MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 32 8.7% (mh32-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.26 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh32-il-1000000.txt Download as CSV file: xf-mh32-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 32 8.7%
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4198 0.08303 0.08146 -0.0290 1.0000 0.0063
-8.250 -0.4210 0.07921 0.07767 -0.0307 1.0000 0.0065
-8.000 -0.4239 0.07554 0.07402 -0.0322 1.0000 0.0065
-7.750 -0.4324 0.07201 0.07054 -0.0332 1.0000 0.0065
-7.500 -0.4479 0.06893 0.06752 -0.0334 1.0000 0.0064
-7.250 -0.4268 0.06021 0.05874 -0.0473 0.9942 0.0066
-7.000 -0.4047 0.05174 0.05014 -0.0580 0.9877 0.0067
-6.750 -0.3796 0.04352 0.04169 -0.0664 0.9835 0.0070
-6.500 -0.3574 0.03723 0.03514 -0.0704 0.9762 0.0073
-6.250 -0.3339 0.03236 0.02998 -0.0724 0.9693 0.0080
-6.000 -0.3097 0.03067 0.02810 -0.0717 0.9610 0.0088
-5.750 -0.2912 0.02807 0.02518 -0.0711 0.9524 0.0089
-5.500 -0.2741 0.02543 0.02222 -0.0700 0.9435 0.0090
-5.000 -0.2446 0.01398 0.00944 -0.0658 0.9268 0.0054
-4.750 -0.2200 0.01261 0.00793 -0.0650 0.9200 0.0046
-4.500 -0.1964 0.01102 0.00609 -0.0638 0.9137 0.0043
-4.250 -0.1717 0.00990 0.00478 -0.0630 0.9065 0.0041
-4.000 -0.1465 0.00914 0.00387 -0.0622 0.9002 0.0041
-3.750 -0.1202 0.00857 0.00318 -0.0617 0.8932 0.0042
-3.500 -0.0937 0.00817 0.00266 -0.0613 0.8870 0.0046
-3.250 -0.0666 0.00774 0.00212 -0.0609 0.8798 0.0066
-3.000 -0.0401 0.00733 0.00179 -0.0605 0.8732 0.0304
-2.750 -0.0131 0.00705 0.00160 -0.0603 0.8656 0.0598
-2.500 0.0133 0.00669 0.00143 -0.0601 0.8585 0.1190
-2.250 0.0395 0.00624 0.00129 -0.0600 0.8502 0.2133
-2.000 0.0658 0.00588 0.00119 -0.0598 0.8419 0.2998
-1.750 0.0923 0.00560 0.00109 -0.0596 0.8330 0.3785
-1.500 0.1188 0.00531 0.00102 -0.0594 0.8223 0.4602
-1.250 0.1453 0.00508 0.00097 -0.0591 0.8109 0.5352
-1.000 0.1717 0.00488 0.00093 -0.0588 0.7992 0.6071
-0.750 0.1977 0.00469 0.00090 -0.0584 0.7866 0.6797
-0.500 0.2236 0.00454 0.00088 -0.0578 0.7728 0.7431
-0.250 0.2490 0.00442 0.00088 -0.0572 0.7575 0.8017
0.000 0.2737 0.00432 0.00089 -0.0563 0.7410 0.8567
0.250 0.2977 0.00426 0.00090 -0.0551 0.7232 0.9097
0.500 0.3274 0.00427 0.00091 -0.0552 0.7031 0.9551
0.750 0.3666 0.00436 0.00090 -0.0577 0.6808 0.9811
1.000 0.4058 0.00447 0.00090 -0.0602 0.6566 0.9944
1.250 0.4391 0.00460 0.00092 -0.0615 0.6319 1.0000
1.500 0.4640 0.00473 0.00096 -0.0609 0.6098 1.0000
1.750 0.4889 0.00489 0.00100 -0.0603 0.5874 1.0000
2.000 0.5143 0.00503 0.00106 -0.0598 0.5649 1.0000
2.250 0.5397 0.00518 0.00112 -0.0593 0.5427 1.0000
2.500 0.5652 0.00535 0.00119 -0.0589 0.5195 1.0000
2.750 0.5910 0.00552 0.00129 -0.0585 0.4955 1.0000
3.000 0.6167 0.00570 0.00138 -0.0581 0.4711 1.0000
3.250 0.6424 0.00591 0.00149 -0.0577 0.4455 1.0000
3.500 0.6681 0.00612 0.00160 -0.0574 0.4196 1.0000
3.750 0.6938 0.00635 0.00175 -0.0570 0.3947 1.0000
4.000 0.7194 0.00659 0.00189 -0.0567 0.3671 1.0000
4.250 0.7448 0.00685 0.00205 -0.0563 0.3390 1.0000
4.500 0.7702 0.00713 0.00222 -0.0559 0.3109 1.0000
4.750 0.7956 0.00741 0.00242 -0.0556 0.2853 1.0000
5.000 0.8201 0.00779 0.00265 -0.0551 0.2493 1.0000
5.250 0.8450 0.00814 0.00288 -0.0547 0.2211 1.0000
5.500 0.8698 0.00848 0.00312 -0.0543 0.1952 1.0000
5.750 0.8947 0.00882 0.00337 -0.0539 0.1715 1.0000
6.000 0.9193 0.00918 0.00365 -0.0535 0.1492 1.0000
6.250 0.9435 0.00959 0.00398 -0.0530 0.1261 1.0000
6.500 0.9675 0.01003 0.00432 -0.0525 0.1030 1.0000
6.750 0.9906 0.01056 0.00471 -0.0519 0.0770 1.0000
7.000 1.0129 0.01117 0.00516 -0.0511 0.0503 1.0000
7.250 1.0351 0.01178 0.00564 -0.0504 0.0306 1.0000
7.500 1.0580 0.01230 0.00610 -0.0498 0.0196 1.0000
7.750 1.0809 0.01281 0.00658 -0.0491 0.0132 1.0000
8.000 1.1027 0.01344 0.00718 -0.0482 0.0057 1.0000
8.250 1.1232 0.01426 0.00808 -0.0471 0.0029 1.0000
8.500 1.1455 0.01479 0.00867 -0.0463 0.0025 1.0000
8.750 1.1667 0.01543 0.00937 -0.0454 0.0021 1.0000
9.000 1.1844 0.01647 0.01055 -0.0438 0.0016 1.0000
9.250 1.2037 0.01725 0.01143 -0.0426 0.0014 1.0000
9.500 1.2220 0.01810 0.01238 -0.0413 0.0013 1.0000
9.750 1.2386 0.01906 0.01347 -0.0397 0.0012 1.0000
10.000 1.2533 0.02014 0.01468 -0.0379 0.0011 1.0000
10.250 1.2664 0.02129 0.01596 -0.0359 0.0010 1.0000
10.500 1.2775 0.02252 0.01733 -0.0337 0.0010 1.0000
10.750 1.2844 0.02384 0.01882 -0.0308 0.0010 1.0000
11.000 1.2865 0.02524 0.02037 -0.0272 0.0010 1.0000
11.250 1.2873 0.02680 0.02209 -0.0238 0.0010 1.0000
11.500 1.2853 0.02867 0.02413 -0.0205 0.0010 1.0000
11.750 1.2817 0.03080 0.02645 -0.0175 0.0010 1.0000
12.000 1.2763 0.03323 0.02907 -0.0149 0.0010 1.0000
12.250 1.2693 0.03599 0.03202 -0.0128 0.0010 1.0000
12.500 1.2587 0.03932 0.03557 -0.0111 0.0010 1.0000
12.750 1.2504 0.04266 0.03909 -0.0102 0.0010 1.0000
13.000 1.2329 0.04747 0.04413 -0.0101 0.0010 1.0000
13.250 1.2156 0.05274 0.04962 -0.0111 0.0010 1.0000
13.500 1.1969 0.05881 0.05590 -0.0132 0.0011 1.0000
13.750 1.1870 0.06399 0.06121 -0.0156 0.0011 1.0000
14.000 1.1635 0.07203 0.06945 -0.0198 0.0011 1.0000
14.250 1.1511 0.07864 0.07620 -0.0237 0.0011 1.0000
14.500 1.1342 0.08663 0.08432 -0.0284 0.0011 1.0000
14.750 1.1154 0.09548 0.09332 -0.0337 0.0011 1.0000
15.000 1.0951 0.10521 0.10318 -0.0394 0.0011 1.0000
15.250 1.0793 0.11420 0.11227 -0.0446 0.0011 1.0000
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Polar data table (+)
Polar graphs
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