SIKORSKY SC1095 AIRFOIL (sc1095-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: SIKORSKY SC1095 AIRFOIL (sc1095-il) Reynolds number: 200,000 Max Cl/Cd: 45.31 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc1095-il-200000.txt Download as CSV file: xf-sc1095-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7638 0.09985 0.09647 0.0088 1.0000 0.0250
-11.500 -0.7567 0.09777 0.09441 0.0076 1.0000 0.0257
-11.250 -0.9334 0.05148 0.04743 -0.0288 1.0000 0.0209
-11.000 -0.9561 0.04655 0.04215 -0.0286 1.0000 0.0208
-10.750 -0.9634 0.04246 0.03770 -0.0279 1.0000 0.0210
-10.500 -0.9621 0.03901 0.03390 -0.0269 1.0000 0.0213
-10.250 -0.9552 0.03595 0.03049 -0.0260 1.0000 0.0219
-10.000 -0.9444 0.03313 0.02730 -0.0249 1.0000 0.0228
-9.750 -0.9304 0.03056 0.02431 -0.0239 1.0000 0.0240
-9.500 -0.9155 0.02800 0.02151 -0.0229 1.0000 0.0256
-9.250 -0.8955 0.02665 0.02008 -0.0223 1.0000 0.0283
-9.000 -0.8768 0.02472 0.01797 -0.0214 1.0000 0.0334
-8.750 -0.8551 0.02362 0.01672 -0.0208 1.0000 0.0406
-8.500 -0.8301 0.02360 0.01657 -0.0206 1.0000 0.0466
-8.250 -0.8062 0.02326 0.01625 -0.0203 1.0000 0.0514
-8.000 -0.7807 0.02341 0.01623 -0.0201 1.0000 0.0568
-7.750 -0.7568 0.02266 0.01547 -0.0198 1.0000 0.0609
-7.500 -0.7313 0.02269 0.01545 -0.0195 1.0000 0.0659
-7.250 -0.7069 0.02186 0.01440 -0.0191 1.0000 0.0706
-7.000 -0.6818 0.02134 0.01392 -0.0188 1.0000 0.0747
-6.750 -0.6564 0.02061 0.01303 -0.0183 1.0000 0.0791
-6.500 -0.6316 0.01947 0.01172 -0.0178 1.0000 0.0836
-6.250 -0.6065 0.01877 0.01105 -0.0174 1.0000 0.0886
-6.000 -0.5809 0.01821 0.01029 -0.0168 1.0000 0.0947
-5.750 -0.5567 0.01724 0.00939 -0.0163 1.0000 0.1019
-5.500 -0.5317 0.01688 0.00886 -0.0157 1.0000 0.1098
-5.250 -0.5081 0.01607 0.00816 -0.0151 1.0000 0.1174
-5.000 -0.4838 0.01576 0.00768 -0.0143 1.0000 0.1240
-4.750 -0.4610 0.01502 0.00706 -0.0135 1.0000 0.1310
-4.500 -0.4373 0.01474 0.00670 -0.0127 1.0000 0.1380
-4.250 -0.4147 0.01415 0.00621 -0.0118 1.0000 0.1450
-4.000 -0.3914 0.01391 0.00591 -0.0109 1.0000 0.1530
-3.750 -0.3688 0.01342 0.00553 -0.0101 1.0000 0.1614
-3.500 -0.3458 0.01309 0.00521 -0.0093 1.0000 0.1704
-3.250 -0.3227 0.01273 0.00492 -0.0085 1.0000 0.1802
-3.000 -0.2994 0.01235 0.00463 -0.0079 1.0000 0.1921
-2.750 -0.2757 0.01199 0.00439 -0.0073 1.0000 0.2110
-2.500 -0.2516 0.01149 0.00418 -0.0070 1.0000 0.2523
-2.250 -0.2268 0.01059 0.00401 -0.0072 1.0000 0.3953
-2.000 -0.2027 0.00967 0.00406 -0.0068 1.0000 0.6050
-1.750 -0.1810 0.00936 0.00427 -0.0052 1.0000 0.7351
-1.500 -0.1474 0.00929 0.00445 -0.0057 0.9945 0.8203
-1.250 -0.1111 0.00933 0.00459 -0.0065 0.9861 0.8766
-1.000 -0.0725 0.00943 0.00471 -0.0078 0.9786 0.9183
-0.750 -0.0263 0.00950 0.00475 -0.0108 0.9726 0.9479
-0.500 0.0239 0.00952 0.00474 -0.0148 0.9662 0.9682
-0.250 0.0826 0.00948 0.00466 -0.0205 0.9594 0.9806
0.000 0.1482 0.00934 0.00450 -0.0273 0.9452 0.9938
0.250 0.1888 0.00916 0.00429 -0.0294 0.9225 1.0000
0.500 0.2105 0.00900 0.00408 -0.0277 0.8988 1.0000
0.750 0.2304 0.00887 0.00389 -0.0256 0.8723 1.0000
1.000 0.2506 0.00877 0.00372 -0.0236 0.8441 1.0000
1.250 0.2715 0.00871 0.00356 -0.0217 0.8128 1.0000
1.500 0.2931 0.00870 0.00342 -0.0199 0.7772 1.0000
1.750 0.3153 0.00875 0.00331 -0.0183 0.7335 1.0000
2.000 0.3377 0.00888 0.00323 -0.0169 0.6801 1.0000
2.250 0.3601 0.00912 0.00318 -0.0155 0.6174 1.0000
2.500 0.3825 0.00948 0.00319 -0.0143 0.5502 1.0000
2.750 0.4055 0.00989 0.00328 -0.0133 0.4860 1.0000
3.000 0.4290 0.01033 0.00343 -0.0125 0.4294 1.0000
3.250 0.4531 0.01077 0.00361 -0.0119 0.3806 1.0000
3.500 0.4776 0.01122 0.00383 -0.0114 0.3371 1.0000
3.750 0.5025 0.01167 0.00409 -0.0110 0.2952 1.0000
4.000 0.5275 0.01216 0.00438 -0.0107 0.2575 1.0000
4.250 0.5528 0.01266 0.00470 -0.0103 0.2276 1.0000
4.500 0.5782 0.01315 0.00506 -0.0100 0.2057 1.0000
4.750 0.6037 0.01368 0.00547 -0.0097 0.1898 1.0000
5.000 0.6294 0.01420 0.00593 -0.0094 0.1771 1.0000
5.250 0.6550 0.01477 0.00646 -0.0090 0.1667 1.0000
5.500 0.6801 0.01545 0.00702 -0.0087 0.1578 1.0000
5.750 0.7065 0.01589 0.00752 -0.0084 0.1501 1.0000
6.000 0.7316 0.01670 0.00821 -0.0081 0.1440 1.0000
6.250 0.7580 0.01723 0.00886 -0.0078 0.1389 1.0000
6.500 0.7840 0.01783 0.00949 -0.0075 0.1341 1.0000
6.750 0.8094 0.01883 0.01040 -0.0073 0.1295 1.0000
7.000 0.8355 0.01938 0.01111 -0.0069 0.1257 1.0000
7.250 0.8614 0.02003 0.01188 -0.0067 0.1218 1.0000
7.500 0.8872 0.02079 0.01265 -0.0064 0.1186 1.0000
7.750 0.9125 0.02217 0.01401 -0.0062 0.1154 1.0000
8.000 0.9378 0.02297 0.01503 -0.0058 0.1130 1.0000
8.250 0.9627 0.02376 0.01603 -0.0054 0.1098 1.0000
8.500 0.9875 0.02465 0.01706 -0.0051 0.1069 1.0000
8.750 1.0121 0.02552 0.01797 -0.0048 0.1041 1.0000
9.000 1.0349 0.02675 0.01931 -0.0044 0.1000 1.0000
9.250 1.0580 0.02645 0.01919 -0.0039 0.0938 1.0000
9.500 1.0807 0.02681 0.01940 -0.0037 0.0879 1.0000
9.750 1.1028 0.02680 0.01969 -0.0030 0.0833 1.0000
10.000 1.1257 0.02679 0.01971 -0.0026 0.0787 1.0000
10.250 1.1468 0.02743 0.02041 -0.0020 0.0744 1.0000
10.500 1.1684 0.02740 0.02066 -0.0014 0.0689 1.0000
10.750 1.1894 0.02732 0.02063 -0.0008 0.0624 1.0000
11.000 1.2133 0.02678 0.02026 -0.0005 0.0469 1.0000
11.250 1.2289 0.02804 0.02144 0.0006 0.0341 1.0000
11.500 1.2409 0.02969 0.02314 0.0019 0.0290 1.0000
11.750 1.2503 0.03151 0.02513 0.0036 0.0264 1.0000
12.000 1.2576 0.03330 0.02708 0.0052 0.0247 1.0000
12.250 1.2583 0.03527 0.02919 0.0075 0.0236 1.0000
12.500 1.2526 0.03778 0.03179 0.0097 0.0228 1.0000
12.750 1.2479 0.04052 0.03470 0.0110 0.0223 1.0000
13.000 1.2440 0.04348 0.03787 0.0115 0.0219 1.0000
13.250 1.2379 0.04699 0.04158 0.0111 0.0215 1.0000
13.500 1.2298 0.05114 0.04594 0.0099 0.0212 1.0000
13.750 1.2197 0.05602 0.05102 0.0076 0.0210 1.0000
14.000 1.2076 0.06170 0.05689 0.0043 0.0209 1.0000
14.250 1.1931 0.06817 0.06357 0.0003 0.0208 1.0000
14.500 1.1761 0.07539 0.07097 -0.0042 0.0208 1.0000
14.750 1.1566 0.08324 0.07900 -0.0090 0.0209 1.0000
15.000 1.1346 0.09166 0.08759 -0.0140 0.0211 1.0000
15.250 1.1106 0.10057 0.09665 -0.0191 0.0213 1.0000
15.500 1.0837 0.11036 0.10659 -0.0247 0.0216 1.0000
15.750 1.0547 0.12105 0.11741 -0.0308 0.0219 1.0000
16.000 1.0228 0.13299 0.12945 -0.0375 0.0223 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SIKORSKY SC1095 AIRFOIL (sc1095-il)