MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 38 9.68% (mh38-il) Reynolds number: 1,000,000 Max Cl/Cd: 133.92 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh38-il-1000000-n5.txt Download as CSV file: xf-mh38-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 38 9.68%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2664 0.10250 0.10061 -0.0396 0.8742 0.0021
-10.750 -0.2666 0.09763 0.09570 -0.0412 0.8613 0.0021
-10.500 -0.3711 0.10759 0.10599 -0.0282 0.9887 0.0021
-10.250 -0.3527 0.10082 0.09919 -0.0361 0.9668 0.0020
-10.000 -0.3331 0.09327 0.09161 -0.0455 0.9520 0.0020
-9.000 -0.4989 0.03363 0.03125 -0.0875 0.8146 0.0016
-8.750 -0.4996 0.02616 0.02317 -0.0908 0.8035 0.0016
-8.500 -0.4867 0.02222 0.01871 -0.0917 0.7943 0.0015
-8.250 -0.4684 0.01949 0.01556 -0.0919 0.7865 0.0015
-8.000 -0.4467 0.01762 0.01336 -0.0919 0.7788 0.0015
-7.750 -0.4233 0.01611 0.01156 -0.0919 0.7719 0.0016
-7.500 -0.3988 0.01491 0.01011 -0.0918 0.7651 0.0016
-7.250 -0.3735 0.01386 0.00884 -0.0918 0.7587 0.0016
-7.000 -0.3476 0.01302 0.00781 -0.0917 0.7523 0.0016
-6.750 -0.3212 0.01228 0.00690 -0.0916 0.7466 0.0017
-6.500 -0.2943 0.01167 0.00614 -0.0916 0.7405 0.0017
-6.250 -0.2673 0.01113 0.00546 -0.0916 0.7349 0.0018
-6.000 -0.2399 0.01065 0.00484 -0.0916 0.7291 0.0018
-5.750 -0.2125 0.01026 0.00433 -0.0916 0.7236 0.0019
-5.500 -0.1847 0.00992 0.00390 -0.0916 0.7184 0.0021
-5.250 -0.1569 0.00960 0.00351 -0.0916 0.7129 0.0023
-5.000 -0.1292 0.00928 0.00311 -0.0916 0.7081 0.0032
-4.750 -0.1012 0.00903 0.00282 -0.0916 0.7029 0.0044
-4.500 -0.0733 0.00879 0.00255 -0.0917 0.6977 0.0072
-4.250 -0.0453 0.00856 0.00230 -0.0917 0.6930 0.0116
-4.000 -0.0173 0.00834 0.00209 -0.0918 0.6878 0.0186
-3.750 0.0107 0.00817 0.00191 -0.0919 0.6827 0.0270
-3.500 0.0388 0.00794 0.00174 -0.0920 0.6780 0.0428
-3.250 0.0669 0.00777 0.00160 -0.0921 0.6728 0.0577
-3.000 0.0950 0.00765 0.00148 -0.0922 0.6680 0.0703
-2.750 0.1234 0.00752 0.00136 -0.0923 0.6631 0.0833
-2.500 0.1517 0.00742 0.00127 -0.0924 0.6578 0.0947
-2.250 0.1799 0.00734 0.00118 -0.0925 0.6530 0.1065
-2.000 0.2083 0.00724 0.00111 -0.0926 0.6479 0.1220
-1.750 0.2365 0.00715 0.00105 -0.0927 0.6427 0.1422
-1.500 0.2648 0.00706 0.00099 -0.0928 0.6377 0.1620
-1.250 0.2931 0.00699 0.00094 -0.0930 0.6323 0.1799
-0.750 0.3496 0.00682 0.00088 -0.0932 0.6218 0.2338
-0.500 0.3778 0.00674 0.00086 -0.0933 0.6161 0.2635
-0.250 0.4059 0.00665 0.00086 -0.0935 0.6108 0.3020
0.000 0.4341 0.00656 0.00086 -0.0936 0.6047 0.3425
0.250 0.4621 0.00649 0.00087 -0.0937 0.5990 0.3840
0.500 0.4903 0.00640 0.00089 -0.0938 0.5927 0.4279
0.750 0.5181 0.00633 0.00092 -0.0939 0.5863 0.4800
1.000 0.5462 0.00623 0.00097 -0.0940 0.5793 0.5337
1.250 0.5738 0.00616 0.00102 -0.0941 0.5722 0.5891
1.500 0.6014 0.00604 0.00108 -0.0941 0.5641 0.6594
1.750 0.6282 0.00591 0.00115 -0.0940 0.5561 0.7431
2.000 0.6528 0.00572 0.00124 -0.0932 0.5470 0.8472
2.250 0.6820 0.00553 0.00128 -0.0933 0.5375 1.0000
2.500 0.7097 0.00563 0.00134 -0.0933 0.5276 1.0000
2.750 0.7373 0.00574 0.00141 -0.0933 0.5169 1.0000
3.000 0.7648 0.00587 0.00149 -0.0933 0.5050 1.0000
3.250 0.7922 0.00600 0.00159 -0.0932 0.4920 1.0000
3.500 0.8194 0.00615 0.00170 -0.0932 0.4773 1.0000
3.750 0.8464 0.00632 0.00182 -0.0931 0.4608 1.0000
4.000 0.8731 0.00652 0.00196 -0.0930 0.4415 1.0000
4.250 0.8994 0.00676 0.00213 -0.0928 0.4200 1.0000
4.500 0.9252 0.00705 0.00232 -0.0926 0.3939 1.0000
4.750 0.9503 0.00741 0.00255 -0.0923 0.3611 1.0000
5.000 0.9737 0.00795 0.00286 -0.0917 0.3136 1.0000
5.250 0.9963 0.00856 0.00322 -0.0911 0.2611 1.0000
5.500 1.0203 0.00901 0.00353 -0.0906 0.2289 1.0000
5.750 1.0422 0.00966 0.00397 -0.0899 0.1817 1.0000
6.000 1.0619 0.01052 0.00451 -0.0889 0.1226 1.0000
6.250 1.0798 0.01153 0.00517 -0.0876 0.0618 1.0000
6.500 1.1003 0.01224 0.00571 -0.0867 0.0311 1.0000
6.750 1.1229 0.01273 0.00613 -0.0860 0.0193 1.0000
7.000 1.1454 0.01320 0.00657 -0.0853 0.0114 1.0000
7.250 1.1674 0.01370 0.00705 -0.0845 0.0058 1.0000
7.500 1.1890 0.01422 0.00757 -0.0836 0.0033 1.0000
7.750 1.2109 0.01469 0.00809 -0.0828 0.0025 1.0000
8.000 1.2316 0.01522 0.00866 -0.0819 0.0019 1.0000
8.250 1.2513 0.01582 0.00932 -0.0807 0.0016 1.0000
8.500 1.2721 0.01628 0.00982 -0.0798 0.0015 1.0000
8.750 1.2913 0.01683 0.01042 -0.0786 0.0014 1.0000
9.000 1.3091 0.01744 0.01109 -0.0772 0.0013 1.0000
9.250 1.3261 0.01806 0.01177 -0.0757 0.0012 1.0000
9.500 1.3403 0.01871 0.01248 -0.0737 0.0012 1.0000
9.750 1.3518 0.01939 0.01322 -0.0713 0.0011 1.0000
10.000 1.3622 0.02014 0.01405 -0.0689 0.0011 1.0000
10.250 1.3725 0.02095 0.01495 -0.0666 0.0010 1.0000
10.500 1.3828 0.02180 0.01587 -0.0645 0.0010 1.0000
10.750 1.3907 0.02288 0.01703 -0.0622 0.0010 1.0000
11.000 1.3992 0.02396 0.01820 -0.0602 0.0009 1.0000
11.250 1.4073 0.02515 0.01946 -0.0584 0.0009 1.0000
11.500 1.4161 0.02634 0.02072 -0.0568 0.0008 1.0000
11.750 1.4235 0.02770 0.02216 -0.0552 0.0008 1.0000
12.000 1.4295 0.02925 0.02380 -0.0536 0.0008 1.0000
12.250 1.4336 0.03103 0.02568 -0.0521 0.0008 1.0000
12.500 1.4359 0.03305 0.02782 -0.0506 0.0007 1.0000
12.750 1.4382 0.03517 0.03004 -0.0494 0.0007 1.0000
13.000 1.4287 0.03859 0.03366 -0.0478 0.0006 1.0000
13.250 1.4277 0.04128 0.03647 -0.0469 0.0006 1.0000
13.500 1.4306 0.04361 0.03890 -0.0463 0.0006 1.0000
13.750 1.4331 0.04605 0.04146 -0.0458 0.0006 1.0000
14.000 1.4375 0.04835 0.04386 -0.0456 0.0006 1.0000
14.250 1.4339 0.05170 0.04735 -0.0454 0.0006 1.0000
14.500 1.4310 0.05510 0.05088 -0.0455 0.0006 1.0000
14.750 1.4338 0.05789 0.05376 -0.0458 0.0005 1.0000
15.000 1.4278 0.06201 0.05802 -0.0463 0.0005 1.0000
15.250 1.4220 0.06629 0.06244 -0.0472 0.0005 1.0000
15.500 1.4203 0.07012 0.06639 -0.0482 0.0005 1.0000
15.750 1.4136 0.07490 0.07130 -0.0496 0.0005 1.0000
16.000 1.4083 0.07962 0.07615 -0.0512 0.0005 1.0000
16.250 1.3962 0.08573 0.08242 -0.0535 0.0005 1.0000
16.500 1.3840 0.09212 0.08896 -0.0562 0.0005 1.0000
16.750 1.3740 0.09834 0.09532 -0.0590 0.0005 1.0000
17.000 1.3613 0.10531 0.10244 -0.0624 0.0005 1.0000
17.250 1.3459 0.11313 0.11042 -0.0664 0.0005 1.0000
17.500 1.3312 0.12101 0.11845 -0.0707 0.0005 1.0000
17.750 1.3166 0.12916 0.12674 -0.0752 0.0005 1.0000
18.000 1.2991 0.13828 0.13600 -0.0805 0.0005 1.0000
18.250 1.2821 0.14755 0.14542 -0.0860 0.0005 1.0000
18.500 1.2652 0.15707 0.15506 -0.0918 0.0005 1.0000
18.750 1.2468 0.16740 0.16553 -0.0981 0.0005 1.0000
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