CLARK-Y 11.7% smoothed (clarkysm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK-Y 11.7% smoothed (clarkysm-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.23 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkysm-il-1000000-n5.txt Download as CSV file: xf-clarkysm-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK-Y 11.7% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.6696 0.10205 0.09987 -0.0482 1.0000 0.0094
-15.000 -1.0206 0.03735 0.03431 -0.0940 1.0000 0.0082
-14.500 -1.0729 0.03154 0.02824 -0.0887 1.0000 0.0082
-14.250 -1.0719 0.02959 0.02616 -0.0874 0.9986 0.0083
-14.000 -1.0534 0.02770 0.02413 -0.0887 0.9960 0.0085
-13.750 -1.0330 0.02622 0.02253 -0.0895 0.9935 0.0086
-13.500 -1.0146 0.02487 0.02108 -0.0896 0.9904 0.0087
-13.250 -0.9924 0.02371 0.01982 -0.0901 0.9876 0.0089
-13.000 -0.9683 0.02263 0.01862 -0.0908 0.9853 0.0091
-12.750 -0.9424 0.02163 0.01752 -0.0916 0.9836 0.0093
-12.500 -0.9214 0.02075 0.01654 -0.0912 0.9797 0.0094
-12.250 -0.8976 0.01993 0.01563 -0.0913 0.9763 0.0096
-12.000 -0.8715 0.01911 0.01471 -0.0917 0.9738 0.0099
-11.750 -0.8431 0.01839 0.01390 -0.0925 0.9718 0.0100
-11.500 -0.8160 0.01772 0.01314 -0.0930 0.9690 0.0102
-11.250 -0.7921 0.01690 0.01223 -0.0928 0.9641 0.0105
-11.000 -0.7626 0.01618 0.01145 -0.0938 0.9611 0.0109
-10.750 -0.7314 0.01557 0.01078 -0.0950 0.9585 0.0112
-10.500 -0.7023 0.01503 0.01017 -0.0956 0.9545 0.0115
-10.250 -0.6743 0.01453 0.00960 -0.0960 0.9489 0.0119
-10.000 -0.6436 0.01403 0.00903 -0.0969 0.9443 0.0122
-9.750 -0.6154 0.01358 0.00851 -0.0972 0.9384 0.0125
-9.500 -0.5875 0.01318 0.00802 -0.0974 0.9314 0.0128
-9.250 -0.5603 0.01271 0.00748 -0.0975 0.9247 0.0133
-9.000 -0.5347 0.01231 0.00703 -0.0972 0.9165 0.0138
-8.750 -0.5083 0.01198 0.00664 -0.0970 0.9091 0.0143
-8.500 -0.4828 0.01168 0.00629 -0.0965 0.9006 0.0149
-8.250 -0.4570 0.01141 0.00595 -0.0961 0.8929 0.0155
-8.000 -0.4317 0.01116 0.00562 -0.0956 0.8842 0.0159
-7.750 -0.4068 0.01084 0.00525 -0.0950 0.8762 0.0167
-7.500 -0.3818 0.01058 0.00494 -0.0944 0.8676 0.0175
-7.250 -0.3565 0.01035 0.00467 -0.0939 0.8597 0.0183
-7.000 -0.3311 0.01015 0.00440 -0.0933 0.8511 0.0192
-6.750 -0.3058 0.00992 0.00413 -0.0927 0.8431 0.0203
-6.500 -0.2806 0.00972 0.00389 -0.0921 0.8345 0.0217
-6.250 -0.2549 0.00954 0.00367 -0.0916 0.8265 0.0231
-6.000 -0.2296 0.00937 0.00344 -0.0910 0.8180 0.0245
-5.750 -0.2039 0.00919 0.00324 -0.0905 0.8099 0.0262
-5.500 -0.1783 0.00906 0.00305 -0.0899 0.8014 0.0280
-5.250 -0.1525 0.00889 0.00287 -0.0894 0.7928 0.0304
-5.000 -0.1269 0.00876 0.00271 -0.0889 0.7844 0.0331
-4.750 -0.1010 0.00862 0.00255 -0.0884 0.7757 0.0359
-4.500 -0.0752 0.00851 0.00241 -0.0878 0.7670 0.0388
-4.250 -0.0493 0.00840 0.00228 -0.0873 0.7575 0.0420
-4.000 -0.0234 0.00829 0.00215 -0.0868 0.7485 0.0461
-3.500 0.0282 0.00812 0.00193 -0.0857 0.7284 0.0545
-3.250 0.0537 0.00807 0.00183 -0.0851 0.7151 0.0583
-3.000 0.0785 0.00801 0.00174 -0.0844 0.6982 0.0644
-2.750 0.1037 0.00798 0.00165 -0.0837 0.6828 0.0691
-2.500 0.1292 0.00792 0.00158 -0.0831 0.6707 0.0765
-2.250 0.1548 0.00788 0.00151 -0.0825 0.6595 0.0839
-2.000 0.1807 0.00782 0.00145 -0.0820 0.6484 0.0931
-1.750 0.2063 0.00777 0.00139 -0.0815 0.6368 0.1046
-1.500 0.2316 0.00771 0.00134 -0.0809 0.6256 0.1213
-1.250 0.2569 0.00764 0.00130 -0.0803 0.6145 0.1418
-1.000 0.2822 0.00757 0.00127 -0.0797 0.6024 0.1696
-0.750 0.3072 0.00752 0.00126 -0.0790 0.5895 0.1974
-0.500 0.3321 0.00747 0.00125 -0.0784 0.5772 0.2272
-0.250 0.3571 0.00744 0.00125 -0.0777 0.5652 0.2548
0.000 0.3822 0.00741 0.00126 -0.0771 0.5521 0.2836
0.250 0.4066 0.00738 0.00128 -0.0764 0.5372 0.3199
0.500 0.4308 0.00733 0.00130 -0.0756 0.5230 0.3650
0.750 0.4544 0.00726 0.00134 -0.0747 0.5088 0.4227
1.000 0.4775 0.00716 0.00138 -0.0737 0.4952 0.4942
1.250 0.4990 0.00700 0.00144 -0.0725 0.4816 0.5870
1.500 0.5154 0.00668 0.00152 -0.0700 0.4681 0.7378
1.750 0.5320 0.00643 0.00163 -0.0673 0.4527 0.8705
2.000 0.5877 0.00657 0.00183 -0.0735 0.4299 0.9443
2.250 0.6382 0.00680 0.00196 -0.0786 0.4108 0.9608
2.750 0.7045 0.00718 0.00218 -0.0810 0.3803 0.9788
3.000 0.7346 0.00737 0.00230 -0.0816 0.3657 0.9852
3.250 0.7690 0.00758 0.00243 -0.0831 0.3504 0.9916
3.750 0.8472 0.00810 0.00273 -0.0884 0.3122 1.0000
4.000 0.8675 0.00829 0.00286 -0.0869 0.2991 1.0000
4.250 0.8879 0.00849 0.00299 -0.0854 0.2861 1.0000
4.500 0.9095 0.00864 0.00311 -0.0841 0.2784 1.0000
4.750 0.9305 0.00881 0.00325 -0.0827 0.2704 1.0000
5.000 0.9519 0.00897 0.00338 -0.0814 0.2620 1.0000
5.250 0.9725 0.00917 0.00354 -0.0799 0.2521 1.0000
5.500 0.9936 0.00936 0.00369 -0.0786 0.2434 1.0000
5.750 1.0145 0.00955 0.00385 -0.0772 0.2350 1.0000
6.000 1.0345 0.00978 0.00403 -0.0756 0.2244 1.0000
6.250 1.0554 0.00997 0.00420 -0.0743 0.2153 1.0000
6.500 1.0750 0.01022 0.00440 -0.0727 0.2030 1.0000
6.750 1.0942 0.01050 0.00462 -0.0710 0.1900 1.0000
7.000 1.1117 0.01085 0.00488 -0.0691 0.1715 1.0000
7.250 1.1260 0.01136 0.00525 -0.0666 0.1443 1.0000
7.500 1.1373 0.01202 0.00572 -0.0637 0.1130 1.0000
7.750 1.1518 0.01247 0.00608 -0.0612 0.0978 1.0000
8.000 1.1660 0.01285 0.00642 -0.0587 0.0884 1.0000
8.250 1.1821 0.01316 0.00672 -0.0565 0.0825 1.0000
8.500 1.1973 0.01353 0.00706 -0.0543 0.0758 1.0000
8.750 1.2146 0.01384 0.00738 -0.0524 0.0720 1.0000
9.000 1.2308 0.01422 0.00774 -0.0504 0.0677 1.0000
9.250 1.2480 0.01456 0.00810 -0.0487 0.0642 1.0000
9.500 1.2656 0.01491 0.00846 -0.0470 0.0618 1.0000
9.750 1.2825 0.01530 0.00886 -0.0453 0.0591 1.0000
10.000 1.2982 0.01577 0.00931 -0.0435 0.0553 1.0000
10.250 1.3158 0.01614 0.00972 -0.0420 0.0537 1.0000
10.500 1.3327 0.01657 0.01017 -0.0405 0.0516 1.0000
10.750 1.3483 0.01707 0.01068 -0.0388 0.0490 1.0000
11.000 1.3633 0.01762 0.01123 -0.0371 0.0460 1.0000
11.250 1.3798 0.01810 0.01174 -0.0356 0.0446 1.0000
11.500 1.3951 0.01865 0.01232 -0.0341 0.0425 1.0000
11.750 1.4095 0.01928 0.01297 -0.0325 0.0405 1.0000
12.000 1.4231 0.01997 0.01367 -0.0309 0.0384 1.0000
12.250 1.4378 0.02060 0.01434 -0.0295 0.0370 1.0000
12.500 1.4515 0.02132 0.01509 -0.0280 0.0351 1.0000
12.750 1.4632 0.02218 0.01596 -0.0264 0.0329 1.0000
13.000 1.4756 0.02302 0.01684 -0.0250 0.0315 1.0000
13.250 1.4877 0.02391 0.01777 -0.0236 0.0296 1.0000
13.500 1.4984 0.02492 0.01880 -0.0222 0.0279 1.0000
13.750 1.5076 0.02606 0.01997 -0.0208 0.0259 1.0000
14.000 1.5174 0.02720 0.02116 -0.0195 0.0242 1.0000
14.250 1.5257 0.02849 0.02248 -0.0181 0.0227 1.0000
14.500 1.5330 0.02988 0.02391 -0.0169 0.0213 1.0000
14.750 1.5405 0.03132 0.02541 -0.0158 0.0201 1.0000
15.000 1.5459 0.03296 0.02710 -0.0146 0.0187 1.0000
15.250 1.5504 0.03475 0.02892 -0.0136 0.0174 1.0000
15.500 1.5552 0.03657 0.03081 -0.0127 0.0163 1.0000
15.750 1.5593 0.03852 0.03283 -0.0120 0.0156 1.0000
16.000 1.5604 0.04082 0.03518 -0.0112 0.0145 1.0000
16.250 1.5621 0.04313 0.03756 -0.0107 0.0136 1.0000
16.500 1.5633 0.04559 0.04009 -0.0103 0.0130 1.0000
16.750 1.5638 0.04820 0.04278 -0.0101 0.0125 1.0000
17.000 1.5607 0.05125 0.04590 -0.0099 0.0117 1.0000
17.250 1.5592 0.05426 0.04899 -0.0100 0.0113 1.0000
17.500 1.5567 0.05745 0.05227 -0.0102 0.0108 1.0000
17.750 1.5532 0.06085 0.05575 -0.0106 0.0105 1.0000
18.000 1.5480 0.06449 0.05949 -0.0111 0.0101 1.0000
18.250 1.5424 0.06830 0.06339 -0.0118 0.0099 1.0000
18.500 1.5344 0.07253 0.06771 -0.0127 0.0095 1.0000
18.750 1.5253 0.07696 0.07224 -0.0137 0.0093 1.0000
19.000 1.5148 0.08165 0.07703 -0.0149 0.0089 1.0000
19.250 1.5050 0.08634 0.08183 -0.0163 0.0088 1.0000
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Polar data table (+)
Polar graphs
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