 0.02847 0.01530 -0.0007 0.1933 1.0000
7.000 0.7945 0.02938 0.01621 0.0000 0.1867 1.0000
7.250 0.8193 0.03037 0.01708 0.0007 0.1824 1.0000
7.500 0.8436 0.03158 0.01855 0.0014 0.1774 1.0000
7.750 0.8673 0.03272 0.01979 0.0022 0.1727 1.0000
8.000 0.8910 0.03377 0.02079 0.0029 0.1686 1.0000
8.250 0.9135 0.03513 0.02230 0.0036 0.1646 1.0000
8.500 0.9348 0.03665 0.02411 0.0044 0.1605 1.0000
8.750 0.9561 0.03821 0.02584 0.0052 0.1576 1.0000
9.000 0.9773 0.03974 0.02749 0.0059 0.1551 1.0000
9.250 0.9990 0.04123 0.02901 0.0067 0.1528 1.0000
9.500 1.0160 0.04332 0.03139 0.0075 0.1504 1.0000
9.750 1.0283 0.04585 0.03435 0.0084 0.1475 1.0000
10.000 1.0403 0.04829 0.03711 0.0093 0.1447 1.0000
10.250 1.0522 0.05066 0.03973 0.0102 0.1424 1.0000
10.500 1.0626 0.05325 0.04256 0.0110 0.1408 1.0000
10.750 1.0715 0.05593 0.04544 0.0118 0.1395 1.0000
11.000 1.0795 0.05868 0.04837 0.0126 0.1383 1.0000
11.250 1.0887 0.06137 0.05117 0.0133 0.1372 1.0000
11.500 1.0630 0.06710 0.05732 0.0135 0.1364 1.0000
11.750 1.0170 0.07440 0.06494 0.0123 0.1360 1.0000
12.000 0.9362 0.08968 0.08043 0.0015 0.1360 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SIKORSKY SC1094R8 AIRFOIL (sc1095r8-il)