CLARK YM-18 AIRFOIL (clarym18-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK YM-18 AIRFOIL (clarym18-il) Reynolds number: 200,000 Max Cl/Cd: 56.01 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarym18-il-200000-n5.txt Download as CSV file: xf-clarym18-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK YM-18 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7278 0.07781 0.07257 -0.0822 1.0000 0.0435
-15.500 -0.7701 0.06794 0.06244 -0.0885 1.0000 0.0436
-15.250 -0.7946 0.06136 0.05567 -0.0925 1.0000 0.0437
-15.000 -0.8127 0.05618 0.05032 -0.0952 1.0000 0.0439
-14.750 -0.8274 0.05196 0.04596 -0.0969 1.0000 0.0442
-14.500 -0.8408 0.04846 0.04232 -0.0975 1.0000 0.0444
-14.250 -0.8540 0.04554 0.03928 -0.0971 1.0000 0.0447
-14.000 -0.8678 0.04313 0.03676 -0.0957 1.0000 0.0450
-13.750 -0.8835 0.04118 0.03470 -0.0932 1.0000 0.0452
-13.500 -0.8971 0.03946 0.03287 -0.0904 0.9994 0.0455
-13.250 -0.8840 0.03721 0.03040 -0.0924 0.9946 0.0461
-13.000 -0.8662 0.03562 0.02878 -0.0939 0.9902 0.0467
-12.750 -0.8483 0.03422 0.02733 -0.0949 0.9848 0.0473
-12.500 -0.8270 0.03287 0.02591 -0.0964 0.9807 0.0479
-12.250 -0.8101 0.03167 0.02462 -0.0965 0.9740 0.0486
-12.000 -0.7886 0.03046 0.02330 -0.0973 0.9691 0.0494
-11.750 -0.7681 0.02933 0.02206 -0.0975 0.9636 0.0503
-11.500 -0.7486 0.02829 0.02088 -0.0973 0.9567 0.0512
-11.250 -0.7234 0.02728 0.01982 -0.0981 0.9525 0.0521
-11.000 -0.7052 0.02652 0.01904 -0.0973 0.9448 0.0530
-10.500 -0.6558 0.02494 0.01732 -0.0978 0.9345 0.0557
-10.250 -0.6375 0.02429 0.01655 -0.0965 0.9261 0.0572
-10.000 -0.6132 0.02358 0.01583 -0.0965 0.9206 0.0586
-9.750 -0.5915 0.02300 0.01522 -0.0959 0.9138 0.0601
-9.500 -0.5695 0.02242 0.01456 -0.0951 0.9066 0.0620
-9.250 -0.5437 0.02177 0.01383 -0.0951 0.9015 0.0641
-9.000 -0.5239 0.02128 0.01333 -0.0939 0.8934 0.0658
-8.750 -0.5001 0.02078 0.01277 -0.0934 0.8867 0.0683
-8.500 -0.4742 0.02027 0.01217 -0.0932 0.8814 0.0711
-8.250 -0.4538 0.01985 0.01176 -0.0920 0.8729 0.0735
-8.000 -0.4285 0.01941 0.01125 -0.0917 0.8668 0.0768
-7.750 -0.4046 0.01898 0.01077 -0.0910 0.8603 0.0798
-7.500 -0.3819 0.01860 0.01038 -0.0902 0.8527 0.0829
-7.250 -0.3557 0.01822 0.00990 -0.0899 0.8469 0.0865
-7.000 -0.3327 0.01783 0.00953 -0.0891 0.8398 0.0898
-6.750 -0.3085 0.01751 0.00917 -0.0885 0.8327 0.0938
-6.500 -0.2820 0.01716 0.00875 -0.0882 0.8272 0.0980
-6.250 -0.2588 0.01684 0.00845 -0.0874 0.8199 0.1024
-5.750 -0.2074 0.01621 0.00776 -0.0866 0.8075 0.1134
-5.500 -0.1835 0.01598 0.00753 -0.0858 0.8002 0.1199
-5.250 -0.1586 0.01567 0.00725 -0.0853 0.7935 0.1281
-5.000 -0.1321 0.01537 0.00694 -0.0850 0.7876 0.1376
-4.750 -0.1086 0.01513 0.00674 -0.0842 0.7788 0.1489
-4.500 -0.0826 0.01485 0.00647 -0.0837 0.7714 0.1633
-4.250 -0.0580 0.01462 0.00629 -0.0831 0.7630 0.1803
-4.000 -0.0326 0.01441 0.00611 -0.0825 0.7545 0.1990
-3.750 -0.0067 0.01423 0.00595 -0.0821 0.7466 0.2174
-3.500 0.0185 0.01409 0.00582 -0.0815 0.7377 0.2344
-3.250 0.0455 0.01395 0.00566 -0.0812 0.7307 0.2508
-3.000 0.0705 0.01385 0.00557 -0.0805 0.7216 0.2654
-2.750 0.0971 0.01373 0.00542 -0.0801 0.7133 0.2801
-2.500 0.1220 0.01362 0.00533 -0.0795 0.7036 0.2938
-2.250 0.1481 0.01351 0.00519 -0.0790 0.6943 0.3077
-2.000 0.1732 0.01342 0.00511 -0.0783 0.6845 0.3221
-1.750 0.1989 0.01330 0.00500 -0.0778 0.6764 0.3377
-1.500 0.2240 0.01319 0.00494 -0.0772 0.6685 0.3551
-1.250 0.2489 0.01306 0.00488 -0.0766 0.6600 0.3803
-1.000 0.2728 0.01287 0.00483 -0.0758 0.6517 0.4183
-0.750 0.2957 0.01267 0.00482 -0.0747 0.6422 0.4677
-0.500 0.3189 0.01249 0.00480 -0.0737 0.6333 0.5197
-0.250 0.3418 0.01233 0.00481 -0.0726 0.6235 0.5714
0.000 0.3651 0.01221 0.00484 -0.0714 0.6146 0.6243
0.250 0.3882 0.01212 0.00491 -0.0702 0.6047 0.6757
0.500 0.4120 0.01208 0.00498 -0.0691 0.5953 0.7233
0.750 0.4363 0.01210 0.00507 -0.0680 0.5848 0.7647
1.000 0.4613 0.01215 0.00518 -0.0670 0.5741 0.8011
1.250 0.4866 0.01226 0.00526 -0.0662 0.5624 0.8328
1.500 0.5136 0.01239 0.00540 -0.0657 0.5494 0.8593
1.750 0.5417 0.01255 0.00552 -0.0654 0.5363 0.8829
2.000 0.5705 0.01275 0.00564 -0.0654 0.5228 0.9029
2.250 0.6002 0.01296 0.00578 -0.0657 0.5083 0.9200
2.500 0.6305 0.01318 0.00593 -0.0661 0.4933 0.9354
2.750 0.6602 0.01342 0.00608 -0.0665 0.4778 0.9495
3.000 0.6931 0.01369 0.00625 -0.0677 0.4611 0.9613
3.250 0.7289 0.01401 0.00646 -0.0694 0.4433 0.9732
3.500 0.7680 0.01437 0.00669 -0.0720 0.4252 0.9837
3.750 0.8067 0.01473 0.00693 -0.0746 0.4091 0.9929
4.000 0.8457 0.01510 0.00718 -0.0773 0.3957 1.0000
4.250 0.8567 0.01530 0.00732 -0.0743 0.3870 1.0000
4.500 0.8661 0.01555 0.00748 -0.0709 0.3796 1.0000
4.750 0.8782 0.01577 0.00766 -0.0681 0.3731 1.0000
5.000 0.8899 0.01601 0.00785 -0.0651 0.3668 1.0000
5.250 0.9000 0.01630 0.00805 -0.0619 0.3613 1.0000
5.500 0.9130 0.01652 0.00826 -0.0592 0.3562 1.0000
5.750 0.9271 0.01678 0.00849 -0.0567 0.3514 1.0000
6.000 0.9423 0.01709 0.00876 -0.0545 0.3470 1.0000
6.250 0.9583 0.01746 0.00905 -0.0526 0.3429 1.0000
6.500 0.9772 0.01775 0.00935 -0.0511 0.3388 1.0000
6.750 0.9958 0.01807 0.00968 -0.0497 0.3343 1.0000
7.000 1.0141 0.01844 0.01002 -0.0483 0.3299 1.0000
7.250 1.0323 0.01886 0.01038 -0.0469 0.3256 1.0000
7.500 1.0520 0.01924 0.01076 -0.0457 0.3218 1.0000
7.750 1.0715 0.01960 0.01116 -0.0446 0.3178 1.0000
8.000 1.0901 0.02000 0.01157 -0.0434 0.3133 1.0000
8.250 1.1079 0.02047 0.01201 -0.0421 0.3087 1.0000
8.500 1.1259 0.02096 0.01246 -0.0408 0.3040 1.0000
8.750 1.1433 0.02138 0.01296 -0.0396 0.2990 1.0000
9.000 1.1601 0.02187 0.01348 -0.0382 0.2938 1.0000
9.250 1.1764 0.02244 0.01400 -0.0369 0.2892 1.0000
9.500 1.1939 0.02296 0.01456 -0.0358 0.2851 1.0000
9.750 1.2115 0.02347 0.01515 -0.0347 0.2809 1.0000
10.000 1.2281 0.02403 0.01576 -0.0336 0.2766 1.0000
10.250 1.2438 0.02467 0.01640 -0.0324 0.2726 1.0000
10.500 1.2595 0.02533 0.01706 -0.0312 0.2689 1.0000
10.750 1.2761 0.02594 0.01779 -0.0302 0.2646 1.0000
11.000 1.2910 0.02664 0.01855 -0.0290 0.2599 1.0000
11.250 1.3043 0.02744 0.01937 -0.0278 0.2553 1.0000
11.500 1.3179 0.02826 0.02023 -0.0266 0.2507 1.0000
11.750 1.3316 0.02909 0.02116 -0.0256 0.2451 1.0000
12.000 1.3428 0.03007 0.02218 -0.0244 0.2396 1.0000
12.250 1.3542 0.03109 0.02325 -0.0232 0.2343 1.0000
12.500 1.3660 0.03213 0.02436 -0.0222 0.2280 1.0000
12.750 1.3740 0.03341 0.02567 -0.0210 0.2220 1.0000
13.000 1.3844 0.03461 0.02695 -0.0200 0.2149 1.0000
13.250 1.3903 0.03615 0.02851 -0.0189 0.2075 1.0000
13.500 1.3978 0.03766 0.03007 -0.0179 0.1994 1.0000
13.750 1.4007 0.03956 0.03198 -0.0169 0.1915 1.0000
14.000 1.4049 0.04144 0.03390 -0.0160 0.1831 1.0000
14.250 1.4061 0.04365 0.03612 -0.0151 0.1758 1.0000
14.500 1.4074 0.04594 0.03843 -0.0143 0.1684 1.0000
14.750 1.4071 0.04843 0.04095 -0.0136 0.1621 1.0000
15.000 1.4069 0.05099 0.04355 -0.0131 0.1558 1.0000
15.250 1.4039 0.05391 0.04650 -0.0126 0.1504 1.0000
15.500 1.4037 0.05663 0.04929 -0.0123 0.1448 1.0000
15.750 1.3991 0.05988 0.05256 -0.0121 0.1400 1.0000
16.000 1.3972 0.06290 0.05565 -0.0120 0.1356 1.0000
16.250 1.3944 0.06610 0.05891 -0.0120 0.1314 1.0000
16.500 1.3887 0.06967 0.06252 -0.0122 0.1278 1.0000
16.750 1.3860 0.07296 0.06588 -0.0124 0.1247 1.0000
17.000 1.3837 0.07625 0.06926 -0.0127 0.1216 1.0000
17.250 1.3797 0.07978 0.07285 -0.0131 0.1189 1.0000
17.500 1.3749 0.08345 0.07655 -0.0137 0.1165 1.0000
17.750 1.3714 0.08696 0.08010 -0.0142 0.1143 1.0000
18.000 1.3701 0.09027 0.08353 -0.0148 0.1121 1.0000
18.250 1.3676 0.09374 0.08708 -0.0155 0.1097 1.0000
18.500 1.3644 0.09734 0.09074 -0.0164 0.1076 1.0000
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