CLARK-Y 11.7% smoothed (clarkysm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK-Y 11.7% smoothed (clarkysm-il) Reynolds number: 500,000 Max Cl/Cd: 101.56 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkysm-il-500000.txt Download as CSV file: xf-clarkysm-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3683 0.10567 0.10330 -0.0408 1.0000 0.0293
-10.500 -0.6823 0.04568 0.04313 -0.0696 0.9978 0.0189
-10.250 -0.6978 0.03453 0.03111 -0.0784 0.9877 0.0191
-10.000 -0.6810 0.03037 0.02639 -0.0811 0.9839 0.0194
-9.750 -0.6692 0.02674 0.02230 -0.0813 0.9776 0.0198
-9.500 -0.6439 0.02477 0.02018 -0.0825 0.9743 0.0203
-9.250 -0.6129 0.02362 0.01892 -0.0842 0.9723 0.0209
-9.000 -0.5809 0.02233 0.01745 -0.0859 0.9708 0.0216
-8.750 -0.5598 0.02133 0.01629 -0.0852 0.9643 0.0223
-8.500 -0.5290 0.02029 0.01503 -0.0863 0.9615 0.0232
-8.250 -0.4985 0.01871 0.01323 -0.0876 0.9595 0.0242
-8.000 -0.4640 0.01788 0.01238 -0.0894 0.9582 0.0253
-7.750 -0.4280 0.01708 0.01148 -0.0914 0.9570 0.0264
-7.500 -0.4049 0.01642 0.01071 -0.0905 0.9503 0.0274
-7.250 -0.3725 0.01571 0.00986 -0.0915 0.9472 0.0285
-7.000 -0.3400 0.01473 0.00887 -0.0928 0.9446 0.0303
-6.750 -0.3048 0.01425 0.00834 -0.0944 0.9423 0.0322
-6.500 -0.2811 0.01388 0.00787 -0.0934 0.9346 0.0337
-6.250 -0.2516 0.01304 0.00701 -0.0939 0.9301 0.0360
-6.000 -0.2205 0.01267 0.00661 -0.0945 0.9255 0.0385
-5.750 -0.1950 0.01233 0.00620 -0.0939 0.9178 0.0408
-5.500 -0.1654 0.01182 0.00569 -0.0943 0.9127 0.0443
-5.250 -0.1400 0.01160 0.00542 -0.0936 0.9048 0.0476
-5.000 -0.1130 0.01112 0.00492 -0.0934 0.8982 0.0517
-4.750 -0.0864 0.01094 0.00471 -0.0930 0.8906 0.0560
-4.500 -0.0603 0.01058 0.00432 -0.0925 0.8832 0.0609
-4.250 -0.0337 0.01041 0.00412 -0.0922 0.8756 0.0661
-4.000 -0.0079 0.01011 0.00380 -0.0916 0.8677 0.0722
-3.750 0.0184 0.00995 0.00361 -0.0911 0.8597 0.0783
-3.500 0.0442 0.00969 0.00334 -0.0906 0.8515 0.0861
-3.250 0.0702 0.00956 0.00317 -0.0900 0.8430 0.0934
-3.000 0.0960 0.00932 0.00294 -0.0895 0.8348 0.1052
-2.750 0.1207 0.00911 0.00278 -0.0887 0.8256 0.1199
-2.500 0.1464 0.00889 0.00259 -0.0881 0.8161 0.1435
-2.250 0.1702 0.00865 0.00246 -0.0872 0.8045 0.1833
-2.000 0.1942 0.00842 0.00236 -0.0863 0.7933 0.2320
-1.750 0.2192 0.00823 0.00227 -0.0856 0.7840 0.2810
-1.500 0.2433 0.00803 0.00221 -0.0848 0.7741 0.3316
-1.250 0.2669 0.00780 0.00216 -0.0839 0.7647 0.3962
-1.000 0.2891 0.00749 0.00210 -0.0827 0.7554 0.4907
-0.750 0.3083 0.00710 0.00210 -0.0808 0.7453 0.6129
-0.500 0.3253 0.00668 0.00213 -0.0781 0.7358 0.7574
-0.250 0.3584 0.00643 0.00223 -0.0787 0.7260 0.8886
0.000 0.4254 0.00653 0.00232 -0.0869 0.7151 0.9440
0.250 0.4685 0.00668 0.00237 -0.0899 0.7043 0.9632
0.500 0.5132 0.00684 0.00245 -0.0933 0.6929 0.9784
0.750 0.5634 0.00697 0.00250 -0.0979 0.6802 0.9890
1.000 0.6073 0.00707 0.00251 -0.1014 0.6666 0.9957
1.250 0.6486 0.00712 0.00248 -0.1043 0.6529 1.0000
1.500 0.6693 0.00719 0.00248 -0.1028 0.6401 1.0000
1.750 0.6900 0.00727 0.00249 -0.1013 0.6268 1.0000
2.000 0.7106 0.00737 0.00251 -0.0998 0.6126 1.0000
2.250 0.7313 0.00747 0.00254 -0.0983 0.5977 1.0000
2.500 0.7518 0.00759 0.00259 -0.0967 0.5819 1.0000
2.750 0.7721 0.00772 0.00266 -0.0951 0.5658 1.0000
3.000 0.7925 0.00787 0.00273 -0.0935 0.5495 1.0000
3.250 0.8128 0.00803 0.00282 -0.0919 0.5324 1.0000
3.500 0.8328 0.00820 0.00293 -0.0903 0.5144 1.0000
3.750 0.8524 0.00840 0.00305 -0.0886 0.4951 1.0000
4.000 0.8713 0.00863 0.00319 -0.0867 0.4748 1.0000
4.250 0.8897 0.00889 0.00334 -0.0848 0.4520 1.0000
4.500 0.9077 0.00917 0.00350 -0.0828 0.4284 1.0000
4.750 0.9260 0.00946 0.00369 -0.0809 0.4083 1.0000
5.000 0.9448 0.00973 0.00388 -0.0791 0.3887 1.0000
5.250 0.9638 0.01000 0.00408 -0.0773 0.3727 1.0000
5.500 0.9830 0.01027 0.00429 -0.0756 0.3586 1.0000
5.750 1.0020 0.01055 0.00451 -0.0739 0.3452 1.0000
6.000 1.0210 0.01083 0.00473 -0.0722 0.3325 1.0000
6.250 1.0408 0.01107 0.00495 -0.0706 0.3206 1.0000
6.500 1.0604 0.01133 0.00519 -0.0690 0.3110 1.0000
6.750 1.0791 0.01162 0.00544 -0.0673 0.3018 1.0000
7.000 1.0992 0.01184 0.00568 -0.0658 0.2929 1.0000
7.250 1.1174 0.01214 0.00595 -0.0640 0.2837 1.0000
7.500 1.1368 0.01238 0.00620 -0.0625 0.2746 1.0000
7.750 1.1548 0.01266 0.00648 -0.0606 0.2658 1.0000
8.000 1.1704 0.01297 0.00676 -0.0583 0.2555 1.0000
8.250 1.1878 0.01322 0.00703 -0.0564 0.2446 1.0000
8.500 1.2037 0.01355 0.00734 -0.0542 0.2313 1.0000
8.750 1.2185 0.01395 0.00768 -0.0520 0.2142 1.0000
9.000 1.2308 0.01449 0.00811 -0.0494 0.1879 1.0000
9.250 1.2362 0.01542 0.00877 -0.0458 0.1453 1.0000
9.500 1.2406 0.01646 0.00960 -0.0423 0.1154 1.0000
9.750 1.2492 0.01733 0.01038 -0.0394 0.1014 1.0000
10.000 1.2610 0.01803 0.01108 -0.0371 0.0937 1.0000
10.250 1.2713 0.01884 0.01189 -0.0347 0.0877 1.0000
10.500 1.2847 0.01949 0.01259 -0.0328 0.0834 1.0000
10.750 1.2949 0.02035 0.01345 -0.0306 0.0793 1.0000
11.000 1.3043 0.02128 0.01442 -0.0284 0.0757 1.0000
11.250 1.3183 0.02196 0.01517 -0.0268 0.0728 1.0000
11.500 1.3295 0.02284 0.01608 -0.0251 0.0699 1.0000
11.750 1.3363 0.02404 0.01730 -0.0229 0.0668 1.0000
12.000 1.3450 0.02515 0.01847 -0.0211 0.0645 1.0000
12.250 1.3585 0.02596 0.01936 -0.0199 0.0622 1.0000
12.500 1.3697 0.02697 0.02042 -0.0185 0.0598 1.0000
12.750 1.3769 0.02830 0.02179 -0.0170 0.0577 1.0000
13.000 1.3772 0.03019 0.02372 -0.0150 0.0551 1.0000
13.250 1.3902 0.03118 0.02481 -0.0141 0.0536 1.0000
13.500 1.4006 0.03239 0.02610 -0.0131 0.0517 1.0000
13.750 1.4091 0.03379 0.02755 -0.0121 0.0497 1.0000
14.000 1.4126 0.03566 0.02946 -0.0110 0.0478 1.0000
14.250 1.4115 0.03802 0.03188 -0.0098 0.0460 1.0000
14.500 1.4214 0.03945 0.03341 -0.0093 0.0444 1.0000
14.750 1.4293 0.04111 0.03516 -0.0087 0.0426 1.0000
15.000 1.4340 0.04311 0.03721 -0.0082 0.0410 1.0000
15.250 1.4315 0.04593 0.04008 -0.0077 0.0392 1.0000
15.500 1.4327 0.04846 0.04271 -0.0074 0.0378 1.0000
15.750 1.4377 0.05065 0.04499 -0.0073 0.0362 1.0000
16.000 1.4404 0.05315 0.04757 -0.0073 0.0346 1.0000
16.250 1.4385 0.05626 0.05073 -0.0074 0.0333 1.0000
16.500 1.4283 0.06044 0.05497 -0.0078 0.0319 1.0000
16.750 1.4320 0.06302 0.05768 -0.0081 0.0306 1.0000
17.000 1.4316 0.06617 0.06094 -0.0087 0.0292 1.0000
17.250 1.4262 0.07004 0.06488 -0.0094 0.0283 1.0000
17.500 1.4185 0.07432 0.06922 -0.0104 0.0271 1.0000
17.750 1.4060 0.07926 0.07424 -0.0116 0.0263 1.0000
18.000 1.4032 0.08299 0.07810 -0.0126 0.0254 1.0000
18.250 1.3959 0.08739 0.08260 -0.0138 0.0247 1.0000
18.500 1.3895 0.09174 0.08705 -0.0152 0.0238 1.0000
18.750 1.3800 0.09657 0.09196 -0.0168 0.0231 1.0000
19.000 1.3682 0.10185 0.09729 -0.0187 0.0222 1.0000
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Polar data table (+)
Polar graphs
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