SIKORSKY SSC-A07 AIRFOIL (ssca07-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY SSC-A07 AIRFOIL (ssca07-il) Reynolds number: 500,000 Max Cl/Cd: 64.81 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ssca07-il-500000.txt Download as CSV file: xf-ssca07-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6326 0.09613 0.09411 0.0179 1.0000 0.0113
-8.250 -0.6294 0.09122 0.08922 0.0137 1.0000 0.0113
-8.000 -0.6270 0.08573 0.08375 0.0076 1.0000 0.0114
-7.750 -0.6226 0.07973 0.07772 0.0004 1.0000 0.0114
-7.500 -0.6145 0.07412 0.07203 -0.0045 1.0000 0.0114
-7.250 -0.6045 0.06870 0.06651 -0.0084 1.0000 0.0114
-7.000 -0.5927 0.06344 0.06113 -0.0113 1.0000 0.0115
-6.750 -0.5791 0.05833 0.05585 -0.0136 1.0000 0.0115
-6.500 -0.5692 0.05131 0.04860 -0.0158 1.0000 0.0117
-6.250 -0.5609 0.04495 0.04204 -0.0176 1.0000 0.0123
-6.000 -0.5427 0.04186 0.03880 -0.0186 1.0000 0.0129
-5.750 -0.5221 0.03881 0.03558 -0.0194 1.0000 0.0137
-5.500 -0.4993 0.03560 0.03214 -0.0198 1.0000 0.0154
-5.250 -0.4675 0.03511 0.03131 -0.0188 1.0000 0.0180
-4.750 -0.4319 0.02570 0.02130 -0.0190 0.9976 0.0207
-4.500 -0.3994 0.02391 0.01933 -0.0206 0.9952 0.0238
-4.250 -0.3623 0.02480 0.01994 -0.0212 0.9922 0.0277
-4.000 -0.3347 0.01908 0.01380 -0.0225 0.9887 0.0311
-3.750 -0.3021 0.01769 0.01228 -0.0237 0.9856 0.0349
-3.500 -0.2715 0.01640 0.01081 -0.0246 0.9817 0.0444
-3.250 -0.2388 0.01287 0.00679 -0.0226 0.9772 0.0196
-3.000 -0.2104 0.01234 0.00620 -0.0225 0.9723 0.0187
-2.750 -0.1852 0.01169 0.00551 -0.0217 0.9661 0.0184
-2.500 -0.1619 0.01084 0.00459 -0.0206 0.9600 0.0185
-2.250 -0.1379 0.00994 0.00361 -0.0197 0.9541 0.0199
-2.000 -0.1138 0.00952 0.00315 -0.0188 0.9483 0.0230
-1.750 -0.0890 0.00928 0.00286 -0.0179 0.9431 0.0276
-1.500 -0.0667 0.00740 0.00231 -0.0177 0.9368 0.4082
-1.250 -0.0500 0.00612 0.00228 -0.0154 0.9288 0.7546
-1.000 -0.0349 0.00585 0.00225 -0.0116 0.9169 0.8359
-0.750 -0.0221 0.00568 0.00221 -0.0071 0.9032 0.8973
-0.500 -0.0128 0.00561 0.00219 -0.0017 0.8912 0.9483
-0.250 0.0116 0.00553 0.00209 -0.0001 0.8825 0.9793
0.000 0.0473 0.00548 0.00195 -0.0016 0.8756 0.9873
0.250 0.0843 0.00544 0.00187 -0.0035 0.8671 0.9932
0.500 0.1218 0.00541 0.00178 -0.0056 0.8580 0.9976
0.750 0.1516 0.00536 0.00168 -0.0060 0.8470 1.0000
1.000 0.1763 0.00532 0.00158 -0.0054 0.8352 1.0000
1.250 0.2016 0.00529 0.00151 -0.0049 0.8220 1.0000
1.500 0.2273 0.00529 0.00145 -0.0044 0.8067 1.0000
1.750 0.2538 0.00530 0.00143 -0.0041 0.7860 1.0000
2.000 0.2805 0.00534 0.00139 -0.0038 0.7576 1.0000
2.250 0.3075 0.00544 0.00135 -0.0036 0.7133 1.0000
2.500 0.3345 0.00578 0.00133 -0.0035 0.6237 1.0000
2.750 0.3623 0.00645 0.00146 -0.0039 0.4941 1.0000
3.000 0.3901 0.00720 0.00169 -0.0045 0.3665 1.0000
3.250 0.4180 0.00774 0.00190 -0.0050 0.2901 1.0000
3.500 0.4460 0.00817 0.00210 -0.0054 0.2409 1.0000
3.750 0.4740 0.00849 0.00230 -0.0057 0.2127 1.0000
4.000 0.5021 0.00877 0.00253 -0.0060 0.1935 1.0000
4.250 0.5302 0.00902 0.00274 -0.0063 0.1783 1.0000
4.500 0.5582 0.00927 0.00296 -0.0065 0.1647 1.0000
4.750 0.5862 0.00952 0.00319 -0.0068 0.1514 1.0000
5.000 0.6141 0.00976 0.00343 -0.0070 0.1374 1.0000
5.250 0.6419 0.01001 0.00366 -0.0072 0.1205 1.0000
5.500 0.6695 0.01033 0.00391 -0.0074 0.0973 1.0000
5.750 0.6961 0.01096 0.00431 -0.0076 0.0574 1.0000
6.000 0.7226 0.01170 0.00498 -0.0077 0.0373 1.0000
6.250 0.7488 0.01256 0.00588 -0.0077 0.0280 1.0000
6.500 0.7757 0.01311 0.00652 -0.0076 0.0249 1.0000
6.750 0.8018 0.01384 0.00731 -0.0076 0.0222 1.0000
7.000 0.8253 0.01537 0.00898 -0.0072 0.0199 1.0000
7.250 0.8489 0.01687 0.01065 -0.0067 0.0190 1.0000
7.500 0.8744 0.01767 0.01159 -0.0065 0.0183 1.0000
7.750 0.8990 0.01873 0.01281 -0.0062 0.0174 1.0000
8.000 0.9235 0.01971 0.01391 -0.0059 0.0162 1.0000
8.250 0.9480 0.02047 0.01478 -0.0058 0.0149 1.0000
8.500 0.9709 0.02168 0.01611 -0.0055 0.0139 1.0000
8.750 0.9857 0.02553 0.02033 -0.0045 0.0127 1.0000
9.000 1.0034 0.02806 0.02325 -0.0036 0.0120 1.0000
9.250 1.0215 0.03013 0.02564 -0.0029 0.0113 1.0000
9.500 1.0374 0.03236 0.02821 -0.0021 0.0104 1.0000
9.750 1.0564 0.03335 0.02931 -0.0017 0.0095 1.0000
10.000 1.0741 0.03431 0.03038 -0.0013 0.0088 1.0000
10.250 1.0827 0.03693 0.03322 -0.0005 0.0084 1.0000
10.500 1.0779 0.04134 0.03800 0.0009 0.0081 1.0000
10.750 1.0637 0.04603 0.04303 0.0023 0.0080 1.0000
11.000 1.0450 0.05036 0.04760 0.0030 0.0080 1.0000
11.250 1.0279 0.05534 0.05280 0.0013 0.0080 1.0000
11.500 1.0130 0.06156 0.05922 -0.0034 0.0080 1.0000
11.750 0.9994 0.07106 0.06893 -0.0129 0.0082 1.0000
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Polar data table (+)
Polar graphs
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