MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 32 8.7% (mh32-il) Reynolds number: 200,000 Max Cl/Cd: 67.16 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh32-il-200000-n5.txt Download as CSV file: xf-mh32-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3434 0.09723 0.09384 -0.0245 1.0000 0.0113
-9.500 -0.4215 0.10167 0.09802 -0.0224 1.0000 0.0126
-9.250 -0.4195 0.09783 0.09421 -0.0239 1.0000 0.0116
-8.750 -0.4206 0.08777 0.08423 -0.0283 1.0000 0.0085
-8.500 -0.4206 0.08417 0.08067 -0.0297 1.0000 0.0083
-8.250 -0.4227 0.08019 0.07675 -0.0314 1.0000 0.0081
-8.000 -0.4257 0.07653 0.07315 -0.0330 1.0000 0.0080
-7.750 -0.4333 0.07282 0.06952 -0.0343 1.0000 0.0078
-7.500 -0.4415 0.06893 0.06570 -0.0365 1.0000 0.0077
-7.250 -0.4487 0.06421 0.06101 -0.0394 1.0000 0.0076
-7.000 -0.4553 0.06005 0.05683 -0.0405 1.0000 0.0074
-6.750 -0.4624 0.05561 0.05233 -0.0408 1.0000 0.0073
-6.500 -0.4398 0.04751 0.04394 -0.0485 0.9932 0.0070
-6.250 -0.4176 0.03991 0.03590 -0.0535 0.9862 0.0066
-6.000 -0.3918 0.03270 0.02805 -0.0571 0.9810 0.0063
-5.750 -0.3672 0.02734 0.02197 -0.0584 0.9746 0.0060
-5.500 -0.3365 0.02366 0.01764 -0.0599 0.9706 0.0060
-5.250 -0.3056 0.02110 0.01460 -0.0608 0.9666 0.0062
-5.000 -0.2764 0.01920 0.01234 -0.0612 0.9613 0.0065
-4.750 -0.2443 0.01763 0.01050 -0.0621 0.9575 0.0069
-4.500 -0.2135 0.01635 0.00901 -0.0626 0.9531 0.0075
-4.250 -0.1845 0.01557 0.00804 -0.0628 0.9472 0.0090
-4.000 -0.1534 0.01468 0.00711 -0.0638 0.9430 0.0127
-3.750 -0.1255 0.01391 0.00620 -0.0636 0.9366 0.0156
-3.500 -0.0962 0.01308 0.00528 -0.0638 0.9309 0.0263
-3.250 -0.0682 0.01232 0.00465 -0.0639 0.9247 0.0615
-3.000 -0.0410 0.01167 0.00426 -0.0640 0.9178 0.1283
-2.500 0.0124 0.01060 0.00374 -0.0638 0.9033 0.3022
-2.250 0.0377 0.01015 0.00356 -0.0634 0.8951 0.3934
-2.000 0.0637 0.00972 0.00341 -0.0629 0.8877 0.4876
-1.750 0.0873 0.00936 0.00332 -0.0618 0.8782 0.5774
-1.500 0.1115 0.00904 0.00321 -0.0607 0.8697 0.6606
-1.250 0.1355 0.00877 0.00314 -0.0593 0.8610 0.7377
-1.000 0.1592 0.00857 0.00309 -0.0578 0.8509 0.8082
-0.750 0.1877 0.00843 0.00301 -0.0572 0.8414 0.8733
-0.500 0.2267 0.00832 0.00286 -0.0590 0.8325 0.9289
-0.250 0.2691 0.00825 0.00272 -0.0618 0.8213 0.9690
0.000 0.3109 0.00820 0.00257 -0.0647 0.8086 0.9980
0.250 0.3366 0.00822 0.00248 -0.0642 0.7937 1.0000
0.500 0.3608 0.00825 0.00240 -0.0633 0.7775 1.0000
0.750 0.3854 0.00829 0.00235 -0.0625 0.7599 1.0000
1.000 0.4102 0.00835 0.00231 -0.0617 0.7417 1.0000
1.250 0.4351 0.00843 0.00229 -0.0609 0.7226 1.0000
1.500 0.4602 0.00853 0.00230 -0.0602 0.7018 1.0000
1.750 0.4852 0.00865 0.00231 -0.0595 0.6806 1.0000
2.000 0.5102 0.00879 0.00234 -0.0588 0.6580 1.0000
2.250 0.5353 0.00895 0.00240 -0.0582 0.6349 1.0000
2.500 0.5602 0.00914 0.00247 -0.0575 0.6115 1.0000
2.750 0.5850 0.00935 0.00261 -0.0569 0.5876 1.0000
3.000 0.6098 0.00957 0.00274 -0.0562 0.5629 1.0000
3.250 0.6346 0.00980 0.00289 -0.0556 0.5380 1.0000
3.500 0.6592 0.01005 0.00306 -0.0550 0.5122 1.0000
3.750 0.6837 0.01032 0.00327 -0.0543 0.4858 1.0000
4.000 0.7081 0.01061 0.00348 -0.0537 0.4588 1.0000
4.250 0.7322 0.01092 0.00372 -0.0531 0.4311 1.0000
4.500 0.7562 0.01126 0.00398 -0.0524 0.4029 1.0000
4.750 0.7799 0.01162 0.00426 -0.0518 0.3740 1.0000
5.000 0.8035 0.01201 0.00461 -0.0511 0.3447 1.0000
5.500 0.8499 0.01288 0.00533 -0.0497 0.2859 1.0000
5.750 0.8729 0.01335 0.00573 -0.0490 0.2573 1.0000
6.000 0.8956 0.01385 0.00618 -0.0483 0.2298 1.0000
6.250 0.9181 0.01438 0.00665 -0.0476 0.2021 1.0000
6.500 0.9400 0.01498 0.00721 -0.0468 0.1724 1.0000
6.750 0.9611 0.01566 0.00778 -0.0460 0.1415 1.0000
7.000 0.9820 0.01637 0.00839 -0.0451 0.1144 1.0000
7.250 1.0034 0.01703 0.00904 -0.0443 0.0939 1.0000
7.500 1.0237 0.01780 0.00976 -0.0433 0.0752 1.0000
7.750 1.0435 0.01862 0.01056 -0.0423 0.0560 1.0000
8.000 1.0618 0.01959 0.01148 -0.0411 0.0406 1.0000
8.250 1.0794 0.02062 0.01248 -0.0398 0.0282 1.0000
8.500 1.0963 0.02170 0.01365 -0.0384 0.0195 1.0000
8.750 1.1129 0.02276 0.01482 -0.0369 0.0138 1.0000
9.000 1.1270 0.02405 0.01621 -0.0351 0.0098 1.0000
9.250 1.1405 0.02531 0.01764 -0.0333 0.0081 1.0000
9.500 1.1504 0.02685 0.01931 -0.0311 0.0069 1.0000
9.750 1.1535 0.02881 0.02145 -0.0280 0.0062 1.0000
10.000 1.1592 0.03037 0.02320 -0.0253 0.0059 1.0000
10.250 1.1634 0.03211 0.02513 -0.0226 0.0056 1.0000
10.500 1.1669 0.03401 0.02722 -0.0201 0.0054 1.0000
10.750 1.1689 0.03616 0.02958 -0.0178 0.0052 1.0000
11.000 1.1717 0.03819 0.03180 -0.0159 0.0048 1.0000
11.250 1.1737 0.04025 0.03405 -0.0143 0.0045 1.0000
11.500 1.1764 0.04210 0.03604 -0.0132 0.0040 1.0000
11.750 1.1757 0.04448 0.03857 -0.0123 0.0038 1.0000
12.000 1.1704 0.04750 0.04175 -0.0118 0.0035 1.0000
12.250 1.1610 0.05138 0.04585 -0.0117 0.0033 1.0000
12.500 1.1523 0.05547 0.05021 -0.0122 0.0032 1.0000
12.750 1.1424 0.06007 0.05503 -0.0132 0.0033 1.0000
13.000 1.1319 0.06505 0.06023 -0.0152 0.0031 1.0000
13.250 1.1233 0.07013 0.06552 -0.0176 0.0030 1.0000
13.500 1.1097 0.07641 0.07202 -0.0208 0.0029 1.0000
13.750 1.0914 0.08391 0.07968 -0.0249 0.0031 1.0000
14.000 1.0800 0.09078 0.08674 -0.0291 0.0030 1.0000
14.250 1.0594 0.09973 0.09584 -0.0342 0.0032 1.0000
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Polar data table (+)
Polar graphs
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