MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 38 9.68% (mh38-il) Reynolds number: 500,000 Max Cl/Cd: 122.68 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh38-il-500000.txt Download as CSV file: xf-mh38-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3327 0.09413 0.09199 -0.0397 1.0000 0.0143
-9.000 -0.3336 0.09034 0.08824 -0.0408 1.0000 0.0147
-8.750 -0.3315 0.08725 0.08518 -0.0416 1.0000 0.0149
-8.500 -0.3299 0.08441 0.08238 -0.0422 1.0000 0.0152
-8.250 -0.3306 0.08154 0.07957 -0.0426 1.0000 0.0154
-7.000 -0.2965 0.03102 0.02796 -0.0947 0.8765 0.0081
-6.750 -0.2821 0.02727 0.02385 -0.0954 0.8650 0.0075
-6.500 -0.2686 0.02199 0.01781 -0.0960 0.8548 0.0070
-6.250 -0.2481 0.01873 0.01397 -0.0958 0.8461 0.0069
-6.000 -0.2246 0.01644 0.01125 -0.0955 0.8376 0.0069
-5.750 -0.1997 0.01483 0.00929 -0.0951 0.8304 0.0070
-5.500 -0.1737 0.01367 0.00789 -0.0948 0.8226 0.0074
-5.250 -0.1481 0.01230 0.00623 -0.0945 0.8159 0.0085
-5.000 -0.1214 0.01144 0.00523 -0.0943 0.8087 0.0111
-4.750 -0.0943 0.01073 0.00441 -0.0941 0.8024 0.0187
-4.500 -0.0669 0.01039 0.00407 -0.0941 0.7956 0.0313
-4.250 -0.0394 0.01014 0.00375 -0.0940 0.7899 0.0442
-4.000 -0.0117 0.00985 0.00345 -0.0940 0.7833 0.0575
-3.750 0.0159 0.00957 0.00315 -0.0940 0.7777 0.0738
-3.500 0.0437 0.00933 0.00294 -0.0940 0.7715 0.0915
-3.250 0.0715 0.00917 0.00276 -0.0940 0.7658 0.1099
-3.000 0.0994 0.00898 0.00258 -0.0941 0.7602 0.1290
-2.750 0.1273 0.00881 0.00241 -0.0941 0.7543 0.1503
-2.500 0.1551 0.00866 0.00228 -0.0941 0.7492 0.1772
-2.250 0.1831 0.00845 0.00218 -0.0942 0.7432 0.2118
-2.000 0.2108 0.00827 0.00208 -0.0943 0.7380 0.2559
-1.750 0.2386 0.00809 0.00202 -0.0944 0.7325 0.3059
-1.500 0.2663 0.00787 0.00196 -0.0945 0.7269 0.3688
-1.250 0.2938 0.00769 0.00192 -0.0945 0.7220 0.4377
-0.750 0.3483 0.00725 0.00191 -0.0944 0.7109 0.5990
-0.500 0.3743 0.00699 0.00194 -0.0940 0.7056 0.6969
-0.250 0.3976 0.00668 0.00198 -0.0928 0.7000 0.8131
0.000 0.4262 0.00642 0.00193 -0.0923 0.6952 0.9644
0.250 0.4603 0.00642 0.00190 -0.0937 0.6892 1.0000
0.500 0.4882 0.00648 0.00189 -0.0937 0.6837 1.0000
0.750 0.5161 0.00655 0.00190 -0.0937 0.6781 1.0000
1.000 0.5439 0.00661 0.00191 -0.0937 0.6722 1.0000
1.250 0.5718 0.00669 0.00194 -0.0937 0.6668 1.0000
1.500 0.5997 0.00674 0.00197 -0.0937 0.6603 1.0000
1.750 0.6274 0.00684 0.00200 -0.0937 0.6546 1.0000
2.000 0.6552 0.00688 0.00206 -0.0937 0.6477 1.0000
2.250 0.6829 0.00698 0.00211 -0.0936 0.6414 1.0000
2.500 0.7107 0.00703 0.00218 -0.0936 0.6341 1.0000
3.000 0.7659 0.00719 0.00232 -0.0935 0.6193 1.0000
3.250 0.7933 0.00728 0.00241 -0.0935 0.6120 1.0000
3.500 0.8208 0.00736 0.00250 -0.0934 0.6034 1.0000
3.750 0.8482 0.00745 0.00261 -0.0933 0.5949 1.0000
4.000 0.8753 0.00757 0.00270 -0.0932 0.5860 1.0000
4.250 0.9025 0.00766 0.00285 -0.0931 0.5755 1.0000
4.500 0.9295 0.00776 0.00298 -0.0930 0.5643 1.0000
4.750 0.9562 0.00789 0.00312 -0.0928 0.5518 1.0000
5.000 0.9826 0.00803 0.00326 -0.0925 0.5368 1.0000
5.250 1.0084 0.00822 0.00342 -0.0922 0.5184 1.0000
5.500 1.0332 0.00845 0.00360 -0.0917 0.4898 1.0000
5.750 1.0578 0.00875 0.00386 -0.0912 0.4609 1.0000
6.000 1.0814 0.00914 0.00415 -0.0906 0.4267 1.0000
6.250 1.1028 0.00972 0.00453 -0.0896 0.3786 1.0000
6.500 1.1214 0.01056 0.00506 -0.0884 0.3146 1.0000
6.750 1.1373 0.01166 0.00574 -0.0869 0.2368 1.0000
7.000 1.1502 0.01303 0.00660 -0.0850 0.1527 1.0000
7.250 1.1610 0.01453 0.00760 -0.0828 0.0752 1.0000
7.500 1.1731 0.01586 0.00862 -0.0807 0.0288 1.0000
7.750 1.1836 0.01731 0.01002 -0.0780 0.0102 1.0000
8.000 1.1986 0.01826 0.01110 -0.0761 0.0081 1.0000
8.250 1.2072 0.01961 0.01259 -0.0732 0.0070 1.0000
8.500 1.2097 0.02103 0.01415 -0.0694 0.0067 1.0000
8.750 1.2072 0.02275 0.01603 -0.0651 0.0064 1.0000
9.000 1.2103 0.02431 0.01769 -0.0620 0.0063 1.0000
9.250 1.2211 0.02536 0.01883 -0.0601 0.0061 1.0000
9.500 1.2350 0.02618 0.01972 -0.0586 0.0056 1.0000
9.750 1.2445 0.02743 0.02105 -0.0569 0.0052 1.0000
10.000 1.2524 0.02893 0.02265 -0.0550 0.0050 1.0000
10.250 1.2594 0.03067 0.02450 -0.0532 0.0048 1.0000
10.500 1.2673 0.03239 0.02633 -0.0516 0.0047 1.0000
10.750 1.2747 0.03440 0.02847 -0.0499 0.0046 1.0000
11.000 1.2825 0.03637 0.03058 -0.0485 0.0044 1.0000
11.250 1.2894 0.03844 0.03279 -0.0471 0.0043 1.0000
11.500 1.2947 0.04042 0.03489 -0.0460 0.0040 1.0000
11.750 1.2987 0.04287 0.03749 -0.0449 0.0039 1.0000
12.000 1.3001 0.04583 0.04062 -0.0437 0.0037 1.0000
12.250 1.3002 0.04899 0.04398 -0.0426 0.0037 1.0000
12.500 1.2958 0.05282 0.04804 -0.0417 0.0037 1.0000
12.750 1.2903 0.05668 0.05211 -0.0411 0.0037 1.0000
13.000 1.2803 0.06122 0.05690 -0.0409 0.0036 1.0000
13.250 1.2698 0.06590 0.06180 -0.0411 0.0037 1.0000
13.500 1.2593 0.07067 0.06679 -0.0418 0.0037 1.0000
13.750 1.1284 0.08153 0.07818 -0.0428 0.0038 1.0000
14.000 1.1027 0.08996 0.08692 -0.0454 0.0041 1.0000
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Polar data table (+)
Polar graphs
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