MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 38 9.68% (mh38-il) Reynolds number: 1,000,000 Max Cl/Cd: 149.65 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh38-il-1000000.txt Download as CSV file: xf-mh38-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.3104 0.14522 0.14369 -0.0194 1.0000 0.0062
-13.250 -0.3049 0.14214 0.14061 -0.0209 1.0000 0.0064
-7.250 -0.3437 0.02465 0.02153 -0.0933 0.8239 0.0046
-7.000 -0.3259 0.02154 0.01808 -0.0936 0.8151 0.0041
-6.750 -0.3082 0.01745 0.01337 -0.0937 0.8066 0.0038
-6.500 -0.2853 0.01511 0.01063 -0.0935 0.7990 0.0037
-6.250 -0.2607 0.01345 0.00860 -0.0932 0.7918 0.0036
-6.000 -0.2349 0.01219 0.00710 -0.0930 0.7849 0.0036
-5.750 -0.2085 0.01128 0.00597 -0.0928 0.7783 0.0037
-5.500 -0.1814 0.01055 0.00507 -0.0927 0.7718 0.0038
-5.250 -0.1540 0.00998 0.00435 -0.0926 0.7656 0.0040
-5.000 -0.1263 0.00958 0.00384 -0.0926 0.7597 0.0043
-4.750 -0.0987 0.00892 0.00304 -0.0925 0.7536 0.0073
-4.500 -0.0711 0.00847 0.00260 -0.0925 0.7481 0.0191
-4.250 -0.0430 0.00825 0.00236 -0.0925 0.7423 0.0272
-4.000 -0.0152 0.00808 0.00217 -0.0926 0.7368 0.0361
-3.750 0.0130 0.00787 0.00200 -0.0927 0.7313 0.0493
-3.500 0.0409 0.00768 0.00186 -0.0928 0.7257 0.0677
-3.250 0.0690 0.00754 0.00174 -0.0928 0.7206 0.0841
-3.000 0.0973 0.00738 0.00161 -0.0929 0.7151 0.1012
-2.750 0.1254 0.00727 0.00149 -0.0930 0.7099 0.1188
-2.500 0.1537 0.00714 0.00140 -0.0931 0.7047 0.1362
-2.250 0.1820 0.00703 0.00131 -0.0932 0.6994 0.1562
-2.000 0.2101 0.00692 0.00124 -0.0933 0.6944 0.1827
-1.750 0.2384 0.00676 0.00118 -0.0935 0.6892 0.2184
-1.500 0.2664 0.00663 0.00112 -0.0936 0.6840 0.2567
-1.250 0.2946 0.00651 0.00109 -0.0937 0.6790 0.2968
-1.000 0.3228 0.00635 0.00106 -0.0939 0.6736 0.3501
-0.750 0.3507 0.00623 0.00104 -0.0940 0.6686 0.4034
-0.500 0.3789 0.00607 0.00104 -0.0941 0.6634 0.4628
-0.250 0.4067 0.00591 0.00105 -0.0942 0.6580 0.5325
0.000 0.4344 0.00576 0.00108 -0.0942 0.6529 0.6071
0.250 0.4618 0.00556 0.00111 -0.0942 0.6473 0.6896
0.500 0.4879 0.00536 0.00115 -0.0938 0.6419 0.7866
0.750 0.5088 0.00505 0.00121 -0.0919 0.6366 0.9173
1.000 0.5451 0.00499 0.00117 -0.0937 0.6304 1.0000
1.250 0.5732 0.00505 0.00120 -0.0937 0.6246 1.0000
1.500 0.6014 0.00511 0.00122 -0.0938 0.6180 1.0000
1.750 0.6294 0.00518 0.00125 -0.0938 0.6117 1.0000
2.000 0.6575 0.00523 0.00129 -0.0939 0.6046 1.0000
2.250 0.6854 0.00531 0.00134 -0.0939 0.5978 1.0000
2.500 0.7135 0.00538 0.00139 -0.0940 0.5902 1.0000
2.750 0.7414 0.00545 0.00145 -0.0940 0.5828 1.0000
3.000 0.7692 0.00554 0.00152 -0.0940 0.5745 1.0000
3.250 0.7971 0.00562 0.00160 -0.0941 0.5660 1.0000
3.500 0.8247 0.00572 0.00168 -0.0941 0.5568 1.0000
3.750 0.8521 0.00583 0.00177 -0.0940 0.5462 1.0000
4.000 0.8797 0.00594 0.00187 -0.0940 0.5346 1.0000
4.250 0.9069 0.00607 0.00199 -0.0940 0.5213 1.0000
4.500 0.9338 0.00624 0.00212 -0.0939 0.5053 1.0000
4.750 0.9605 0.00642 0.00226 -0.0937 0.4849 1.0000
5.000 0.9858 0.00673 0.00244 -0.0934 0.4522 1.0000
5.250 1.0109 0.00706 0.00266 -0.0930 0.4200 1.0000
5.500 1.0356 0.00743 0.00291 -0.0927 0.3868 1.0000
5.750 1.0586 0.00799 0.00326 -0.0920 0.3386 1.0000
6.000 1.0789 0.00880 0.00373 -0.0911 0.2702 1.0000
6.250 1.0966 0.00985 0.00434 -0.0898 0.1893 1.0000
6.500 1.1150 0.01081 0.00495 -0.0886 0.1270 1.0000
6.750 1.1334 0.01172 0.00558 -0.0874 0.0763 1.0000
7.500 1.1888 0.01430 0.00777 -0.0834 0.0050 1.0000
7.750 1.2078 0.01505 0.00860 -0.0820 0.0037 1.0000
8.000 1.2258 0.01583 0.00949 -0.0805 0.0033 1.0000
8.250 1.2451 0.01644 0.01016 -0.0793 0.0031 1.0000
8.500 1.2628 0.01713 0.01093 -0.0779 0.0030 1.0000
8.750 1.2788 0.01790 0.01178 -0.0761 0.0028 1.0000
9.000 1.2921 0.01876 0.01273 -0.0740 0.0027 1.0000
9.250 1.3021 0.01957 0.01361 -0.0713 0.0026 1.0000
9.500 1.3112 0.02041 0.01452 -0.0686 0.0025 1.0000
9.750 1.3191 0.02137 0.01555 -0.0659 0.0024 1.0000
10.000 1.3272 0.02238 0.01664 -0.0635 0.0023 1.0000
10.250 1.3352 0.02348 0.01782 -0.0613 0.0022 1.0000
10.500 1.3443 0.02456 0.01897 -0.0594 0.0020 1.0000
10.750 1.3481 0.02613 0.02065 -0.0571 0.0020 1.0000
11.000 1.3516 0.02783 0.02244 -0.0550 0.0019 1.0000
11.250 1.3473 0.03040 0.02516 -0.0525 0.0018 1.0000
11.500 1.3384 0.03380 0.02880 -0.0498 0.0016 1.0000
11.750 1.3450 0.03557 0.03067 -0.0486 0.0015 1.0000
12.000 1.3493 0.03765 0.03288 -0.0473 0.0015 1.0000
12.250 1.3505 0.04018 0.03556 -0.0461 0.0015 1.0000
12.500 1.3507 0.04293 0.03847 -0.0450 0.0014 1.0000
12.750 1.3491 0.04595 0.04166 -0.0441 0.0014 1.0000
13.000 1.3449 0.04943 0.04533 -0.0433 0.0014 1.0000
13.250 1.3371 0.05350 0.04960 -0.0428 0.0014 1.0000
13.500 1.3297 0.05757 0.05386 -0.0428 0.0014 1.0000
13.750 1.3189 0.06229 0.05877 -0.0431 0.0014 1.0000
14.000 1.3036 0.06802 0.06472 -0.0441 0.0014 1.0000
14.250 1.2897 0.07375 0.07064 -0.0456 0.0014 1.0000
14.500 1.2735 0.08025 0.07733 -0.0478 0.0014 1.0000
14.750 1.2543 0.08772 0.08500 -0.0508 0.0014 1.0000
15.000 1.2378 0.09514 0.09260 -0.0543 0.0014 1.0000
15.250 1.2191 0.10351 0.10114 -0.0586 0.0015 1.0000
15.500 1.1999 0.11253 0.11033 -0.0637 0.0015 1.0000
15.750 1.1810 0.12204 0.12000 -0.0692 0.0015 1.0000
16.000 1.1612 0.13248 0.13059 -0.0756 0.0015 1.0000
16.250 1.1431 0.14297 0.14120 -0.0821 0.0015 1.0000
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Polar data table (+)
Polar graphs
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