CLARK YS AIRFOIL (clarkys-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK YS AIRFOIL (clarkys-il) Reynolds number: 200,000 Max Cl/Cd: 58.07 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkys-il-200000-n5.txt Download as CSV file: xf-clarkys-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5770 0.07872 0.07507 -0.0204 0.8468 0.0301
-10.000 -0.6518 0.06156 0.05775 -0.0304 0.8394 0.0296
-9.750 -0.7101 0.05248 0.04830 -0.0269 0.8325 0.0295
-9.500 -0.7334 0.04750 0.04293 -0.0231 0.8270 0.0298
-9.250 -0.7419 0.04386 0.03894 -0.0199 0.8224 0.0303
-9.000 -0.7431 0.04073 0.03546 -0.0170 0.8176 0.0311
-8.750 -0.7421 0.03759 0.03186 -0.0139 0.8131 0.0320
-8.500 -0.7367 0.03481 0.02860 -0.0111 0.8092 0.0327
-8.250 -0.7259 0.03246 0.02582 -0.0087 0.8048 0.0333
-8.000 -0.7116 0.03064 0.02359 -0.0067 0.8005 0.0338
-7.750 -0.6955 0.02885 0.02146 -0.0050 0.7966 0.0345
-7.500 -0.6757 0.02745 0.01992 -0.0039 0.7928 0.0353
-7.250 -0.6542 0.02634 0.01869 -0.0030 0.7884 0.0359
-7.000 -0.6321 0.02526 0.01742 -0.0020 0.7844 0.0365
-6.750 -0.6094 0.02425 0.01622 -0.0011 0.7809 0.0371
-6.500 -0.5851 0.02325 0.01507 -0.0005 0.7765 0.0377
-6.250 -0.5605 0.02235 0.01401 0.0001 0.7722 0.0384
-6.000 -0.5356 0.02159 0.01310 0.0007 0.7684 0.0394
-5.750 -0.5101 0.02086 0.01224 0.0013 0.7646 0.0404
-5.500 -0.4839 0.02011 0.01138 0.0016 0.7599 0.0411
-5.250 -0.4577 0.01942 0.01058 0.0020 0.7558 0.0416
-5.000 -0.4319 0.01882 0.00987 0.0026 0.7522 0.0421
-4.750 -0.4061 0.01803 0.00909 0.0030 0.7475 0.0431
-4.500 -0.3807 0.01745 0.00850 0.0034 0.7429 0.0440
-4.250 -0.3554 0.01699 0.00800 0.0040 0.7388 0.0452
-4.000 -0.3298 0.01657 0.00756 0.0046 0.7346 0.0466
-3.750 -0.3039 0.01620 0.00717 0.0050 0.7289 0.0485
-3.500 -0.2784 0.01584 0.00674 0.0056 0.7238 0.0507
-3.250 -0.2529 0.01544 0.00634 0.0062 0.7177 0.0531
-3.000 -0.2272 0.01507 0.00597 0.0068 0.7105 0.0565
-2.750 -0.2014 0.01476 0.00561 0.0074 0.7045 0.0616
-2.500 -0.1755 0.01440 0.00530 0.0079 0.6963 0.0722
-2.250 -0.1500 0.01405 0.00497 0.0086 0.6895 0.0884
-2.000 -0.1244 0.01370 0.00473 0.0091 0.6811 0.1120
-1.750 -0.0995 0.01331 0.00448 0.0097 0.6755 0.1509
-1.500 -0.0749 0.01293 0.00436 0.0103 0.6680 0.2098
-1.250 -0.0515 0.01253 0.00419 0.0112 0.6617 0.2761
-1.000 0.0623 0.01156 0.00544 -0.0050 0.6523 0.7692
-0.750 0.0118 0.01051 0.00417 0.0099 0.6467 0.7297
-0.250 0.1109 0.01205 0.00566 0.0036 0.6301 0.9167
0.250 0.2299 0.01306 0.00644 -0.0078 0.6085 0.9523
0.500 0.2611 0.01319 0.00648 -0.0082 0.5982 0.9599
0.750 0.3102 0.01314 0.00634 -0.0124 0.5863 0.9658
1.000 0.3425 0.01319 0.00632 -0.0132 0.5751 0.9709
1.250 0.3828 0.01312 0.00616 -0.0158 0.5618 0.9757
1.500 0.4210 0.01309 0.00604 -0.0179 0.5474 0.9812
1.750 0.4510 0.01313 0.00600 -0.0183 0.5332 0.9842
2.000 0.4786 0.01312 0.00593 -0.0183 0.5186 0.9848
2.250 0.5018 0.01318 0.00593 -0.0174 0.5041 0.9846
2.500 0.5249 0.01327 0.00596 -0.0165 0.4888 0.9844
2.750 0.5480 0.01337 0.00599 -0.0156 0.4725 0.9842
3.000 0.5710 0.01349 0.00603 -0.0147 0.4561 0.9840
3.250 0.5946 0.01361 0.00611 -0.0140 0.4410 0.9840
3.500 0.6192 0.01373 0.00618 -0.0135 0.4263 0.9841
3.750 0.6429 0.01388 0.00627 -0.0128 0.4123 0.9841
4.000 0.6657 0.01406 0.00640 -0.0119 0.3978 0.9840
4.250 0.6886 0.01425 0.00653 -0.0111 0.3843 0.9840
4.500 0.7115 0.01445 0.00669 -0.0103 0.3733 0.9839
4.750 0.7344 0.01467 0.00686 -0.0095 0.3627 0.9839
5.000 0.7575 0.01486 0.00704 -0.0088 0.3509 0.9840
5.250 0.7805 0.01508 0.00723 -0.0081 0.3389 0.9840
5.500 0.8034 0.01533 0.00745 -0.0074 0.3291 0.9841
5.750 0.8270 0.01550 0.00767 -0.0068 0.3210 0.9843
6.000 0.8500 0.01575 0.00790 -0.0061 0.3133 0.9844
6.250 0.8736 0.01593 0.00815 -0.0055 0.3046 0.9846
6.500 0.8967 0.01618 0.00842 -0.0049 0.2966 0.9849
6.750 0.9203 0.01638 0.00869 -0.0043 0.2877 0.9851
7.000 0.9434 0.01663 0.00898 -0.0038 0.2792 0.9855
7.250 0.9664 0.01688 0.00929 -0.0032 0.2687 0.9858
7.500 0.9895 0.01714 0.00960 -0.0026 0.2562 0.9863
7.750 1.0127 0.01744 0.00994 -0.0022 0.2409 0.9870
8.000 1.0347 0.01785 0.01031 -0.0017 0.2178 0.9878
8.250 1.0543 0.01845 0.01079 -0.0010 0.1897 0.9887
8.750 1.0887 0.01992 0.01209 0.0011 0.1482 0.9907
9.000 1.1056 0.02063 0.01278 0.0022 0.1347 0.9918
9.500 1.1381 0.02210 0.01427 0.0044 0.1116 0.9942
9.750 1.1554 0.02289 0.01506 0.0050 0.1010 0.9955
10.000 1.1714 0.02372 0.01591 0.0058 0.0936 0.9970
10.250 1.1875 0.02452 0.01677 0.0066 0.0867 0.9986
10.500 1.1995 0.02543 0.01772 0.0078 0.0802 1.0000
10.750 1.1923 0.02616 0.01851 0.0127 0.0756 1.0000
11.000 1.1798 0.02721 0.01958 0.0176 0.0712 1.0000
11.250 1.1745 0.02817 0.02063 0.0214 0.0669 1.0000
11.500 1.1679 0.02932 0.02180 0.0251 0.0602 1.0000
11.750 1.1620 0.03057 0.02305 0.0284 0.0521 1.0000
12.000 1.1529 0.03221 0.02463 0.0317 0.0406 1.0000
12.250 1.1443 0.03406 0.02642 0.0344 0.0311 1.0000
12.500 1.1358 0.03616 0.02850 0.0367 0.0261 1.0000
12.750 1.1285 0.03843 0.03077 0.0385 0.0233 1.0000
13.000 1.1241 0.04065 0.03306 0.0398 0.0218 1.0000
13.250 1.1208 0.04294 0.03543 0.0409 0.0209 1.0000
13.500 1.1150 0.04565 0.03821 0.0416 0.0196 1.0000
13.750 1.1111 0.04831 0.04098 0.0420 0.0192 1.0000
14.000 1.1044 0.05141 0.04417 0.0422 0.0185 1.0000
14.250 1.0962 0.05492 0.04779 0.0420 0.0180 1.0000
14.500 1.0906 0.05834 0.05134 0.0416 0.0176 1.0000
14.750 1.0854 0.06185 0.05498 0.0409 0.0172 1.0000
15.000 1.0780 0.06579 0.05905 0.0400 0.0169 1.0000
15.250 1.0713 0.06978 0.06316 0.0390 0.0168 1.0000
15.500 1.0627 0.07417 0.06768 0.0376 0.0164 1.0000
15.750 1.0538 0.07873 0.07236 0.0362 0.0162 1.0000
16.000 1.0451 0.08336 0.07711 0.0346 0.0160 1.0000
16.250 1.0361 0.08815 0.08201 0.0329 0.0159 1.0000
16.500 1.0267 0.09309 0.08706 0.0311 0.0157 1.0000
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