CLARK X AIRFOIL (clarkx-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK X AIRFOIL (clarkx-il) Reynolds number: 200,000 Max Cl/Cd: 76.22 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkx-il-200000.txt Download as CSV file: xf-clarkx-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK X 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3905 0.08981 0.08619 -0.0420 1.0000 0.0817
-8.750 -0.4207 0.08638 0.08290 -0.0437 1.0000 0.0845
-8.500 -0.4586 0.08433 0.08099 -0.0416 1.0000 0.0850
-8.250 -0.4969 0.08125 0.07799 -0.0415 1.0000 0.0853
-8.000 -0.5389 0.07545 0.07203 -0.0454 0.9989 0.0858
-7.750 -0.5213 0.07030 0.06699 -0.0456 0.9967 0.0873
-7.500 -0.4931 0.07001 0.06676 -0.0434 0.9948 0.0891
-7.250 -0.5029 0.04610 0.04170 -0.0639 0.9834 0.0747
-7.000 -0.4817 0.04087 0.03619 -0.0659 0.9773 0.0695
-6.750 -0.4576 0.03490 0.02959 -0.0689 0.9725 0.0683
-6.500 -0.4301 0.03069 0.02479 -0.0709 0.9680 0.0682
-6.250 -0.4019 0.02834 0.02201 -0.0719 0.9620 0.0699
-6.000 -0.3665 0.02624 0.01946 -0.0740 0.9586 0.0715
-5.750 -0.3275 0.02470 0.01750 -0.0765 0.9562 0.0728
-5.500 -0.3029 0.02268 0.01527 -0.0765 0.9489 0.0748
-5.250 -0.2662 0.02164 0.01418 -0.0786 0.9452 0.0779
-5.000 -0.2261 0.02064 0.01305 -0.0812 0.9427 0.0809
-4.500 -0.1590 0.01884 0.01094 -0.0834 0.9323 0.0873
-4.250 -0.1205 0.01800 0.01017 -0.0857 0.9291 0.0926
-4.000 -0.0809 0.01734 0.00941 -0.0878 0.9266 0.0982
-3.750 -0.0552 0.01664 0.00875 -0.0874 0.9185 0.1036
-3.500 -0.0204 0.01615 0.00826 -0.0887 0.9140 0.1120
-3.250 0.0156 0.01545 0.00762 -0.0902 0.9107 0.1219
-3.000 0.0396 0.01506 0.00726 -0.0893 0.9017 0.1327
-2.750 0.0721 0.01447 0.00676 -0.0901 0.8969 0.1506
-2.500 0.0983 0.01395 0.00638 -0.0897 0.8894 0.1787
-2.250 0.1261 0.01327 0.00610 -0.0897 0.8828 0.2555
-2.000 0.1537 0.01276 0.00589 -0.0895 0.8766 0.3439
-1.750 0.1784 0.01233 0.00574 -0.0888 0.8682 0.4188
-1.500 0.2047 0.01173 0.00556 -0.0882 0.8624 0.5278
-1.250 0.2236 0.01116 0.00558 -0.0859 0.8529 0.6805
-1.000 0.2509 0.01068 0.00556 -0.0842 0.8477 0.8535
-0.750 0.2988 0.01063 0.00555 -0.0873 0.8393 0.9479
-0.500 0.3639 0.01046 0.00524 -0.0944 0.8338 0.9902
-0.250 0.4046 0.01039 0.00507 -0.0970 0.8240 1.0000
0.000 0.4301 0.01033 0.00489 -0.0963 0.8152 1.0000
0.250 0.4535 0.01034 0.00481 -0.0954 0.8044 1.0000
0.500 0.4775 0.01037 0.00476 -0.0945 0.7941 1.0000
0.750 0.5038 0.01035 0.00462 -0.0939 0.7854 1.0000
1.000 0.5270 0.01041 0.00463 -0.0929 0.7738 1.0000
1.250 0.5515 0.01046 0.00461 -0.0920 0.7633 1.0000
1.500 0.5777 0.01049 0.00453 -0.0914 0.7538 1.0000
1.750 0.6013 0.01056 0.00457 -0.0904 0.7417 1.0000
2.000 0.6256 0.01063 0.00459 -0.0895 0.7300 1.0000
2.250 0.6505 0.01070 0.00459 -0.0887 0.7184 1.0000
2.500 0.6755 0.01075 0.00456 -0.0879 0.7057 1.0000
2.750 0.6998 0.01082 0.00456 -0.0869 0.6918 1.0000
3.000 0.7236 0.01091 0.00462 -0.0859 0.6775 1.0000
3.250 0.7477 0.01101 0.00469 -0.0850 0.6635 1.0000
3.500 0.7720 0.01113 0.00477 -0.0842 0.6495 1.0000
3.750 0.7964 0.01126 0.00487 -0.0833 0.6350 1.0000
4.000 0.8207 0.01140 0.00498 -0.0824 0.6202 1.0000
4.250 0.8449 0.01156 0.00510 -0.0816 0.6051 1.0000
4.500 0.8689 0.01173 0.00524 -0.0807 0.5891 1.0000
4.750 0.8926 0.01192 0.00539 -0.0798 0.5720 1.0000
5.000 0.9161 0.01213 0.00555 -0.0788 0.5543 1.0000
5.250 0.9393 0.01238 0.00574 -0.0778 0.5363 1.0000
5.500 0.9623 0.01264 0.00598 -0.0768 0.5176 1.0000
5.750 0.9848 0.01292 0.00623 -0.0758 0.4980 1.0000
6.000 1.0070 0.01324 0.00651 -0.0746 0.4781 1.0000
6.250 1.0287 0.01361 0.00681 -0.0735 0.4581 1.0000
6.500 1.0498 0.01397 0.00714 -0.0722 0.4361 1.0000
6.750 1.0699 0.01439 0.00747 -0.0708 0.4131 1.0000
7.000 1.0890 0.01482 0.00783 -0.0693 0.3877 1.0000
7.250 1.1071 0.01532 0.00823 -0.0676 0.3626 1.0000
7.500 1.1253 0.01581 0.00865 -0.0661 0.3383 1.0000
7.750 1.1433 0.01635 0.00911 -0.0645 0.3167 1.0000
8.000 1.1615 0.01686 0.00960 -0.0630 0.2957 1.0000
8.250 1.1786 0.01742 0.01011 -0.0613 0.2752 1.0000
8.500 1.1956 0.01799 0.01065 -0.0597 0.2560 1.0000
8.750 1.2123 0.01855 0.01121 -0.0580 0.2353 1.0000
9.000 1.2257 0.01925 0.01184 -0.0559 0.2120 1.0000
9.250 1.2352 0.02011 0.01257 -0.0532 0.1774 1.0000
9.750 1.2259 0.02410 0.01568 -0.0448 0.0655 1.0000
10.000 1.2286 0.02574 0.01728 -0.0418 0.0556 1.0000
10.250 1.2344 0.02719 0.01879 -0.0394 0.0503 1.0000
10.500 1.2354 0.02902 0.02065 -0.0367 0.0468 1.0000
10.750 1.2415 0.03054 0.02228 -0.0347 0.0441 1.0000
11.000 1.2452 0.03232 0.02412 -0.0327 0.0419 1.0000
11.250 1.2450 0.03447 0.02632 -0.0306 0.0404 1.0000
11.500 1.2445 0.03680 0.02867 -0.0285 0.0391 1.0000
11.750 1.2513 0.03856 0.03055 -0.0270 0.0379 1.0000
12.000 1.2576 0.04041 0.03250 -0.0256 0.0366 1.0000
12.250 1.2637 0.04231 0.03446 -0.0243 0.0352 1.0000
12.500 1.2696 0.04427 0.03643 -0.0230 0.0339 1.0000
12.750 1.2789 0.04624 0.03835 -0.0214 0.0327 1.0000
13.000 1.2914 0.04803 0.04022 -0.0199 0.0320 1.0000
13.250 1.3013 0.04988 0.04223 -0.0188 0.0314 1.0000
13.500 1.3111 0.05185 0.04435 -0.0176 0.0308 1.0000
13.750 1.3198 0.05397 0.04661 -0.0165 0.0301 1.0000
14.000 1.3266 0.05623 0.04902 -0.0155 0.0294 1.0000
14.250 1.3325 0.05853 0.05143 -0.0146 0.0287 1.0000
14.500 1.3371 0.06097 0.05399 -0.0139 0.0280 1.0000
14.750 1.3443 0.06344 0.05653 -0.0131 0.0274 1.0000
15.000 1.3545 0.06637 0.05956 -0.0122 0.0268 1.0000
15.250 1.3571 0.07021 0.06359 -0.0113 0.0266 1.0000
15.500 1.3512 0.07440 0.06800 -0.0108 0.0265 1.0000
15.750 1.3394 0.07855 0.07238 -0.0108 0.0265 1.0000
16.000 1.3267 0.08301 0.07708 -0.0112 0.0265 1.0000
16.250 1.3133 0.08783 0.08210 -0.0119 0.0265 1.0000
16.500 1.2984 0.09274 0.08725 -0.0131 0.0265 1.0000
16.750 1.2816 0.09799 0.09271 -0.0150 0.0266 1.0000
17.000 1.2639 0.10365 0.09859 -0.0177 0.0267 1.0000
17.250 1.2441 0.11009 0.10526 -0.0213 0.0269 1.0000
17.500 1.2181 0.11826 0.11370 -0.0265 0.0272 1.0000
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