SIKORSKY SSC-A07 AIRFOIL (ssca07-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY SSC-A07 AIRFOIL (ssca07-il) Reynolds number: 100,000 Max Cl/Cd: 39.42 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ssca07-il-100000.txt Download as CSV file: xf-ssca07-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SSC-A07 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6179 0.09740 0.09296 0.0102 1.0000 0.0763
-8.000 -0.6229 0.09254 0.08816 0.0019 1.0000 0.0782
-7.750 -0.6292 0.08785 0.08331 -0.0090 1.0000 0.0794
-7.500 -0.6187 0.08209 0.07768 -0.0065 1.0000 0.0819
-7.250 -0.6080 0.07851 0.07408 -0.0058 1.0000 0.0866
-7.000 -0.6070 0.07453 0.06973 -0.0152 1.0000 0.0929
-6.750 -0.5950 0.06876 0.06411 -0.0139 1.0000 0.0963
-6.500 -0.5823 0.06519 0.06042 -0.0157 1.0000 0.1048
-6.250 -0.5709 0.06062 0.05578 -0.0169 1.0000 0.1113
-6.000 -0.5576 0.05673 0.05166 -0.0189 1.0000 0.1233
-5.750 -0.5425 0.05317 0.04798 -0.0196 1.0000 0.1372
-5.500 -0.5266 0.04982 0.04462 -0.0195 1.0000 0.1535
-5.250 -0.5119 0.04687 0.04163 -0.0193 1.0000 0.1810
-4.750 -0.4835 0.04154 0.03637 -0.0168 1.0000 0.2527
-4.000 -0.3738 0.02787 0.01963 -0.0183 1.0000 0.0766
-3.750 -0.3475 0.02572 0.01686 -0.0164 1.0000 0.0652
-3.500 -0.3244 0.02321 0.01417 -0.0152 1.0000 0.0621
-3.250 -0.3002 0.02137 0.01208 -0.0138 1.0000 0.0599
-3.000 -0.2763 0.01997 0.01051 -0.0126 1.0000 0.0615
-2.750 -0.2526 0.01896 0.00933 -0.0114 1.0000 0.0654
-2.500 -0.2292 0.01748 0.00786 -0.0102 1.0000 0.0677
-2.250 -0.2068 0.01630 0.00678 -0.0091 1.0000 0.0730
-2.000 -0.1837 0.01538 0.00586 -0.0082 1.0000 0.0855
-1.750 -0.0750 0.01166 0.00515 -0.0174 1.0000 1.0000
-1.500 -0.0692 0.01157 0.00489 -0.0142 1.0000 1.0000
-1.250 -0.0650 0.01151 0.00470 -0.0106 1.0000 1.0000
-1.000 -0.0585 0.01148 0.00454 -0.0073 1.0000 1.0000
-0.750 -0.0473 0.01149 0.00441 -0.0049 1.0000 1.0000
-0.500 -0.0312 0.01154 0.00432 -0.0034 1.0000 1.0000
-0.250 -0.0122 0.01162 0.00428 -0.0023 1.0000 1.0000
0.000 0.0085 0.01173 0.00427 -0.0016 1.0000 1.0000
0.250 0.0303 0.01187 0.00432 -0.0011 1.0000 1.0000
0.500 0.0528 0.01203 0.00443 -0.0008 1.0000 1.0000
0.750 0.0757 0.01222 0.00457 -0.0006 1.0000 1.0000
1.000 0.0988 0.01244 0.00477 -0.0004 1.0000 1.0000
1.250 0.1221 0.01269 0.00501 -0.0004 1.0000 1.0000
1.500 0.1624 0.01303 0.00537 -0.0036 0.9945 1.0000
1.750 0.2264 0.01337 0.00579 -0.0112 0.9772 1.0000
2.000 0.2930 0.01356 0.00615 -0.0189 0.9598 1.0000
2.250 0.3482 0.01359 0.00635 -0.0238 0.9391 1.0000
2.500 0.3925 0.01348 0.00640 -0.0259 0.9157 1.0000
2.750 0.4218 0.01325 0.00635 -0.0246 0.8882 1.0000
3.000 0.4430 0.01294 0.00615 -0.0215 0.8562 1.0000
3.250 0.4614 0.01255 0.00585 -0.0176 0.8158 1.0000
3.500 0.4780 0.01217 0.00546 -0.0131 0.7436 1.0000
3.750 0.4896 0.01242 0.00482 -0.0072 0.5390 1.0000
4.000 0.5083 0.01390 0.00531 -0.0053 0.3938 1.0000
4.250 0.5322 0.01492 0.00596 -0.0047 0.3415 1.0000
4.500 0.5571 0.01582 0.00663 -0.0043 0.3087 1.0000
4.750 0.5823 0.01663 0.00731 -0.0040 0.2804 1.0000
5.000 0.6079 0.01738 0.00803 -0.0038 0.2548 1.0000
5.250 0.6334 0.01815 0.00886 -0.0036 0.2295 1.0000
5.500 0.6583 0.01892 0.00963 -0.0033 0.2009 1.0000
5.750 0.6825 0.01977 0.01042 -0.0031 0.1658 1.0000
6.000 0.7062 0.02084 0.01138 -0.0027 0.1285 1.0000
6.250 0.7303 0.02215 0.01263 -0.0022 0.1013 1.0000
6.500 0.7553 0.02358 0.01427 -0.0016 0.0840 1.0000
6.750 0.7797 0.02540 0.01613 -0.0011 0.0737 1.0000
7.000 0.8050 0.02764 0.01872 -0.0003 0.0678 1.0000
7.250 0.8279 0.03073 0.02187 0.0001 0.0632 1.0000
7.500 0.8499 0.03317 0.02504 0.0010 0.0590 1.0000
7.750 0.8687 0.03699 0.02949 0.0019 0.0575 1.0000
8.000 0.8825 0.04191 0.03510 0.0028 0.0576 1.0000
8.250 0.8902 0.04776 0.04159 0.0036 0.0589 1.0000
8.500 0.8943 0.05371 0.04800 0.0039 0.0607 1.0000
8.750 0.8985 0.05949 0.05405 0.0041 0.0624 1.0000
9.000 0.8653 0.07144 0.06672 0.0008 0.0725 1.0000
9.250 0.7614 0.06461 0.06021 0.0073 0.0695 1.0000
9.500 0.7315 0.07219 0.06784 0.0034 0.0713 1.0000
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Polar data table (+)
Polar graphs
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