CLARK Y AIRFOIL (clarky-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: CLARK Y AIRFOIL (clarky-il) Reynolds number: 500,000 Max Cl/Cd: 98.66 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarky-il-500000.txt Download as CSV file: xf-clarky-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK Y AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3940 0.08504 0.08280 -0.0444 1.0000 0.0381
-9.000 -0.4033 0.08275 0.08056 -0.0431 1.0000 0.0387
-8.750 -0.4929 0.04594 0.04332 -0.0802 0.9855 0.0348
-8.500 -0.4974 0.03456 0.03116 -0.0866 0.9772 0.0344
-8.250 -0.4759 0.02994 0.02595 -0.0893 0.9733 0.0352
-8.000 -0.4463 0.02768 0.02325 -0.0914 0.9710 0.0358
-7.750 -0.4301 0.02331 0.01843 -0.0916 0.9643 0.0365
-7.500 -0.4024 0.02155 0.01653 -0.0925 0.9600 0.0373
-7.250 -0.3722 0.02018 0.01500 -0.0935 0.9568 0.0379
-7.000 -0.3479 0.01919 0.01389 -0.0931 0.9498 0.0386
-6.750 -0.3205 0.01829 0.01288 -0.0932 0.9443 0.0394
-6.500 -0.2942 0.01724 0.01167 -0.0930 0.9387 0.0399
-6.250 -0.2696 0.01629 0.01057 -0.0923 0.9311 0.0403
-6.000 -0.2426 0.01543 0.00958 -0.0921 0.9257 0.0408
-5.750 -0.2181 0.01471 0.00876 -0.0913 0.9173 0.0413
-5.500 -0.1915 0.01408 0.00802 -0.0910 0.9110 0.0419
-5.250 -0.1658 0.01361 0.00747 -0.0904 0.9029 0.0426
-5.000 -0.1391 0.01312 0.00689 -0.0900 0.8960 0.0430
-4.750 -0.1139 0.01244 0.00613 -0.0894 0.8877 0.0436
-4.500 -0.0885 0.01171 0.00534 -0.0889 0.8804 0.0446
-4.250 -0.0629 0.01125 0.00485 -0.0884 0.8713 0.0457
-4.000 -0.0363 0.01091 0.00444 -0.0879 0.8630 0.0469
-3.750 -0.0102 0.01061 0.00411 -0.0875 0.8528 0.0482
-3.500 0.0167 0.01036 0.00381 -0.0871 0.8441 0.0499
-3.250 0.0438 0.01016 0.00354 -0.0868 0.8350 0.0516
-3.000 0.0703 0.00985 0.00319 -0.0864 0.8255 0.0547
-2.750 0.0975 0.00965 0.00296 -0.0861 0.8168 0.0589
-2.500 0.1243 0.00942 0.00275 -0.0857 0.8067 0.0669
-2.250 0.1510 0.00915 0.00254 -0.0854 0.7976 0.0936
-2.000 0.1774 0.00887 0.00238 -0.0851 0.7876 0.1350
-1.750 0.2037 0.00859 0.00228 -0.0848 0.7769 0.1935
-1.500 0.2303 0.00838 0.00221 -0.0846 0.7675 0.2491
-1.250 0.2571 0.00820 0.00215 -0.0844 0.7583 0.2986
-1.000 0.2836 0.00799 0.00210 -0.0841 0.7496 0.3576
-0.750 0.3095 0.00774 0.00206 -0.0838 0.7404 0.4367
-0.500 0.3338 0.00732 0.00205 -0.0831 0.7305 0.5667
-0.250 0.3551 0.00684 0.00209 -0.0816 0.7213 0.7347
0.000 0.3760 0.00652 0.00219 -0.0794 0.7115 0.8796
0.250 0.4107 0.00654 0.00224 -0.0804 0.7020 0.9451
0.500 0.4534 0.00663 0.00225 -0.0833 0.6921 0.9765
0.750 0.5065 0.00669 0.00224 -0.0886 0.6803 0.9953
1.000 0.5439 0.00675 0.00222 -0.0907 0.6684 1.0000
1.250 0.5687 0.00682 0.00222 -0.0901 0.6567 1.0000
1.500 0.5934 0.00691 0.00222 -0.0894 0.6450 1.0000
1.750 0.6180 0.00699 0.00225 -0.0887 0.6323 1.0000
2.000 0.6426 0.00708 0.00228 -0.0880 0.6193 1.0000
2.250 0.6670 0.00719 0.00232 -0.0872 0.6053 1.0000
2.500 0.6912 0.00732 0.00237 -0.0864 0.5901 1.0000
2.750 0.7151 0.00746 0.00244 -0.0855 0.5739 1.0000
3.000 0.7389 0.00761 0.00251 -0.0847 0.5572 1.0000
3.250 0.7624 0.00779 0.00261 -0.0838 0.5390 1.0000
3.500 0.7857 0.00799 0.00271 -0.0828 0.5188 1.0000
3.750 0.8090 0.00820 0.00284 -0.0819 0.4959 1.0000
4.000 0.8315 0.00848 0.00299 -0.0808 0.4690 1.0000
4.250 0.8536 0.00880 0.00315 -0.0797 0.4386 1.0000
4.500 0.8757 0.00914 0.00334 -0.0787 0.4111 1.0000
4.750 0.8987 0.00945 0.00355 -0.0778 0.3891 1.0000
5.000 0.9220 0.00976 0.00376 -0.0770 0.3723 1.0000
5.250 0.9457 0.01004 0.00398 -0.0763 0.3590 1.0000
5.500 0.9697 0.01032 0.00421 -0.0756 0.3484 1.0000
5.750 0.9940 0.01057 0.00444 -0.0750 0.3396 1.0000
6.000 1.0185 0.01082 0.00468 -0.0745 0.3319 1.0000
6.250 1.0426 0.01108 0.00492 -0.0739 0.3237 1.0000
6.500 1.0671 0.01132 0.00517 -0.0733 0.3159 1.0000
6.750 1.0910 0.01160 0.00543 -0.0727 0.3073 1.0000
7.000 1.1155 0.01183 0.00567 -0.0721 0.2979 1.0000
7.250 1.1388 0.01212 0.00594 -0.0715 0.2876 1.0000
7.500 1.1627 0.01238 0.00619 -0.0708 0.2767 1.0000
7.750 1.1866 0.01263 0.00644 -0.0702 0.2648 1.0000
8.000 1.2096 0.01293 0.00672 -0.0695 0.2509 1.0000
8.250 1.2317 0.01328 0.00703 -0.0687 0.2337 1.0000
8.500 1.2520 0.01375 0.00740 -0.0676 0.2092 1.0000
8.750 1.2691 0.01442 0.00789 -0.0660 0.1778 1.0000
9.000 1.2847 0.01519 0.00850 -0.0643 0.1507 1.0000
9.250 1.2999 0.01594 0.00914 -0.0624 0.1304 1.0000
9.500 1.3150 0.01659 0.00973 -0.0605 0.1159 1.0000
9.750 1.3299 0.01726 0.01035 -0.0587 0.1043 1.0000
10.000 1.3447 0.01794 0.01099 -0.0568 0.0940 1.0000
10.250 1.3602 0.01858 0.01163 -0.0551 0.0853 1.0000
10.500 1.3747 0.01929 0.01232 -0.0534 0.0759 1.0000
10.750 1.3868 0.02016 0.01312 -0.0514 0.0621 1.0000
11.000 1.3917 0.02153 0.01429 -0.0487 0.0373 1.0000
11.250 1.3923 0.02324 0.01587 -0.0456 0.0223 1.0000
11.500 1.3998 0.02452 0.01720 -0.0434 0.0198 1.0000
11.750 1.4079 0.02581 0.01857 -0.0415 0.0183 1.0000
12.000 1.4163 0.02711 0.01997 -0.0397 0.0173 1.0000
12.250 1.4223 0.02865 0.02159 -0.0380 0.0164 1.0000
12.500 1.4251 0.03050 0.02353 -0.0361 0.0157 1.0000
12.750 1.4237 0.03282 0.02595 -0.0343 0.0151 1.0000
13.000 1.4287 0.03464 0.02789 -0.0330 0.0148 1.0000
13.250 1.4317 0.03673 0.03008 -0.0319 0.0145 1.0000
13.500 1.4329 0.03907 0.03254 -0.0308 0.0141 1.0000
13.750 1.4323 0.04167 0.03524 -0.0299 0.0138 1.0000
14.000 1.4303 0.04452 0.03820 -0.0293 0.0135 1.0000
14.250 1.4269 0.04763 0.04141 -0.0288 0.0133 1.0000
14.500 1.4220 0.05103 0.04492 -0.0285 0.0130 1.0000
14.750 1.4153 0.05481 0.04879 -0.0286 0.0128 1.0000
15.000 1.4066 0.05897 0.05306 -0.0288 0.0126 1.0000
15.250 1.3959 0.06349 0.05768 -0.0293 0.0124 1.0000
15.500 1.3832 0.06838 0.06268 -0.0300 0.0122 1.0000
15.750 1.3730 0.07302 0.06742 -0.0307 0.0120 1.0000
16.000 1.3700 0.07690 0.07141 -0.0315 0.0119 1.0000
16.250 1.3662 0.08095 0.07557 -0.0325 0.0117 1.0000
16.500 1.3615 0.08517 0.07990 -0.0335 0.0116 1.0000
16.750 1.3564 0.08948 0.08431 -0.0346 0.0114 1.0000
17.000 1.3510 0.09382 0.08876 -0.0358 0.0113 1.0000
|
Polar data table (+)
Polar graphs
<< Back to CLARK Y AIRFOIL (clarky-il)