CLARK YS AIRFOIL (clarkys-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YS AIRFOIL (clarkys-il) Reynolds number: 100,000 Max Cl/Cd: 45.67 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkys-il-100000.txt Download as CSV file: xf-clarkys-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK YS 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 -0.4663 0.10056 0.09604 -0.0054 1.0000 0.1305
-9.250 -0.4796 0.09697 0.09253 -0.0101 1.0000 0.1364
-9.000 -0.5334 0.09316 0.08884 -0.0191 1.0000 0.1380
-8.750 -0.4692 0.08904 0.08469 -0.0123 1.0000 0.1437
-8.500 -0.4739 0.08541 0.08112 -0.0154 1.0000 0.1499
-8.250 -0.5275 0.08232 0.07805 -0.0207 1.0000 0.1532
-8.000 -0.4935 0.07757 0.07339 -0.0193 1.0000 0.1576
-7.750 -0.4869 0.07476 0.07061 -0.0192 1.0000 0.1630
-7.500 -0.5500 0.07461 0.07029 -0.0179 1.0000 0.1692
-7.250 -0.5518 0.07103 0.06684 -0.0148 1.0000 0.1710
-7.000 -0.5346 0.06824 0.06413 -0.0132 0.9975 0.1745
-6.750 -0.5251 0.06414 0.05981 -0.0174 0.9843 0.1875
-6.500 -0.4959 0.06083 0.05648 -0.0192 0.9772 0.1965
-6.250 -0.4867 0.05814 0.05344 -0.0221 0.9667 0.2182
-6.000 -0.4857 0.04136 0.03497 -0.0233 0.9566 0.1106
-5.750 -0.4654 0.03760 0.03076 -0.0225 0.9478 0.1019
-5.500 -0.4432 0.03355 0.02560 -0.0212 0.9409 0.0943
-5.250 -0.4199 0.03179 0.02344 -0.0203 0.9322 0.0938
-5.000 -0.3853 0.02932 0.02078 -0.0220 0.9267 0.0960
-4.750 -0.3599 0.02798 0.01927 -0.0216 0.9182 0.0979
-4.500 -0.3249 0.02643 0.01746 -0.0227 0.9121 0.0994
-4.250 -0.2955 0.02527 0.01610 -0.0228 0.9043 0.1016
-4.000 -0.2614 0.02417 0.01480 -0.0235 0.8975 0.1050
-3.750 -0.2291 0.02312 0.01371 -0.0243 0.8905 0.1110
-3.500 -0.1987 0.02236 0.01296 -0.0246 0.8828 0.1187
-3.250 -0.1673 0.02144 0.01213 -0.0249 0.8760 0.1289
-3.000 -0.1415 0.02073 0.01155 -0.0244 0.8672 0.1485
-2.750 -0.0013 0.01758 0.01174 -0.0418 0.8639 0.8550
-2.500 0.1514 0.01792 0.01143 -0.0624 0.8525 1.0000
-2.250 0.1712 0.01811 0.01143 -0.0608 0.8414 1.0000
-2.000 0.1906 0.01833 0.01147 -0.0590 0.8314 1.0000
-1.750 0.2128 0.01852 0.01153 -0.0581 0.8204 1.0000
-1.500 0.2341 0.01875 0.01162 -0.0569 0.8099 1.0000
-1.250 0.2542 0.01898 0.01172 -0.0552 0.8002 1.0000
-1.000 0.2759 0.01918 0.01181 -0.0540 0.7891 1.0000
-0.750 0.2980 0.01938 0.01193 -0.0530 0.7780 1.0000
-0.500 0.3193 0.01956 0.01202 -0.0516 0.7676 1.0000
-0.250 0.3401 0.01969 0.01205 -0.0499 0.7577 1.0000
0.000 0.3627 0.01982 0.01214 -0.0489 0.7458 1.0000
0.250 0.3846 0.01991 0.01218 -0.0476 0.7344 1.0000
0.500 0.4051 0.01987 0.01204 -0.0455 0.7256 1.0000
0.750 0.4278 0.01988 0.01203 -0.0445 0.7126 1.0000
1.000 0.4503 0.01988 0.01200 -0.0432 0.7004 1.0000
1.250 0.4722 0.01978 0.01184 -0.0416 0.6894 1.0000
1.500 0.4939 0.01954 0.01154 -0.0397 0.6793 1.0000
1.750 0.5166 0.01943 0.01140 -0.0384 0.6657 1.0000
2.000 0.5392 0.01929 0.01123 -0.0369 0.6524 1.0000
2.250 0.5619 0.01914 0.01105 -0.0355 0.6394 1.0000
2.500 0.5847 0.01898 0.01083 -0.0340 0.6266 1.0000
2.750 0.6076 0.01879 0.01057 -0.0324 0.6140 1.0000
3.000 0.6309 0.01868 0.01038 -0.0310 0.6005 1.0000
3.250 0.6543 0.01871 0.01038 -0.0299 0.5855 1.0000
3.500 0.6779 0.01880 0.01043 -0.0289 0.5709 1.0000
3.750 0.7016 0.01893 0.01054 -0.0279 0.5567 1.0000
4.000 0.7252 0.01911 0.01071 -0.0270 0.5432 1.0000
4.250 0.7488 0.01928 0.01085 -0.0261 0.5302 1.0000
4.500 0.7724 0.01942 0.01094 -0.0251 0.5179 1.0000
4.750 0.7962 0.01956 0.01101 -0.0241 0.5061 1.0000
5.000 0.8194 0.01987 0.01139 -0.0233 0.4933 1.0000
5.250 0.8426 0.02017 0.01173 -0.0225 0.4813 1.0000
5.500 0.8656 0.02037 0.01191 -0.0215 0.4690 1.0000
5.750 0.8885 0.02053 0.01203 -0.0205 0.4560 1.0000
6.000 0.9113 0.02069 0.01215 -0.0194 0.4430 1.0000
6.250 0.9333 0.02100 0.01254 -0.0184 0.4297 1.0000
6.500 0.9551 0.02135 0.01296 -0.0175 0.4171 1.0000
6.750 0.9769 0.02169 0.01336 -0.0164 0.4047 1.0000
7.000 0.9986 0.02203 0.01370 -0.0153 0.3921 1.0000
7.250 1.0203 0.02238 0.01401 -0.0142 0.3793 1.0000
7.500 1.0409 0.02279 0.01446 -0.0130 0.3653 1.0000
7.750 1.0605 0.02324 0.01496 -0.0117 0.3500 1.0000
8.000 1.0795 0.02373 0.01547 -0.0104 0.3339 1.0000
8.250 1.0976 0.02427 0.01602 -0.0089 0.3170 1.0000
8.500 1.1133 0.02491 0.01679 -0.0071 0.2986 1.0000
8.750 1.1278 0.02557 0.01753 -0.0052 0.2794 1.0000
9.000 1.1414 0.02619 0.01818 -0.0032 0.2608 1.0000
9.250 1.1539 0.02680 0.01879 -0.0010 0.2438 1.0000
9.500 1.1647 0.02744 0.01943 0.0013 0.2282 1.0000
9.750 1.1739 0.02817 0.02020 0.0038 0.2142 1.0000
10.000 1.1817 0.02898 0.02104 0.0064 0.2019 1.0000
10.250 1.1887 0.02986 0.02191 0.0091 0.1912 1.0000
10.500 1.1956 0.03072 0.02266 0.0118 0.1818 1.0000
10.750 1.1974 0.03169 0.02380 0.0152 0.1730 1.0000
11.000 1.1999 0.03268 0.02476 0.0184 0.1652 1.0000
11.250 1.1962 0.03361 0.02578 0.0224 0.1578 1.0000
11.500 1.1900 0.03454 0.02670 0.0267 0.1515 1.0000
11.750 1.1784 0.03557 0.02785 0.0313 0.1457 1.0000
12.000 1.1759 0.03671 0.02888 0.0344 0.1390 1.0000
12.250 1.1663 0.03819 0.03058 0.0376 0.1332 1.0000
12.500 1.1640 0.03959 0.03185 0.0400 0.1256 1.0000
12.750 1.1511 0.04161 0.03413 0.0425 0.1187 1.0000
13.000 1.1436 0.04363 0.03609 0.0444 0.1105 1.0000
13.250 1.1302 0.04620 0.03873 0.0459 0.1018 1.0000
13.500 1.1173 0.04921 0.04181 0.0471 0.0925 1.0000
13.750 1.1061 0.05229 0.04483 0.0480 0.0837 1.0000
14.000 1.0977 0.05529 0.04781 0.0485 0.0768 1.0000
14.250 1.0917 0.05842 0.05103 0.0491 0.0711 1.0000
14.500 1.0876 0.06132 0.05398 0.0495 0.0666 1.0000
14.750 1.0908 0.06371 0.05632 0.0504 0.0628 1.0000
15.000 1.0835 0.06735 0.06020 0.0503 0.0605 1.0000
15.250 1.0779 0.07083 0.06383 0.0500 0.0583 1.0000
15.500 1.0767 0.07379 0.06683 0.0498 0.0562 1.0000
15.750 1.0831 0.07598 0.06892 0.0505 0.0538 1.0000
16.000 1.0685 0.08100 0.07421 0.0490 0.0530 1.0000
16.250 1.0521 0.08652 0.07997 0.0470 0.0524 1.0000
16.500 1.0335 0.09270 0.08638 0.0445 0.0521 1.0000
16.750 1.0107 0.09989 0.09379 0.0412 0.0521 1.0000
17.000 0.9832 0.10836 0.10248 0.0369 0.0525 1.0000
17.250 0.9501 0.11850 0.11280 0.0314 0.0531 1.0000
17.500 0.9170 0.12937 0.12379 0.0257 0.0539 1.0000
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