CLARK YM-15 AIRFOIL (clarym15-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YM-15 AIRFOIL (clarym15-il) Reynolds number: 200,000 Max Cl/Cd: 66.23 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarym15-il-200000.txt Download as CSV file: xf-clarym15-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3489 0.10303 0.09935 -0.0448 1.0000 0.0893
-10.000 -0.3541 0.10129 0.09768 -0.0428 1.0000 0.0908
-9.750 -0.6121 0.06345 0.05959 -0.0657 0.9930 0.0671
-9.500 -0.5889 0.06075 0.05692 -0.0677 0.9886 0.0677
-9.250 -0.5621 0.05870 0.05488 -0.0704 0.9843 0.0687
-9.000 -0.6043 0.04362 0.03869 -0.0750 0.9715 0.0616
-8.750 -0.6055 0.03674 0.03086 -0.0752 0.9632 0.0603
-8.500 -0.5799 0.03422 0.02805 -0.0764 0.9581 0.0607
-8.250 -0.5466 0.03238 0.02601 -0.0786 0.9552 0.0618
-8.000 -0.5240 0.03080 0.02419 -0.0785 0.9482 0.0629
-7.750 -0.4945 0.02900 0.02209 -0.0796 0.9434 0.0640
-7.500 -0.4591 0.02723 0.01999 -0.0816 0.9405 0.0650
-7.250 -0.4200 0.02578 0.01820 -0.0841 0.9386 0.0662
-7.000 -0.4001 0.02455 0.01686 -0.0828 0.9299 0.0673
-6.750 -0.3628 0.02349 0.01584 -0.0850 0.9267 0.0695
-6.500 -0.3240 0.02262 0.01489 -0.0872 0.9242 0.0722
-6.250 -0.2848 0.02171 0.01382 -0.0893 0.9222 0.0750
-6.000 -0.2656 0.02087 0.01297 -0.0877 0.9128 0.0772
-5.750 -0.2309 0.02007 0.01222 -0.0890 0.9091 0.0809
-5.500 -0.1943 0.01935 0.01140 -0.0905 0.9062 0.0862
-5.250 -0.1736 0.01873 0.01089 -0.0893 0.8977 0.0918
-5.000 -0.1434 0.01797 0.01015 -0.0896 0.8928 0.1007
-4.750 -0.1105 0.01720 0.00942 -0.0904 0.8893 0.1132
-4.500 -0.0891 0.01684 0.00908 -0.0891 0.8805 0.1253
-4.250 -0.0599 0.01628 0.00859 -0.0893 0.8752 0.1406
-4.000 -0.0277 0.01570 0.00808 -0.0899 0.8712 0.1583
-3.750 -0.0065 0.01541 0.00788 -0.0885 0.8609 0.1767
-3.500 0.0241 0.01487 0.00744 -0.0886 0.8554 0.2068
-3.250 0.0474 0.01456 0.00728 -0.0876 0.8460 0.2435
-3.000 0.0758 0.01416 0.00699 -0.0874 0.8392 0.2864
-2.750 0.1008 0.01388 0.00681 -0.0867 0.8308 0.3222
-2.500 0.1276 0.01353 0.00656 -0.0862 0.8230 0.3557
-2.250 0.1535 0.01322 0.00635 -0.0856 0.8150 0.3924
-2.000 0.1787 0.01286 0.00614 -0.0848 0.8058 0.4384
-1.750 0.2028 0.01247 0.00599 -0.0838 0.7971 0.5010
-1.500 0.2255 0.01203 0.00589 -0.0824 0.7883 0.5894
-1.250 0.2479 0.01168 0.00590 -0.0806 0.7809 0.6932
-1.000 0.2711 0.01149 0.00597 -0.0788 0.7721 0.7826
-0.750 0.3008 0.01143 0.00600 -0.0780 0.7649 0.8517
-0.500 0.3336 0.01153 0.00613 -0.0779 0.7552 0.9042
-0.250 0.3769 0.01165 0.00615 -0.0800 0.7475 0.9403
0.000 0.4249 0.01177 0.00618 -0.0836 0.7376 0.9607
0.250 0.4760 0.01179 0.00607 -0.0880 0.7288 0.9737
0.500 0.5258 0.01177 0.00595 -0.0923 0.7182 0.9855
0.750 0.5771 0.01172 0.00581 -0.0972 0.7068 0.9962
1.000 0.6123 0.01167 0.00562 -0.0987 0.6964 1.0000
1.250 0.6332 0.01167 0.00558 -0.0976 0.6841 1.0000
1.500 0.6550 0.01169 0.00553 -0.0965 0.6726 1.0000
1.750 0.6777 0.01172 0.00544 -0.0954 0.6615 1.0000
2.000 0.6985 0.01177 0.00544 -0.0941 0.6484 1.0000
2.250 0.7194 0.01184 0.00545 -0.0927 0.6349 1.0000
2.500 0.7404 0.01192 0.00545 -0.0914 0.6209 1.0000
2.750 0.7611 0.01202 0.00545 -0.0899 0.6058 1.0000
3.000 0.7814 0.01214 0.00548 -0.0883 0.5897 1.0000
3.250 0.8011 0.01229 0.00554 -0.0867 0.5725 1.0000
3.500 0.8204 0.01247 0.00562 -0.0849 0.5542 1.0000
3.750 0.8392 0.01269 0.00574 -0.0831 0.5350 1.0000
4.000 0.8577 0.01295 0.00588 -0.0812 0.5156 1.0000
4.250 0.8760 0.01324 0.00604 -0.0794 0.4970 1.0000
4.500 0.8947 0.01355 0.00624 -0.0776 0.4799 1.0000
4.750 0.9141 0.01387 0.00646 -0.0760 0.4652 1.0000
5.000 0.9341 0.01422 0.00670 -0.0745 0.4524 1.0000
5.250 0.9548 0.01457 0.00695 -0.0732 0.4408 1.0000
5.500 0.9757 0.01488 0.00724 -0.0720 0.4299 1.0000
5.750 0.9976 0.01526 0.00751 -0.0709 0.4207 1.0000
6.000 1.0188 0.01558 0.00782 -0.0697 0.4111 1.0000
6.250 1.0411 0.01596 0.00813 -0.0688 0.4028 1.0000
6.500 1.0619 0.01629 0.00844 -0.0676 0.3934 1.0000
6.750 1.0831 0.01666 0.00878 -0.0665 0.3843 1.0000
7.000 1.1039 0.01702 0.00909 -0.0654 0.3755 1.0000
7.250 1.1262 0.01743 0.00948 -0.0645 0.3684 1.0000
7.500 1.1475 0.01778 0.00986 -0.0635 0.3614 1.0000
7.750 1.1720 0.01828 0.01026 -0.0631 0.3550 1.0000
8.000 1.1915 0.01861 0.01070 -0.0618 0.3483 1.0000
8.250 1.2129 0.01902 0.01110 -0.0608 0.3418 1.0000
8.500 1.2352 0.01949 0.01157 -0.0601 0.3356 1.0000
8.750 1.2539 0.01986 0.01202 -0.0587 0.3288 1.0000
9.000 1.2762 0.02036 0.01244 -0.0580 0.3221 1.0000
9.250 1.2924 0.02075 0.01296 -0.0562 0.3153 1.0000
9.500 1.3092 0.02115 0.01340 -0.0545 0.3085 1.0000
9.750 1.3270 0.02164 0.01389 -0.0531 0.3017 1.0000
10.000 1.3386 0.02204 0.01440 -0.0505 0.2944 1.0000
10.250 1.3552 0.02257 0.01488 -0.0490 0.2871 1.0000
10.500 1.3634 0.02303 0.01551 -0.0461 0.2790 1.0000
10.750 1.3764 0.02361 0.01603 -0.0442 0.2711 1.0000
11.000 1.3837 0.02420 0.01681 -0.0415 0.2619 1.0000
11.250 1.3928 0.02492 0.01754 -0.0392 0.2529 1.0000
11.500 1.3997 0.02572 0.01842 -0.0369 0.2420 1.0000
11.750 1.4063 0.02668 0.01945 -0.0347 0.2299 1.0000
12.000 1.4114 0.02782 0.02061 -0.0325 0.2172 1.0000
12.250 1.4153 0.02917 0.02195 -0.0305 0.2046 1.0000
12.500 1.4176 0.03075 0.02347 -0.0285 0.1929 1.0000
12.750 1.4201 0.03243 0.02513 -0.0267 0.1821 1.0000
13.000 1.4238 0.03414 0.02685 -0.0251 0.1726 1.0000
13.250 1.4250 0.03607 0.02871 -0.0235 0.1651 1.0000
13.500 1.4296 0.03784 0.03055 -0.0222 0.1577 1.0000
13.750 1.4312 0.03985 0.03247 -0.0208 0.1519 1.0000
14.000 1.4363 0.04166 0.03442 -0.0198 0.1462 1.0000
14.250 1.4393 0.04367 0.03641 -0.0187 0.1414 1.0000
14.500 1.4438 0.04558 0.03834 -0.0177 0.1371 1.0000
14.750 1.4484 0.04758 0.04045 -0.0170 0.1331 1.0000
15.000 1.4523 0.04965 0.04256 -0.0163 0.1295 1.0000
15.250 1.4587 0.05141 0.04423 -0.0153 0.1259 1.0000
15.500 1.4613 0.05375 0.04676 -0.0149 0.1230 1.0000
15.750 1.4637 0.05612 0.04925 -0.0146 0.1197 1.0000
16.000 1.4659 0.05852 0.05171 -0.0143 0.1167 1.0000
16.250 1.4728 0.06029 0.05338 -0.0135 0.1134 1.0000
16.500 1.4726 0.06314 0.05643 -0.0136 0.1111 1.0000
16.750 1.4719 0.06609 0.05953 -0.0137 0.1084 1.0000
17.000 1.4712 0.06904 0.06258 -0.0140 0.1056 1.0000
17.250 1.4727 0.07166 0.06520 -0.0140 0.1028 1.0000
17.500 1.4735 0.07444 0.06805 -0.0141 0.1003 1.0000
17.750 1.4691 0.07813 0.07194 -0.0149 0.0980 1.0000
18.000 1.4658 0.08168 0.07562 -0.0157 0.0955 1.0000
18.250 1.4631 0.08515 0.07916 -0.0165 0.0930 1.0000
18.500 1.4660 0.08758 0.08153 -0.0167 0.0901 1.0000
18.750 1.4559 0.09244 0.08664 -0.0184 0.0881 1.0000
19.000 1.4479 0.09702 0.09138 -0.0200 0.0855 1.0000
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