MH 61 10.26% (mh61-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 61 10.26% (mh61-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.62 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh61-il-1000000-n5.txt Download as CSV file: xf-mh61-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 61 10.26%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.7475 0.03893 0.03606 -0.0057 0.7685 0.0032
-7.500 -0.7253 0.03165 0.02820 -0.0036 0.7579 0.0026
-7.000 -0.6994 0.02402 0.01972 -0.0010 0.7478 0.0024
-6.750 -0.6802 0.02140 0.01674 0.0001 0.7426 0.0023
-6.500 -0.6590 0.01923 0.01425 0.0011 0.7379 0.0023
-6.250 -0.6361 0.01746 0.01222 0.0019 0.7329 0.0023
-6.000 -0.6123 0.01603 0.01057 0.0026 0.7277 0.0022
-5.750 -0.5880 0.01476 0.00911 0.0033 0.7229 0.0022
-5.500 -0.5631 0.01373 0.00791 0.0039 0.7177 0.0022
-5.250 -0.5380 0.01283 0.00686 0.0045 0.7127 0.0022
-5.000 -0.5124 0.01206 0.00597 0.0050 0.7078 0.0022
-4.750 -0.4864 0.01142 0.00521 0.0054 0.7024 0.0022
-4.500 -0.4600 0.01086 0.00455 0.0058 0.6973 0.0022
-4.250 -0.4332 0.01040 0.00400 0.0060 0.6919 0.0022
-4.000 -0.4061 0.01001 0.00351 0.0063 0.6863 0.0023
-3.750 -0.3787 0.00968 0.00311 0.0064 0.6808 0.0023
-3.500 -0.3511 0.00940 0.00273 0.0066 0.6748 0.0024
-3.250 -0.3233 0.00917 0.00244 0.0067 0.6690 0.0026
-3.000 -0.2954 0.00896 0.00217 0.0068 0.6625 0.0032
-2.750 -0.2677 0.00874 0.00194 0.0068 0.6563 0.0084
-2.500 -0.2408 0.00833 0.00169 0.0070 0.6497 0.0482
-2.250 -0.2145 0.00787 0.00146 0.0071 0.6432 0.1172
-2.000 -0.1881 0.00741 0.00128 0.0072 0.6361 0.1937
-1.750 -0.1624 0.00691 0.00114 0.0074 0.6291 0.2958
-1.500 -0.1350 0.00670 0.00105 0.0074 0.6216 0.3396
-1.250 -0.1071 0.00658 0.00098 0.0074 0.6142 0.3697
-1.000 -0.0791 0.00647 0.00091 0.0074 0.6059 0.3976
-0.750 -0.0511 0.00637 0.00086 0.0074 0.5979 0.4241
-0.250 0.0048 0.00620 0.00079 0.0073 0.5800 0.4793
0.000 0.0327 0.00612 0.00076 0.0073 0.5708 0.5087
0.250 0.0605 0.00604 0.00074 0.0073 0.5610 0.5407
0.500 0.0882 0.00595 0.00073 0.0073 0.5504 0.5750
0.750 0.1157 0.00586 0.00073 0.0073 0.5401 0.6129
1.000 0.1428 0.00577 0.00074 0.0075 0.5291 0.6545
1.250 0.1696 0.00567 0.00075 0.0077 0.5176 0.6997
1.500 0.1959 0.00557 0.00078 0.0080 0.5057 0.7497
1.750 0.2215 0.00545 0.00081 0.0085 0.4932 0.8056
2.000 0.2469 0.00532 0.00086 0.0092 0.4804 0.8673
2.250 0.2816 0.00527 0.00095 0.0078 0.4661 0.9305
2.500 0.3324 0.00538 0.00104 0.0026 0.4477 0.9592
2.750 0.3731 0.00553 0.00113 -0.0003 0.4289 0.9710
3.000 0.4064 0.00569 0.00123 -0.0015 0.4099 0.9800
3.250 0.4382 0.00586 0.00133 -0.0025 0.3892 0.9872
3.500 0.4703 0.00605 0.00145 -0.0036 0.3684 0.9923
3.750 0.5039 0.00625 0.00158 -0.0050 0.3457 0.9955
4.000 0.5386 0.00646 0.00170 -0.0067 0.3218 0.9981
4.250 0.5735 0.00669 0.00185 -0.0085 0.2970 1.0000
4.500 0.6003 0.00693 0.00200 -0.0085 0.2737 1.0000
5.000 0.6529 0.00760 0.00243 -0.0084 0.2097 1.0000
5.250 0.6789 0.00795 0.00267 -0.0084 0.1813 1.0000
5.500 0.7048 0.00832 0.00293 -0.0083 0.1533 1.0000
5.750 0.7299 0.00885 0.00328 -0.0082 0.1141 1.0000
6.000 0.7549 0.00937 0.00364 -0.0080 0.0812 1.0000
6.250 0.7792 0.00998 0.00409 -0.0079 0.0478 1.0000
6.500 0.8035 0.01050 0.00449 -0.0076 0.0272 1.0000
6.750 0.8282 0.01091 0.00486 -0.0073 0.0181 1.0000
7.000 0.8527 0.01134 0.00525 -0.0070 0.0109 1.0000
7.250 0.8770 0.01176 0.00565 -0.0066 0.0069 1.0000
7.500 0.9009 0.01220 0.00610 -0.0062 0.0039 1.0000
7.750 0.9247 0.01265 0.00657 -0.0058 0.0025 1.0000
8.000 0.9476 0.01319 0.00715 -0.0052 0.0017 1.0000
8.250 0.9701 0.01377 0.00781 -0.0046 0.0015 1.0000
8.500 0.9923 0.01435 0.00849 -0.0039 0.0014 1.0000
8.750 1.0141 0.01494 0.00915 -0.0033 0.0013 1.0000
9.000 1.0349 0.01561 0.00990 -0.0025 0.0013 1.0000
9.250 1.0549 0.01631 0.01069 -0.0016 0.0013 1.0000
9.500 1.0740 0.01707 0.01153 -0.0007 0.0013 1.0000
9.750 1.0912 0.01797 0.01254 0.0005 0.0012 1.0000
10.000 1.1074 0.01888 0.01355 0.0017 0.0012 1.0000
10.250 1.1226 0.01981 0.01458 0.0030 0.0012 1.0000
10.500 1.1376 0.02066 0.01551 0.0043 0.0011 1.0000
10.750 1.1494 0.02170 0.01666 0.0059 0.0011 1.0000
11.000 1.1531 0.02297 0.01805 0.0084 0.0011 1.0000
11.250 1.1587 0.02415 0.01934 0.0104 0.0010 1.0000
11.500 1.1656 0.02546 0.02075 0.0117 0.0010 1.0000
11.750 1.1727 0.02689 0.02228 0.0128 0.0010 1.0000
12.000 1.1799 0.02842 0.02391 0.0136 0.0009 1.0000
12.250 1.1843 0.03030 0.02590 0.0143 0.0009 1.0000
12.500 1.1880 0.03234 0.02806 0.0147 0.0009 1.0000
12.750 1.1826 0.03546 0.03136 0.0151 0.0009 1.0000
13.000 1.1828 0.03807 0.03410 0.0151 0.0009 1.0000
13.250 1.1887 0.04012 0.03623 0.0149 0.0009 1.0000
13.500 1.1854 0.04335 0.03959 0.0144 0.0008 1.0000
13.750 1.1795 0.04704 0.04343 0.0136 0.0008 1.0000
14.000 1.1710 0.05123 0.04777 0.0123 0.0008 1.0000
14.250 1.1699 0.05461 0.05125 0.0111 0.0008 1.0000
14.500 1.1634 0.05885 0.05561 0.0094 0.0008 1.0000
14.750 1.1489 0.06463 0.06155 0.0069 0.0008 1.0000
15.000 1.1406 0.06970 0.06675 0.0045 0.0008 1.0000
15.250 1.1226 0.07666 0.07386 0.0011 0.0008 1.0000
15.500 1.0995 0.08482 0.08219 -0.0029 0.0008 1.0000
15.750 1.0891 0.09095 0.08842 -0.0061 0.0008 1.0000
16.000 1.0703 0.09880 0.09640 -0.0100 0.0008 1.0000
16.250 1.0514 0.10695 0.10466 -0.0140 0.0008 1.0000
16.500 1.0241 0.11718 0.11504 -0.0190 0.0009 1.0000
16.750 1.0164 0.12332 0.12123 -0.0220 0.0009 1.0000
17.000 0.9815 0.13610 0.13416 -0.0281 0.0009 1.0000
17.250 0.9625 0.14553 0.14369 -0.0326 0.0009 1.0000
17.500 0.9404 0.15639 0.15463 -0.0378 0.0009 1.0000
17.750 0.9192 0.16763 0.16595 -0.0430 0.0009 1.0000
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Polar data table (+)
Polar graphs
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