SIKORSKY SSC-A07 AIRFOIL (ssca07-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: SIKORSKY SSC-A07 AIRFOIL (ssca07-il) Reynolds number: 200,000 Max Cl/Cd: 48.3 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ssca07-il-200000-n5.txt Download as CSV file: xf-ssca07-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6203 0.09584 0.09262 0.0103 1.0000 0.0179
-8.250 -0.6178 0.09063 0.08743 0.0054 1.0000 0.0179
-8.000 -0.6161 0.08508 0.08188 -0.0008 1.0000 0.0179
-7.750 -0.6113 0.07979 0.07652 -0.0053 1.0000 0.0179
-7.500 -0.6049 0.07462 0.07126 -0.0088 1.0000 0.0180
-7.250 -0.5969 0.06958 0.06610 -0.0116 1.0000 0.0180
-6.750 -0.5781 0.05938 0.05562 -0.0154 1.0000 0.0178
-6.000 -0.5379 0.04458 0.04016 -0.0188 1.0000 0.0167
-5.750 -0.5205 0.04003 0.03532 -0.0193 1.0000 0.0154
-5.500 -0.5000 0.03544 0.03034 -0.0192 1.0000 0.0143
-5.250 -0.4780 0.03116 0.02560 -0.0187 1.0000 0.0136
-5.000 -0.4552 0.02764 0.02163 -0.0180 1.0000 0.0135
-4.750 -0.4324 0.02493 0.01852 -0.0171 1.0000 0.0137
-4.500 -0.4104 0.02334 0.01666 -0.0162 1.0000 0.0153
-4.250 -0.3857 0.02161 0.01459 -0.0155 0.9983 0.0164
-4.000 -0.3532 0.01949 0.01211 -0.0163 0.9947 0.0163
-3.750 -0.3216 0.01780 0.01013 -0.0169 0.9907 0.0164
-3.500 -0.2897 0.01641 0.00855 -0.0176 0.9872 0.0166
-3.250 -0.2574 0.01523 0.00727 -0.0185 0.9842 0.0171
-3.000 -0.2270 0.01432 0.00627 -0.0190 0.9798 0.0178
-2.750 -0.1969 0.01331 0.00522 -0.0197 0.9755 0.0190
-2.500 -0.1654 0.01268 0.00455 -0.0207 0.9718 0.0227
-2.250 -0.1362 0.01228 0.00407 -0.0211 0.9664 0.0270
-2.000 -0.1062 0.01179 0.00351 -0.0215 0.9615 0.0347
-1.750 -0.0785 0.01086 0.00312 -0.0220 0.9564 0.1665
-1.500 -0.0639 0.00862 0.00313 -0.0200 0.9499 0.7261
-1.250 -0.0520 0.00851 0.00349 -0.0146 0.9437 0.8841
-1.000 -0.0307 0.00864 0.00362 -0.0117 0.9375 0.9446
-0.750 -0.0004 0.00864 0.00352 -0.0120 0.9326 0.9573
-0.500 0.0316 0.00861 0.00340 -0.0128 0.9250 0.9668
-0.250 0.0609 0.00852 0.00321 -0.0126 0.9109 0.9756
0.000 0.0874 0.00836 0.00294 -0.0116 0.8899 0.9849
0.250 0.1182 0.00822 0.00271 -0.0118 0.8677 0.9928
0.500 0.1512 0.00814 0.00256 -0.0127 0.8526 1.0000
0.750 0.1739 0.00809 0.00245 -0.0116 0.8384 1.0000
1.000 0.1969 0.00805 0.00236 -0.0105 0.8231 1.0000
1.250 0.2205 0.00804 0.00229 -0.0095 0.8059 1.0000
1.500 0.2449 0.00804 0.00224 -0.0087 0.7847 1.0000
1.750 0.2693 0.00805 0.00219 -0.0078 0.7562 1.0000
2.000 0.2936 0.00810 0.00212 -0.0068 0.7125 1.0000
2.250 0.3172 0.00829 0.00202 -0.0056 0.6409 1.0000
2.500 0.3415 0.00876 0.00202 -0.0049 0.5390 1.0000
2.750 0.3669 0.00944 0.00218 -0.0048 0.4253 1.0000
3.000 0.3931 0.01004 0.00244 -0.0049 0.3422 1.0000
3.250 0.4199 0.01050 0.00268 -0.0051 0.2930 1.0000
3.500 0.4469 0.01088 0.00293 -0.0053 0.2590 1.0000
3.750 0.4739 0.01125 0.00321 -0.0054 0.2330 1.0000
4.000 0.5009 0.01162 0.00353 -0.0055 0.2114 1.0000
4.250 0.5279 0.01197 0.00382 -0.0056 0.1905 1.0000
4.500 0.5549 0.01231 0.00414 -0.0057 0.1745 1.0000
4.750 0.5819 0.01265 0.00448 -0.0058 0.1600 1.0000
5.000 0.6088 0.01300 0.00486 -0.0059 0.1447 1.0000
5.250 0.6356 0.01337 0.00521 -0.0060 0.1273 1.0000
5.500 0.6625 0.01373 0.00558 -0.0060 0.1051 1.0000
5.750 0.6887 0.01426 0.00601 -0.0061 0.0763 1.0000
6.000 0.7140 0.01504 0.00664 -0.0061 0.0517 1.0000
6.250 0.7394 0.01585 0.00747 -0.0060 0.0390 1.0000
6.500 0.7650 0.01658 0.00833 -0.0058 0.0325 1.0000
6.750 0.7896 0.01757 0.00939 -0.0056 0.0275 1.0000
7.000 0.8148 0.01831 0.01028 -0.0054 0.0240 1.0000
7.250 0.8392 0.01926 0.01135 -0.0052 0.0217 1.0000
7.500 0.8616 0.02068 0.01288 -0.0048 0.0199 1.0000
7.750 0.8837 0.02223 0.01464 -0.0042 0.0189 1.0000
8.000 0.9064 0.02369 0.01633 -0.0037 0.0181 1.0000
8.250 0.9282 0.02542 0.01833 -0.0031 0.0173 1.0000
8.500 0.9499 0.02697 0.02014 -0.0026 0.0160 1.0000
8.750 0.9708 0.02840 0.02179 -0.0021 0.0147 1.0000
9.000 0.9895 0.03033 0.02399 -0.0015 0.0139 1.0000
9.250 1.0056 0.03256 0.02645 -0.0009 0.0131 1.0000
9.500 1.0155 0.03599 0.03033 0.0000 0.0122 1.0000
9.750 1.0281 0.03839 0.03322 0.0008 0.0112 1.0000
10.000 1.0323 0.04203 0.03732 0.0019 0.0107 1.0000
10.250 1.0292 0.04623 0.04196 0.0029 0.0103 1.0000
10.500 1.0180 0.05062 0.04672 0.0037 0.0102 1.0000
10.750 0.9999 0.05533 0.05170 0.0035 0.0101 1.0000
11.000 0.9787 0.06153 0.05815 0.0003 0.0102 1.0000
11.250 0.9554 0.07118 0.06802 -0.0085 0.0105 1.0000
11.500 0.9266 0.08690 0.08382 -0.0215 0.0112 1.0000
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Polar data table (+)
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