SIKORSKY GS-1 AIRFOIL (gs1-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY GS-1 AIRFOIL (gs1-il) Reynolds number: 100,000 Max Cl/Cd: 51.04 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-gs1-il-100000.txt Download as CSV file: xf-gs1-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY GS-1 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3726 0.09878 0.09412 -0.0244 1.0000 0.1697
-7.500 -0.4337 0.09968 0.09521 -0.0215 1.0000 0.1712
-7.250 -0.4974 0.06345 0.05846 -0.0592 0.9832 0.1133
-7.000 -0.4809 0.05632 0.05104 -0.0655 0.9741 0.1120
-6.750 -0.4646 0.04776 0.04189 -0.0731 0.9656 0.1115
-6.500 -0.4439 0.04137 0.03474 -0.0778 0.9565 0.1121
-6.250 -0.4163 0.03768 0.03059 -0.0806 0.9486 0.1144
-6.000 -0.3796 0.03693 0.02994 -0.0828 0.9407 0.1188
-5.750 -0.3485 0.03441 0.02689 -0.0851 0.9326 0.1237
-5.500 -0.3157 0.03221 0.02430 -0.0871 0.9246 0.1286
-5.250 -0.2766 0.03131 0.02334 -0.0895 0.9180 0.1357
-5.000 -0.2473 0.02983 0.02152 -0.0904 0.9084 0.1428
-4.750 -0.2017 0.02891 0.02048 -0.0937 0.9038 0.1533
-4.500 -0.1783 0.02811 0.01966 -0.0932 0.8925 0.1613
-4.250 -0.1336 0.02711 0.01850 -0.0963 0.8876 0.1748
-4.000 -0.1078 0.02671 0.01803 -0.0960 0.8771 0.1864
-3.750 -0.0646 0.02593 0.01726 -0.0986 0.8716 0.2017
-3.500 -0.0149 0.02513 0.01641 -0.1023 0.8684 0.2201
-3.250 0.0051 0.02490 0.01627 -0.1009 0.8562 0.2322
-3.000 0.0507 0.02421 0.01557 -0.1036 0.8520 0.2516
-2.750 0.0739 0.02402 0.01540 -0.1027 0.8411 0.2659
-2.500 0.1148 0.02344 0.01483 -0.1045 0.8357 0.2861
-2.250 0.1432 0.02318 0.01458 -0.1043 0.8268 0.3040
-2.000 0.1774 0.02274 0.01416 -0.1050 0.8194 0.3251
-1.750 0.2197 0.02207 0.01349 -0.1068 0.8151 0.3513
-1.500 0.2385 0.02206 0.01355 -0.1051 0.8029 0.3711
-1.250 0.2776 0.02144 0.01300 -0.1064 0.7980 0.4006
-1.000 0.2977 0.02144 0.01306 -0.1049 0.7864 0.4254
-0.750 0.3342 0.02086 0.01257 -0.1056 0.7807 0.4570
-0.500 0.3552 0.02084 0.01266 -0.1042 0.7698 0.4838
-0.250 0.3895 0.02034 0.01223 -0.1046 0.7633 0.5187
0.000 0.4118 0.02030 0.01232 -0.1034 0.7530 0.5513
0.250 0.4432 0.01981 0.01199 -0.1032 0.7460 0.5940
0.500 0.4656 0.01966 0.01207 -0.1019 0.7362 0.6461
0.750 0.4925 0.01894 0.01188 -0.1003 0.7288 0.7596
1.000 0.5598 0.01854 0.01160 -0.1073 0.7198 1.0000
1.250 0.5891 0.01859 0.01145 -0.1073 0.7112 1.0000
1.500 0.6129 0.01887 0.01159 -0.1065 0.7018 1.0000
1.750 0.6419 0.01894 0.01151 -0.1063 0.6934 1.0000
2.000 0.6651 0.01925 0.01174 -0.1053 0.6839 1.0000
2.250 0.6940 0.01934 0.01171 -0.1051 0.6756 1.0000
2.500 0.7169 0.01969 0.01200 -0.1041 0.6663 1.0000
2.750 0.7456 0.01981 0.01201 -0.1039 0.6579 1.0000
3.000 0.7684 0.02020 0.01237 -0.1029 0.6487 1.0000
3.250 0.7965 0.02036 0.01245 -0.1026 0.6403 1.0000
3.500 0.8194 0.02077 0.01283 -0.1016 0.6312 1.0000
3.750 0.8468 0.02098 0.01298 -0.1012 0.6227 1.0000
4.000 0.8701 0.02139 0.01337 -0.1003 0.6139 1.0000
4.250 0.8964 0.02165 0.01360 -0.0998 0.6052 1.0000
4.500 0.9205 0.02206 0.01400 -0.0990 0.5968 1.0000
4.750 0.9452 0.02239 0.01432 -0.0983 0.5879 1.0000
5.000 0.9707 0.02277 0.01468 -0.0977 0.5800 1.0000
5.250 0.9931 0.02319 0.01514 -0.0967 0.5708 1.0000
5.500 1.0212 0.02349 0.01540 -0.0964 0.5635 1.0000
5.750 1.0401 0.02407 0.01606 -0.0950 0.5540 1.0000
6.000 1.0722 0.02422 0.01613 -0.0952 0.5473 1.0000
6.250 1.0867 0.02497 0.01702 -0.0932 0.5373 1.0000
6.500 1.1210 0.02505 0.01702 -0.0938 0.5310 1.0000
6.750 1.1323 0.02596 0.01810 -0.0914 0.5210 1.0000
7.000 1.1661 0.02599 0.01806 -0.0918 0.5142 1.0000
7.250 1.1786 0.02677 0.01899 -0.0895 0.5038 1.0000
7.500 1.2122 0.02648 0.01861 -0.0897 0.4943 1.0000
7.750 1.2319 0.02654 0.01872 -0.0880 0.4819 1.0000
8.000 1.2511 0.02667 0.01889 -0.0862 0.4697 1.0000
8.250 1.2783 0.02647 0.01863 -0.0855 0.4582 1.0000
8.500 1.3027 0.02628 0.01840 -0.0843 0.4456 1.0000
8.750 1.3159 0.02660 0.01883 -0.0818 0.4332 1.0000
9.000 1.3362 0.02675 0.01901 -0.0803 0.4220 1.0000
9.250 1.3618 0.02668 0.01886 -0.0795 0.4105 1.0000
9.500 1.3702 0.02712 0.01947 -0.0763 0.3982 1.0000
9.750 1.3833 0.02740 0.01982 -0.0738 0.3859 1.0000
10.000 1.3970 0.02757 0.02002 -0.0713 0.3730 1.0000
10.250 1.4072 0.02776 0.02021 -0.0683 0.3590 1.0000
10.500 1.4073 0.02818 0.02072 -0.0639 0.3449 1.0000
10.750 1.4039 0.02876 0.02138 -0.0592 0.3294 1.0000
11.000 1.3991 0.02952 0.02215 -0.0547 0.3117 1.0000
11.250 1.3892 0.03073 0.02341 -0.0503 0.2905 1.0000
11.500 1.3758 0.03241 0.02504 -0.0460 0.2647 1.0000
11.750 1.3578 0.03485 0.02734 -0.0422 0.2345 1.0000
12.000 1.3387 0.03792 0.03021 -0.0391 0.2051 1.0000
12.250 1.3219 0.04129 0.03335 -0.0368 0.1818 1.0000
12.500 1.3101 0.04456 0.03647 -0.0350 0.1648 1.0000
12.750 1.3027 0.04762 0.03939 -0.0337 0.1520 1.0000
13.000 1.2999 0.05035 0.04196 -0.0325 0.1423 1.0000
13.250 1.3020 0.05272 0.04430 -0.0315 0.1338 1.0000
13.500 1.3086 0.05475 0.04625 -0.0304 0.1263 1.0000
13.750 1.3182 0.05651 0.04792 -0.0294 0.1198 1.0000
14.000 1.3323 0.05806 0.04947 -0.0284 0.1142 1.0000
14.250 1.3456 0.05967 0.05105 -0.0275 0.1088 1.0000
14.500 1.3686 0.06078 0.05207 -0.0265 0.1037 1.0000
14.750 1.3769 0.06300 0.05446 -0.0259 0.1001 1.0000
15.000 1.4009 0.06413 0.05548 -0.0252 0.0956 1.0000
15.250 1.4194 0.06613 0.05755 -0.0245 0.0922 1.0000
15.500 1.4219 0.06896 0.06062 -0.0240 0.0899 1.0000
15.750 1.4265 0.07169 0.06352 -0.0237 0.0875 1.0000
16.000 1.4708 0.07271 0.06429 -0.0232 0.0830 1.0000
16.250 1.4568 0.07659 0.06851 -0.0229 0.0822 1.0000
16.500 1.4424 0.08084 0.07307 -0.0230 0.0814 1.0000
16.750 1.4269 0.08547 0.07800 -0.0236 0.0805 1.0000
17.000 1.4095 0.09055 0.08337 -0.0245 0.0797 1.0000
17.250 1.3901 0.09614 0.08923 -0.0261 0.0791 1.0000
17.500 1.3666 0.10253 0.09591 -0.0284 0.0787 1.0000
17.750 1.3365 0.11024 0.10391 -0.0318 0.0786 1.0000
18.000 1.2950 0.12039 0.11439 -0.0372 0.0793 1.0000
18.250 1.2403 0.13407 0.12839 -0.0454 0.0807 1.0000
18.500 1.1804 0.15101 0.14554 -0.0561 0.0825 1.0000
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