CLARK YM-15 AIRFOIL (clarym15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YM-15 AIRFOIL (clarym15-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.5 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarym15-il-1000000.txt Download as CSV file: xf-clarym15-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK YM-15 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.8865 0.07769 0.07500 -0.0690 1.0000 0.0248
-16.500 -0.9277 0.06722 0.06435 -0.0762 1.0000 0.0248
-16.250 -0.9547 0.05906 0.05602 -0.0822 1.0000 0.0249
-16.000 -0.9731 0.05228 0.04909 -0.0875 1.0000 0.0249
-15.750 -0.9847 0.04671 0.04337 -0.0921 1.0000 0.0250
-15.500 -0.9916 0.04223 0.03875 -0.0956 1.0000 0.0252
-15.250 -0.9958 0.03861 0.03501 -0.0981 1.0000 0.0253
-15.000 -0.9980 0.03581 0.03208 -0.0994 1.0000 0.0255
-14.750 -1.0001 0.03361 0.02978 -0.0994 1.0000 0.0256
-14.500 -1.0051 0.03194 0.02801 -0.0977 1.0000 0.0258
-14.250 -1.0167 0.03078 0.02677 -0.0939 1.0000 0.0259
-14.000 -1.0371 0.03001 0.02593 -0.0877 0.9998 0.0259
-13.750 -1.0174 0.02879 0.02460 -0.0885 0.9971 0.0261
-13.500 -0.9925 0.02775 0.02345 -0.0899 0.9948 0.0262
-13.250 -0.9769 0.02504 0.02058 -0.0909 0.9925 0.0267
-13.000 -0.9552 0.02376 0.01924 -0.0914 0.9892 0.0270
-12.750 -0.9284 0.02281 0.01826 -0.0924 0.9868 0.0273
-12.500 -0.8992 0.02201 0.01742 -0.0938 0.9850 0.0277
-12.250 -0.8692 0.02126 0.01661 -0.0951 0.9834 0.0280
-12.000 -0.8398 0.02047 0.01576 -0.0963 0.9816 0.0284
-11.750 -0.8171 0.01977 0.01500 -0.0959 0.9761 0.0287
-11.500 -0.7915 0.01907 0.01424 -0.0961 0.9718 0.0290
-11.250 -0.7657 0.01842 0.01351 -0.0962 0.9678 0.0293
-11.000 -0.7450 0.01786 0.01289 -0.0951 0.9605 0.0296
-10.750 -0.7214 0.01732 0.01228 -0.0946 0.9550 0.0298
-10.500 -0.6990 0.01688 0.01178 -0.0937 0.9478 0.0301
-10.250 -0.6752 0.01653 0.01136 -0.0930 0.9411 0.0303
-10.000 -0.6569 0.01545 0.01020 -0.0917 0.9334 0.0309
-9.750 -0.6350 0.01482 0.00952 -0.0908 0.9257 0.0313
-9.500 -0.6115 0.01434 0.00899 -0.0901 0.9183 0.0317
-9.250 -0.5874 0.01392 0.00853 -0.0895 0.9103 0.0321
-9.000 -0.5626 0.01353 0.00809 -0.0890 0.9030 0.0325
-8.750 -0.5377 0.01316 0.00767 -0.0885 0.8948 0.0329
-8.500 -0.5123 0.01282 0.00726 -0.0880 0.8875 0.0334
-8.250 -0.4866 0.01249 0.00688 -0.0876 0.8795 0.0338
-8.000 -0.4608 0.01220 0.00651 -0.0872 0.8720 0.0343
-7.750 -0.4343 0.01194 0.00621 -0.0869 0.8644 0.0347
-7.500 -0.4093 0.01152 0.00572 -0.0864 0.8567 0.0354
-7.250 -0.3837 0.01114 0.00531 -0.0860 0.8495 0.0362
-7.000 -0.3573 0.01086 0.00499 -0.0857 0.8418 0.0370
-6.750 -0.3306 0.01063 0.00471 -0.0854 0.8346 0.0378
-6.500 -0.3037 0.01041 0.00445 -0.0851 0.8266 0.0386
-6.250 -0.2768 0.01024 0.00421 -0.0848 0.8187 0.0394
-6.000 -0.2501 0.00997 0.00392 -0.0846 0.8102 0.0407
-5.750 -0.2235 0.00976 0.00366 -0.0842 0.8016 0.0424
-5.500 -0.1961 0.00956 0.00346 -0.0840 0.7938 0.0444
-5.250 -0.1691 0.00937 0.00324 -0.0838 0.7865 0.0475
-5.000 -0.1419 0.00917 0.00305 -0.0836 0.7790 0.0528
-4.750 -0.1151 0.00897 0.00288 -0.0833 0.7704 0.0629
-4.500 -0.0878 0.00881 0.00275 -0.0831 0.7626 0.0735
-4.250 -0.0603 0.00868 0.00263 -0.0830 0.7549 0.0816
-4.000 -0.0326 0.00860 0.00252 -0.0828 0.7477 0.0876
-3.750 -0.0050 0.00846 0.00241 -0.0827 0.7392 0.0947
-3.500 0.0223 0.00838 0.00230 -0.0825 0.7306 0.1014
-3.250 0.0499 0.00827 0.00219 -0.0823 0.7215 0.1095
-3.000 0.0770 0.00815 0.00209 -0.0821 0.7126 0.1221
-2.750 0.1040 0.00798 0.00199 -0.0819 0.7036 0.1439
-2.500 0.1306 0.00781 0.00191 -0.0816 0.6954 0.1769
-2.250 0.1581 0.00768 0.00186 -0.0815 0.6870 0.2049
-2.000 0.1850 0.00758 0.00181 -0.0813 0.6785 0.2309
-1.750 0.2127 0.00750 0.00178 -0.0812 0.6692 0.2533
-1.500 0.2397 0.00743 0.00174 -0.0810 0.6598 0.2770
-1.250 0.2670 0.00736 0.00172 -0.0808 0.6497 0.3003
-1.000 0.2942 0.00729 0.00169 -0.0806 0.6404 0.3267
-0.750 0.3210 0.00721 0.00168 -0.0803 0.6302 0.3582
-0.250 0.3737 0.00697 0.00167 -0.0797 0.6099 0.4572
0.000 0.3998 0.00681 0.00168 -0.0794 0.5991 0.5204
0.250 0.4252 0.00666 0.00170 -0.0789 0.5885 0.5909
0.750 0.4737 0.00634 0.00180 -0.0772 0.5645 0.7552
1.000 0.4978 0.00627 0.00188 -0.0763 0.5520 0.8162
1.250 0.5219 0.00628 0.00197 -0.0752 0.5393 0.8673
1.500 0.5463 0.00634 0.00208 -0.0742 0.5259 0.9080
1.750 0.5720 0.00644 0.00217 -0.0735 0.5121 0.9334
2.000 0.5985 0.00659 0.00226 -0.0731 0.4969 0.9512
2.250 0.6278 0.00676 0.00237 -0.0733 0.4794 0.9633
2.500 0.6584 0.00698 0.00248 -0.0739 0.4584 0.9720
2.750 0.6878 0.00723 0.00261 -0.0742 0.4336 0.9810
3.000 0.7235 0.00755 0.00277 -0.0761 0.4039 0.9851
3.250 0.7584 0.00785 0.00293 -0.0778 0.3802 0.9889
3.500 0.7922 0.00811 0.00309 -0.0792 0.3638 0.9930
3.750 0.8307 0.00835 0.00325 -0.0817 0.3512 0.9955
4.000 0.8709 0.00860 0.00341 -0.0845 0.3402 0.9987
4.250 0.9017 0.00877 0.00354 -0.0853 0.3321 1.0000
4.500 0.9202 0.00896 0.00367 -0.0835 0.3240 1.0000
4.750 0.9402 0.00909 0.00379 -0.0819 0.3177 1.0000
5.000 0.9602 0.00924 0.00390 -0.0804 0.3117 1.0000
5.250 0.9793 0.00943 0.00405 -0.0787 0.3058 1.0000
5.500 1.0008 0.00955 0.00417 -0.0774 0.3023 1.0000
5.750 1.0225 0.00967 0.00430 -0.0762 0.2989 1.0000
6.000 1.0441 0.00982 0.00444 -0.0750 0.2952 1.0000
6.250 1.0655 0.01001 0.00460 -0.0738 0.2910 1.0000
6.500 1.0876 0.01020 0.00478 -0.0727 0.2868 1.0000
6.750 1.1117 0.01031 0.00492 -0.0720 0.2836 1.0000
7.000 1.1353 0.01047 0.00508 -0.0713 0.2798 1.0000
7.250 1.1580 0.01067 0.00526 -0.0704 0.2756 1.0000
7.500 1.1800 0.01091 0.00548 -0.0694 0.2707 1.0000
7.750 1.2046 0.01103 0.00564 -0.0689 0.2671 1.0000
8.000 1.2275 0.01121 0.00582 -0.0680 0.2624 1.0000
8.250 1.2482 0.01146 0.00604 -0.0668 0.2571 1.0000
8.500 1.2701 0.01165 0.00625 -0.0658 0.2526 1.0000
8.750 1.2921 0.01186 0.00646 -0.0649 0.2465 1.0000
9.000 1.3119 0.01217 0.00674 -0.0636 0.2382 1.0000
9.250 1.3327 0.01245 0.00700 -0.0626 0.2283 1.0000
9.500 1.3520 0.01281 0.00732 -0.0613 0.2164 1.0000
9.750 1.3694 0.01327 0.00770 -0.0598 0.2019 1.0000
10.000 1.3844 0.01387 0.00820 -0.0580 0.1844 1.0000
10.250 1.3971 0.01460 0.00882 -0.0559 0.1667 1.0000
10.500 1.4100 0.01533 0.00947 -0.0539 0.1513 1.0000
10.750 1.4230 0.01609 0.01015 -0.0520 0.1382 1.0000
11.000 1.4364 0.01684 0.01085 -0.0502 0.1273 1.0000
11.250 1.4509 0.01753 0.01153 -0.0487 0.1191 1.0000
11.500 1.4646 0.01830 0.01227 -0.0471 0.1118 1.0000
11.750 1.4787 0.01906 0.01302 -0.0456 0.1059 1.0000
12.000 1.4919 0.01989 0.01384 -0.0441 0.1002 1.0000
12.250 1.5062 0.02067 0.01463 -0.0428 0.0961 1.0000
12.500 1.5181 0.02163 0.01558 -0.0413 0.0917 1.0000
12.750 1.5322 0.02246 0.01644 -0.0401 0.0889 1.0000
13.000 1.5458 0.02333 0.01734 -0.0390 0.0861 1.0000
13.250 1.5572 0.02439 0.01841 -0.0376 0.0832 1.0000
13.500 1.5672 0.02557 0.01961 -0.0363 0.0799 1.0000
13.750 1.5811 0.02649 0.02057 -0.0354 0.0781 1.0000
14.000 1.5923 0.02763 0.02174 -0.0343 0.0756 1.0000
14.250 1.6014 0.02895 0.02308 -0.0331 0.0730 1.0000
14.500 1.6097 0.03037 0.02453 -0.0320 0.0704 1.0000
14.750 1.6212 0.03155 0.02577 -0.0311 0.0686 1.0000
15.000 1.6298 0.03300 0.02726 -0.0302 0.0662 1.0000
15.250 1.6355 0.03474 0.02902 -0.0292 0.0633 1.0000
15.500 1.6430 0.03637 0.03069 -0.0283 0.0606 1.0000
15.750 1.6483 0.03824 0.03258 -0.0275 0.0571 1.0000
16.000 1.6511 0.04038 0.03474 -0.0267 0.0534 1.0000
16.250 1.6505 0.04292 0.03729 -0.0259 0.0482 1.0000
16.500 1.6468 0.04587 0.04024 -0.0252 0.0420 1.0000
16.750 1.6359 0.04966 0.04402 -0.0246 0.0337 1.0000
17.000 1.6179 0.05440 0.04875 -0.0242 0.0252 1.0000
17.250 1.6020 0.05912 0.05351 -0.0241 0.0208 1.0000
17.500 1.5917 0.06330 0.05776 -0.0242 0.0190 1.0000
17.750 1.5805 0.06771 0.06225 -0.0246 0.0178 1.0000
18.000 1.5716 0.07195 0.06658 -0.0251 0.0170 1.0000
18.250 1.5620 0.07635 0.07108 -0.0258 0.0164 1.0000
18.500 1.5507 0.08103 0.07585 -0.0266 0.0159 1.0000
18.750 1.5383 0.08596 0.08088 -0.0276 0.0156 1.0000
19.000 1.5248 0.09114 0.08616 -0.0288 0.0152 1.0000
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