MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 32 8.7% (mh32-il) Reynolds number: 500,000 Max Cl/Cd: 94.66 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh32-il-500000.txt Download as CSV file: xf-mh32-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3381 0.09249 0.09035 -0.0256 1.0000 0.0138
-9.250 -0.3370 0.08835 0.08624 -0.0271 1.0000 0.0141
-9.000 -0.3357 0.08414 0.08204 -0.0287 1.0000 0.0145
-8.750 -0.3333 0.08018 0.07810 -0.0305 1.0000 0.0150
-8.500 -0.3322 0.07619 0.07413 -0.0319 1.0000 0.0152
-8.250 -0.3328 0.07193 0.06989 -0.0335 1.0000 0.0153
-8.000 -0.3346 0.06771 0.06570 -0.0350 1.0000 0.0153
-7.750 -0.3388 0.06346 0.06149 -0.0364 1.0000 0.0153
-7.500 -0.3474 0.05960 0.05768 -0.0373 1.0000 0.0153
-7.250 -0.3701 0.05764 0.05579 -0.0345 1.0000 0.0153
-7.000 -0.3728 0.05156 0.04969 -0.0418 0.9963 0.0153
-6.750 -0.3601 0.04316 0.04113 -0.0510 0.9918 0.0154
-6.500 -0.3453 0.03629 0.03404 -0.0572 0.9868 0.0154
-6.250 -0.3253 0.03022 0.02767 -0.0622 0.9835 0.0155
-6.000 -0.3201 0.01948 0.01645 -0.0673 0.9780 0.0168
-5.750 -0.3292 0.03060 0.02713 -0.0669 0.9782 0.0171
-5.500 -0.3001 0.02793 0.02428 -0.0689 0.9746 0.0181
-5.250 -0.2686 0.02510 0.02116 -0.0709 0.9718 0.0194
-5.000 -0.2337 0.01878 0.01382 -0.0704 0.9690 0.0092
-4.750 -0.2095 0.01577 0.01048 -0.0697 0.9627 0.0080
-4.500 -0.1799 0.01378 0.00818 -0.0698 0.9584 0.0075
-4.250 -0.1512 0.01237 0.00658 -0.0696 0.9540 0.0075
-4.000 -0.1267 0.01141 0.00549 -0.0687 0.9469 0.0078
-3.750 -0.0994 0.01069 0.00465 -0.0682 0.9418 0.0087
-3.500 -0.0760 0.00986 0.00369 -0.0671 0.9337 0.0117
-3.250 -0.0507 0.00911 0.00303 -0.0662 0.9278 0.0463
-3.000 -0.0273 0.00847 0.00276 -0.0655 0.9197 0.1328
-2.750 -0.0025 0.00797 0.00253 -0.0650 0.9135 0.2212
-2.250 0.0471 0.00715 0.00223 -0.0638 0.8986 0.3986
-2.000 0.0715 0.00674 0.00212 -0.0631 0.8905 0.5014
-1.750 0.0959 0.00640 0.00204 -0.0623 0.8826 0.5941
-1.500 0.1202 0.00610 0.00196 -0.0613 0.8746 0.6783
-1.250 0.1439 0.00584 0.00193 -0.0601 0.8652 0.7566
-1.000 0.1673 0.00564 0.00189 -0.0587 0.8561 0.8251
-0.750 0.1909 0.00549 0.00183 -0.0572 0.8465 0.8854
-0.500 0.2209 0.00540 0.00177 -0.0571 0.8352 0.9375
-0.250 0.2627 0.00537 0.00168 -0.0599 0.8241 0.9704
0.000 0.3062 0.00535 0.00159 -0.0631 0.8123 0.9892
0.250 0.3449 0.00535 0.00151 -0.0655 0.7989 1.0000
0.500 0.3689 0.00539 0.00146 -0.0646 0.7836 1.0000
0.750 0.3933 0.00544 0.00142 -0.0638 0.7673 1.0000
1.000 0.4178 0.00551 0.00139 -0.0630 0.7493 1.0000
1.250 0.4425 0.00559 0.00139 -0.0623 0.7294 1.0000
1.500 0.4673 0.00570 0.00140 -0.0615 0.7087 1.0000
1.750 0.4921 0.00582 0.00142 -0.0609 0.6859 1.0000
2.000 0.5172 0.00597 0.00146 -0.0602 0.6626 1.0000
2.250 0.5422 0.00613 0.00152 -0.0596 0.6389 1.0000
2.500 0.5672 0.00631 0.00159 -0.0590 0.6148 1.0000
2.750 0.5925 0.00649 0.00170 -0.0585 0.5905 1.0000
3.000 0.6178 0.00668 0.00180 -0.0580 0.5665 1.0000
3.250 0.6431 0.00689 0.00192 -0.0575 0.5416 1.0000
3.500 0.6683 0.00710 0.00205 -0.0570 0.5162 1.0000
3.750 0.6935 0.00734 0.00221 -0.0565 0.4894 1.0000
4.000 0.7185 0.00759 0.00237 -0.0560 0.4611 1.0000
4.250 0.7435 0.00786 0.00255 -0.0555 0.4327 1.0000
4.500 0.7683 0.00815 0.00275 -0.0550 0.4031 1.0000
4.750 0.7929 0.00847 0.00299 -0.0545 0.3730 1.0000
5.250 0.8418 0.00916 0.00349 -0.0535 0.3128 1.0000
5.500 0.8657 0.00958 0.00378 -0.0530 0.2784 1.0000
5.750 0.8892 0.01004 0.00409 -0.0524 0.2432 1.0000
6.000 0.9127 0.01050 0.00443 -0.0518 0.2105 1.0000
6.250 0.9364 0.01095 0.00482 -0.0512 0.1833 1.0000
6.500 0.9598 0.01144 0.00522 -0.0506 0.1568 1.0000
6.750 0.9827 0.01197 0.00565 -0.0500 0.1304 1.0000
7.000 1.0051 0.01254 0.00612 -0.0493 0.1045 1.0000
7.250 1.0268 0.01320 0.00665 -0.0485 0.0781 1.0000
7.500 1.0472 0.01399 0.00726 -0.0475 0.0505 1.0000
7.750 1.0678 0.01474 0.00792 -0.0466 0.0324 1.0000
8.000 1.0883 0.01550 0.00865 -0.0456 0.0219 1.0000
8.250 1.1047 0.01677 0.00997 -0.0438 0.0094 1.0000
8.500 1.1208 0.01800 0.01128 -0.0421 0.0062 1.0000
8.750 1.1405 0.01874 0.01212 -0.0409 0.0052 1.0000
9.000 1.1579 0.01969 0.01318 -0.0394 0.0046 1.0000
9.250 1.1745 0.02066 0.01422 -0.0380 0.0039 1.0000
9.500 1.1826 0.02241 0.01616 -0.0352 0.0035 1.0000
9.750 1.1846 0.02472 0.01869 -0.0318 0.0032 1.0000
10.000 1.1964 0.02583 0.01994 -0.0296 0.0031 1.0000
10.250 1.2035 0.02718 0.02144 -0.0268 0.0029 1.0000
10.500 1.2076 0.02882 0.02325 -0.0239 0.0028 1.0000
10.750 1.2092 0.03078 0.02541 -0.0209 0.0027 1.0000
11.000 1.2097 0.03288 0.02772 -0.0182 0.0026 1.0000
11.250 1.2075 0.03535 0.03041 -0.0157 0.0026 1.0000
11.500 1.2028 0.03812 0.03341 -0.0134 0.0025 1.0000
11.750 1.1952 0.04132 0.03685 -0.0116 0.0026 1.0000
12.000 1.1856 0.04487 0.04063 -0.0103 0.0025 1.0000
12.250 1.1742 0.04882 0.04481 -0.0098 0.0026 1.0000
12.500 1.1605 0.05338 0.04963 -0.0101 0.0026 1.0000
12.750 1.1475 0.05824 0.05469 -0.0114 0.0027 1.0000
13.000 1.1296 0.06432 0.06099 -0.0138 0.0027 1.0000
13.250 1.1131 0.07077 0.06759 -0.0170 0.0027 1.0000
13.500 1.0955 0.07799 0.07500 -0.0211 0.0027 1.0000
13.750 1.0811 0.08516 0.08231 -0.0255 0.0027 1.0000
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Polar data table (+)
Polar graphs
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