SIKORSKY SSC-A07 AIRFOIL (ssca07-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SIKORSKY SSC-A07 AIRFOIL (ssca07-il) Reynolds number: 100,000 Max Cl/Cd: 37.75 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ssca07-il-100000-n5.txt Download as CSV file: xf-ssca07-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4982 0.10547 0.10104 0.0067 1.0000 0.0442
-9.250 -0.4980 0.10140 0.09696 0.0055 1.0000 0.0453
-8.750 -0.6267 0.10194 0.09742 0.0085 1.0000 0.0411
-8.500 -0.6207 0.09803 0.09353 0.0090 1.0000 0.0422
-8.250 -0.6170 0.09390 0.08942 0.0072 1.0000 0.0432
-8.000 -0.6149 0.08941 0.08496 0.0037 1.0000 0.0440
-7.250 -0.6028 0.07477 0.07023 -0.0091 1.0000 0.0468
-6.250 -0.5521 0.05245 0.04686 -0.0190 1.0000 0.0262
-6.000 -0.5370 0.04809 0.04228 -0.0196 1.0000 0.0250
-5.750 -0.5192 0.04388 0.03775 -0.0200 1.0000 0.0239
-5.500 -0.4990 0.04014 0.03362 -0.0200 1.0000 0.0244
-5.250 -0.4768 0.03693 0.02993 -0.0196 1.0000 0.0259
-5.000 -0.4546 0.03378 0.02635 -0.0192 1.0000 0.0260
-4.750 -0.4320 0.03076 0.02292 -0.0186 1.0000 0.0255
-4.500 -0.4087 0.02813 0.01988 -0.0178 1.0000 0.0253
-4.250 -0.3851 0.02587 0.01722 -0.0168 1.0000 0.0252
-4.000 -0.3617 0.02391 0.01493 -0.0158 1.0000 0.0252
-3.750 -0.3386 0.02223 0.01293 -0.0146 1.0000 0.0255
-3.500 -0.3158 0.02079 0.01128 -0.0134 1.0000 0.0261
-3.250 -0.2932 0.01968 0.01001 -0.0122 1.0000 0.0273
-3.000 -0.2717 0.01829 0.00863 -0.0112 1.0000 0.0304
-2.750 -0.2500 0.01736 0.00768 -0.0102 1.0000 0.0332
-2.500 -0.2279 0.01652 0.00677 -0.0091 1.0000 0.0356
-2.250 -0.2051 0.01587 0.00594 -0.0082 1.0000 0.0390
-2.000 -0.1819 0.01522 0.00526 -0.0076 1.0000 0.0493
-1.750 -0.1577 0.01450 0.00463 -0.0070 1.0000 0.0758
-1.500 -0.0792 0.01158 0.00496 -0.0123 1.0000 0.9969
-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 -0.0380 0.01150 0.00440 -0.0067 0.9972 1.0000
-0.500 -0.0025 0.01157 0.00431 -0.0088 0.9913 1.0000
-0.250 0.0347 0.01166 0.00425 -0.0112 0.9856 1.0000
0.000 0.0719 0.01176 0.00425 -0.0136 0.9796 1.0000
0.250 0.1152 0.01185 0.00428 -0.0171 0.9727 1.0000
0.500 0.1674 0.01187 0.00426 -0.0218 0.9536 1.0000
0.750 0.2055 0.01181 0.00417 -0.0230 0.9263 1.0000
1.000 0.2313 0.01178 0.00410 -0.0220 0.9049 1.0000
1.250 0.2539 0.01177 0.00409 -0.0206 0.8864 1.0000
1.500 0.2765 0.01175 0.00409 -0.0192 0.8680 1.0000
1.750 0.2991 0.01171 0.00405 -0.0176 0.8489 1.0000
2.000 0.3219 0.01168 0.00404 -0.0161 0.8257 1.0000
2.250 0.3446 0.01165 0.00402 -0.0146 0.7993 1.0000
2.500 0.3673 0.01163 0.00398 -0.0129 0.7654 1.0000
2.750 0.3899 0.01163 0.00398 -0.0112 0.7124 1.0000
3.000 0.4103 0.01175 0.00379 -0.0087 0.6209 1.0000
3.250 0.4308 0.01233 0.00379 -0.0067 0.4961 1.0000
3.500 0.4535 0.01314 0.00407 -0.0059 0.3882 1.0000
3.750 0.4779 0.01385 0.00445 -0.0056 0.3231 1.0000
4.000 0.5031 0.01443 0.00492 -0.0053 0.2842 1.0000
4.250 0.5286 0.01498 0.00538 -0.0051 0.2567 1.0000
4.500 0.5542 0.01552 0.00587 -0.0050 0.2343 1.0000
4.750 0.5798 0.01605 0.00637 -0.0048 0.2125 1.0000
5.000 0.6055 0.01656 0.00688 -0.0047 0.1920 1.0000
5.250 0.6312 0.01707 0.00748 -0.0045 0.1724 1.0000
5.500 0.6568 0.01759 0.00803 -0.0044 0.1512 1.0000
5.750 0.6824 0.01813 0.00859 -0.0043 0.1262 1.0000
6.000 0.7079 0.01875 0.00925 -0.0042 0.0970 1.0000
6.250 0.7324 0.01965 0.01010 -0.0040 0.0700 1.0000
6.500 0.7560 0.02086 0.01131 -0.0036 0.0560 1.0000
6.750 0.7792 0.02212 0.01264 -0.0032 0.0460 1.0000
7.000 0.8015 0.02357 0.01417 -0.0028 0.0401 1.0000
7.250 0.8240 0.02523 0.01605 -0.0021 0.0370 1.0000
7.500 0.8466 0.02688 0.01797 -0.0014 0.0338 1.0000
7.750 0.8682 0.02838 0.01965 -0.0011 0.0302 1.0000
8.000 0.8877 0.03085 0.02234 -0.0004 0.0281 1.0000
8.250 0.9079 0.03333 0.02527 0.0004 0.0270 1.0000
8.500 0.9254 0.03636 0.02881 0.0012 0.0259 1.0000
8.750 0.9391 0.03995 0.03295 0.0021 0.0251 1.0000
9.000 0.9477 0.04410 0.03768 0.0031 0.0246 1.0000
9.250 0.9517 0.04832 0.04241 0.0038 0.0237 1.0000
9.500 0.9531 0.05216 0.04663 0.0043 0.0226 1.0000
9.750 0.9516 0.05577 0.05053 0.0045 0.0216 1.0000
10.000 0.9418 0.06005 0.05508 0.0045 0.0212 1.0000
10.250 0.9060 0.06827 0.06364 0.0014 0.0224 1.0000
10.500 0.8656 0.08240 0.07795 -0.0106 0.0248 1.0000
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Polar data table (+)
Polar graphs
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