SIKORSKY SSC-A07 AIRFOIL (ssca07-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY SSC-A07 AIRFOIL (ssca07-il) Reynolds number: 50,000 Max Cl/Cd: 29.66 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ssca07-il-50000.txt Download as CSV file: xf-ssca07-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6076 0.10568 0.09940 0.0243 1.0000 0.2528
-8.000 -0.6054 0.10228 0.09606 0.0241 1.0000 0.2696
-7.750 -0.6122 0.09949 0.09336 0.0228 1.0000 0.2867
-7.500 -0.5948 0.09513 0.08900 0.0253 1.0000 0.3102
-7.250 -0.5884 0.09164 0.08556 0.0265 1.0000 0.3356
-7.000 -0.5807 0.08838 0.08235 0.0285 1.0000 0.3663
-6.750 -0.5879 0.08618 0.08024 0.0298 1.0000 0.3989
-6.500 -0.5561 0.08184 0.07586 0.0347 1.0000 0.4462
-6.250 -0.5516 0.07964 0.07372 0.0388 1.0000 0.4963
-6.000 -0.5211 0.07614 0.07014 0.0442 1.0000 0.5656
-5.000 -0.4899 0.04559 0.03759 -0.0210 1.0000 0.1769
-4.750 -0.4566 0.04111 0.03214 -0.0216 1.0000 0.1343
-4.500 -0.4293 0.03784 0.02817 -0.0211 1.0000 0.1208
-4.250 -0.4049 0.03453 0.02460 -0.0206 1.0000 0.1187
-4.000 -0.3793 0.03176 0.02148 -0.0198 1.0000 0.1157
-3.750 -0.3521 0.02931 0.01856 -0.0188 1.0000 0.1111
-3.500 -0.3249 0.02731 0.01608 -0.0176 1.0000 0.1089
-3.250 -0.2985 0.02537 0.01397 -0.0164 1.0000 0.1101
-3.000 -0.2727 0.02378 0.01231 -0.0151 1.0000 0.1176
-2.750 -0.2470 0.02229 0.01080 -0.0137 1.0000 0.1297
-2.500 -0.1306 0.01621 0.00790 -0.0208 1.0000 1.0000
-2.250 -0.1123 0.01598 0.00715 -0.0195 1.0000 1.0000
-2.000 -0.0964 0.01580 0.00664 -0.0181 1.0000 1.0000
-1.750 -0.0828 0.01566 0.00624 -0.0161 1.0000 1.0000
-1.500 -0.0712 0.01557 0.00589 -0.0138 1.0000 1.0000
-1.250 -0.0606 0.01551 0.00564 -0.0112 1.0000 1.0000
-1.000 -0.0493 0.01548 0.00543 -0.0088 1.0000 1.0000
-0.750 -0.0362 0.01548 0.00526 -0.0066 1.0000 1.0000
-0.500 -0.0210 0.01552 0.00513 -0.0048 1.0000 1.0000
-0.250 -0.0040 0.01558 0.00504 -0.0034 1.0000 1.0000
0.000 0.0145 0.01567 0.00498 -0.0022 1.0000 1.0000
0.250 0.0340 0.01579 0.00499 -0.0012 1.0000 1.0000
0.500 0.0543 0.01593 0.00505 -0.0005 1.0000 1.0000
0.750 0.0751 0.01610 0.00516 0.0002 1.0000 1.0000
1.000 0.0964 0.01630 0.00532 0.0007 1.0000 1.0000
1.250 0.1180 0.01653 0.00553 0.0012 1.0000 1.0000
1.500 0.1398 0.01678 0.00580 0.0015 1.0000 1.0000
1.750 0.1617 0.01708 0.00612 0.0017 1.0000 1.0000
2.000 0.1836 0.01741 0.00651 0.0019 1.0000 1.0000
2.250 0.2054 0.01779 0.00697 0.0020 1.0000 1.0000
2.500 0.2271 0.01822 0.00752 0.0020 1.0000 1.0000
2.750 0.2484 0.01872 0.00815 0.0019 1.0000 1.0000
3.000 0.2693 0.01931 0.00889 0.0016 1.0000 1.0000
3.250 0.3292 0.02028 0.01020 -0.0061 0.9808 1.0000
3.500 0.4613 0.02041 0.01131 -0.0234 0.9006 1.0000
3.750 0.5122 0.01886 0.01027 -0.0210 0.7998 1.0000
4.000 0.5289 0.01783 0.00886 -0.0121 0.6306 1.0000
4.250 0.5452 0.01902 0.00904 -0.0076 0.5086 1.0000
4.500 0.5679 0.02041 0.00997 -0.0060 0.4463 1.0000
4.750 0.5931 0.02175 0.01114 -0.0051 0.4015 1.0000
5.000 0.6180 0.02311 0.01237 -0.0042 0.3639 1.0000
5.250 0.6425 0.02451 0.01384 -0.0034 0.3257 1.0000
5.500 0.6662 0.02608 0.01540 -0.0026 0.2869 1.0000
5.750 0.6894 0.02793 0.01724 -0.0017 0.2465 1.0000
6.000 0.7125 0.03014 0.01936 -0.0007 0.2091 1.0000
6.250 0.7350 0.03239 0.02189 0.0001 0.1762 1.0000
6.500 0.7584 0.03502 0.02454 0.0009 0.1553 1.0000
6.750 0.7796 0.03788 0.02795 0.0016 0.1381 1.0000
7.000 0.8007 0.04152 0.03208 0.0022 0.1300 1.0000
7.250 0.8178 0.04596 0.03708 0.0027 0.1251 1.0000
7.500 0.8309 0.05031 0.04205 0.0030 0.1191 1.0000
7.750 0.8475 0.05397 0.04575 0.0035 0.1136 1.0000
8.000 0.8550 0.05964 0.05199 0.0033 0.1149 1.0000
8.250 0.8407 0.06830 0.06141 0.0005 0.1227 1.0000
8.500 0.8442 0.07423 0.06748 -0.0005 0.1262 1.0000
8.750 0.8223 0.08324 0.07673 -0.0064 0.1386 1.0000
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Polar data table (+)
Polar graphs
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