SIKORSKY SC1095 AIRFOIL (sc1095-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: SIKORSKY SC1095 AIRFOIL (sc1095-il) Reynolds number: 100,000 Max Cl/Cd: 34.17 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc1095-il-100000.txt Download as CSV file: xf-sc1095-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SC1095 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6357 0.10365 0.09883 0.0098 1.0000 0.1515
-9.250 -0.7182 0.07845 0.07368 -0.0171 1.0000 0.0946
-9.000 -0.7270 0.07187 0.06698 -0.0195 1.0000 0.0942
-8.750 -0.7346 0.06527 0.06021 -0.0213 1.0000 0.0937
-8.500 -0.7421 0.05850 0.05311 -0.0228 1.0000 0.0935
-8.250 -0.7465 0.05193 0.04599 -0.0234 1.0000 0.0941
-8.000 -0.7423 0.04648 0.03989 -0.0230 1.0000 0.0949
-7.750 -0.7189 0.04529 0.03905 -0.0227 1.0000 0.1010
-7.500 -0.7062 0.04121 0.03451 -0.0223 1.0000 0.1033
-7.250 -0.6912 0.03720 0.02994 -0.0217 1.0000 0.1051
-7.000 -0.6736 0.03425 0.02621 -0.0207 1.0000 0.1091
-6.750 -0.6525 0.03151 0.02338 -0.0204 1.0000 0.1129
-6.500 -0.6293 0.02962 0.02129 -0.0198 1.0000 0.1171
-6.250 -0.6063 0.02790 0.01899 -0.0190 1.0000 0.1236
-6.000 -0.5828 0.02609 0.01722 -0.0186 1.0000 0.1301
-5.750 -0.5583 0.02468 0.01541 -0.0178 1.0000 0.1379
-5.500 -0.5343 0.02325 0.01402 -0.0173 1.0000 0.1463
-5.250 -0.5100 0.02211 0.01274 -0.0166 1.0000 0.1566
-5.000 -0.4857 0.02125 0.01174 -0.0159 1.0000 0.1667
-4.750 -0.4619 0.02029 0.01084 -0.0152 1.0000 0.1768
-4.500 -0.4381 0.01949 0.01002 -0.0145 1.0000 0.1880
-4.250 -0.4142 0.01883 0.00925 -0.0136 1.0000 0.1990
-4.000 -0.3908 0.01805 0.00858 -0.0128 1.0000 0.2099
-3.750 -0.3673 0.01732 0.00793 -0.0120 1.0000 0.2213
-3.500 -0.3438 0.01663 0.00732 -0.0112 1.0000 0.2338
-3.250 -0.3207 0.01598 0.00679 -0.0103 1.0000 0.2509
-3.000 -0.2980 0.01530 0.00632 -0.0094 1.0000 0.2773
-2.750 -0.2759 0.01442 0.00588 -0.0085 1.0000 0.3291
-2.500 -0.2580 0.01280 0.00562 -0.0067 1.0000 0.5491
-2.250 -0.2458 0.01229 0.00597 -0.0016 1.0000 0.7675
-2.000 -0.2295 0.01240 0.00625 0.0027 1.0000 0.8654
-1.750 -0.1963 0.01263 0.00643 0.0033 1.0000 0.9343
-1.500 -0.1217 0.01284 0.00643 -0.0048 1.0000 0.9804
-1.250 -0.0443 0.01282 0.00622 -0.0146 1.0000 1.0000
-1.000 -0.0462 0.01275 0.00610 -0.0104 1.0000 1.0000
-0.750 -0.0461 0.01274 0.00604 -0.0064 1.0000 1.0000
-0.500 -0.0409 0.01280 0.00604 -0.0033 1.0000 1.0000
-0.250 -0.0289 0.01293 0.00611 -0.0014 1.0000 1.0000
0.000 -0.0130 0.01314 0.00626 -0.0002 1.0000 1.0000
0.250 0.0136 0.01340 0.00648 -0.0011 0.9972 1.0000
0.500 0.0758 0.01367 0.00673 -0.0083 0.9838 1.0000
0.750 0.1416 0.01379 0.00688 -0.0159 0.9679 1.0000
1.000 0.2173 0.01359 0.00675 -0.0245 0.9468 1.0000
1.250 0.2708 0.01331 0.00654 -0.0285 0.9206 1.0000
1.500 0.3081 0.01304 0.00630 -0.0291 0.8916 1.0000
1.750 0.3350 0.01280 0.00606 -0.0275 0.8586 1.0000
2.000 0.3569 0.01262 0.00584 -0.0249 0.8210 1.0000
2.250 0.3774 0.01250 0.00564 -0.0221 0.7766 1.0000
2.500 0.3978 0.01249 0.00547 -0.0194 0.7224 1.0000
2.750 0.4185 0.01262 0.00535 -0.0169 0.6580 1.0000
3.000 0.4395 0.01296 0.00533 -0.0147 0.5842 1.0000
3.250 0.4610 0.01349 0.00544 -0.0131 0.5120 1.0000
3.500 0.4830 0.01414 0.00568 -0.0117 0.4469 1.0000
3.750 0.5055 0.01487 0.00606 -0.0107 0.3891 1.0000
4.000 0.5285 0.01566 0.00650 -0.0099 0.3407 1.0000
4.250 0.5522 0.01644 0.00701 -0.0092 0.3028 1.0000
4.500 0.5765 0.01724 0.00759 -0.0086 0.2752 1.0000
4.750 0.6017 0.01797 0.00824 -0.0081 0.2529 1.0000
5.000 0.6269 0.01871 0.00886 -0.0076 0.2354 1.0000
5.250 0.6523 0.01947 0.00956 -0.0072 0.2207 1.0000
5.500 0.6782 0.02033 0.01043 -0.0068 0.2093 1.0000
5.750 0.7042 0.02132 0.01131 -0.0065 0.2004 1.0000
6.000 0.7302 0.02219 0.01227 -0.0062 0.1915 1.0000
6.250 0.7561 0.02326 0.01337 -0.0059 0.1840 1.0000
6.500 0.7818 0.02422 0.01444 -0.0056 0.1769 1.0000
6.750 0.8078 0.02561 0.01580 -0.0054 0.1720 1.0000
7.000 0.8328 0.02689 0.01742 -0.0049 0.1672 1.0000
7.250 0.8579 0.02816 0.01886 -0.0046 0.1625 1.0000
7.500 0.8828 0.02986 0.02050 -0.0044 0.1581 1.0000
7.750 0.9046 0.03141 0.02259 -0.0037 0.1540 1.0000
8.000 0.9266 0.03331 0.02485 -0.0031 0.1507 1.0000
8.250 0.9488 0.03517 0.02692 -0.0026 0.1477 1.0000
8.500 0.9719 0.03713 0.02890 -0.0024 0.1443 1.0000
8.750 0.9863 0.03993 0.03229 -0.0014 0.1412 1.0000
9.000 0.9978 0.04328 0.03620 -0.0004 0.1389 1.0000
9.250 1.0072 0.04679 0.04017 0.0005 0.1362 1.0000
9.500 1.0280 0.04822 0.04164 0.0011 0.1319 1.0000
9.750 1.0413 0.05136 0.04490 0.0016 0.1283 1.0000
10.000 1.0285 0.05686 0.05108 0.0028 0.1261 1.0000
10.250 1.0056 0.06344 0.05812 0.0032 0.1251 1.0000
10.500 0.9744 0.07085 0.06581 0.0025 0.1261 1.0000
10.750 0.9441 0.07789 0.07295 0.0010 0.1275 1.0000
11.000 0.9204 0.08568 0.08079 -0.0025 0.1285 1.0000
11.250 0.9042 0.09389 0.08905 -0.0066 0.1295 1.0000
11.500 1.1174 0.05693 0.05138 0.0094 0.0743 1.0000
11.750 1.0861 0.06214 0.05694 0.0111 0.0738 1.0000
12.000 1.0553 0.06796 0.06298 0.0104 0.0742 1.0000
12.250 1.0255 0.07496 0.07014 0.0072 0.0749 1.0000
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