MH 61 10.26% (mh61-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 61 10.26% (mh61-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.99 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh61-il-1000000.txt Download as CSV file: xf-mh61-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6201 0.08276 0.08121 0.0093 0.8787 0.0072
-8.750 -0.6316 0.07614 0.07456 0.0052 0.8629 0.0072
-8.500 -0.6606 0.06496 0.06330 -0.0052 0.8457 0.0068
-8.250 -0.6201 0.05198 0.05028 -0.0047 0.8158 0.0071
-8.000 -0.6489 0.04688 0.04503 -0.0051 0.8084 0.0069
-7.750 -0.6612 0.04115 0.03911 -0.0056 0.8026 0.0070
-7.500 -0.6647 0.03576 0.03348 -0.0056 0.7970 0.0071
-7.250 -0.6613 0.03098 0.02846 -0.0052 0.7920 0.0073
-7.000 -0.6527 0.02669 0.02391 -0.0046 0.7866 0.0076
-6.750 -0.6397 0.02307 0.02002 -0.0038 0.7817 0.0081
-6.500 -0.6216 0.02054 0.01725 -0.0031 0.7766 0.0086
-6.250 -0.5953 0.02052 0.01710 -0.0026 0.7708 0.0094
-6.000 -0.5766 0.01832 0.01459 -0.0018 0.7660 0.0095
-5.750 -0.5575 0.01575 0.01174 -0.0011 0.7609 0.0095
-5.500 -0.5492 0.00913 0.00443 0.0005 0.7574 0.0109
-4.750 -0.4794 0.01375 0.00803 0.0031 0.7501 0.0056
-4.500 -0.4516 0.01347 0.00771 0.0032 0.7445 0.0053
-4.250 -0.4289 0.01169 0.00575 0.0044 0.7396 0.0049
-4.000 -0.4034 0.01078 0.00473 0.0051 0.7343 0.0047
-3.750 -0.3772 0.01014 0.00396 0.0056 0.7289 0.0047
-3.500 -0.3503 0.00965 0.00332 0.0059 0.7237 0.0047
-3.250 -0.3228 0.00926 0.00286 0.0062 0.7179 0.0049
-3.000 -0.2951 0.00900 0.00249 0.0064 0.7125 0.0052
-2.750 -0.2701 0.00806 0.00188 0.0070 0.7069 0.0941
-2.500 -0.2449 0.00742 0.00163 0.0072 0.7011 0.1975
-2.250 -0.2187 0.00699 0.00147 0.0074 0.6956 0.2777
-2.000 -0.1919 0.00665 0.00135 0.0075 0.6893 0.3430
-1.750 -0.1659 0.00628 0.00125 0.0077 0.6836 0.4306
-1.500 -0.1386 0.00605 0.00118 0.0078 0.6771 0.4804
-1.250 -0.1113 0.00590 0.00111 0.0079 0.6710 0.5204
-1.000 -0.0838 0.00573 0.00105 0.0080 0.6642 0.5610
-0.750 -0.0566 0.00558 0.00099 0.0082 0.6577 0.6040
-0.500 -0.0296 0.00541 0.00095 0.0084 0.6506 0.6505
-0.250 -0.0033 0.00523 0.00092 0.0088 0.6436 0.7036
0.000 0.0225 0.00503 0.00089 0.0093 0.6360 0.7615
0.250 0.0475 0.00482 0.00088 0.0101 0.6287 0.8261
0.500 0.0741 0.00461 0.00089 0.0106 0.6204 0.8960
0.750 0.1195 0.00459 0.00094 0.0070 0.6116 0.9479
1.000 0.1666 0.00466 0.00097 0.0028 0.6020 0.9665
1.250 0.2044 0.00474 0.00102 0.0007 0.5917 0.9778
1.500 0.2405 0.00481 0.00105 -0.0011 0.5813 0.9862
1.750 0.2775 0.00490 0.00110 -0.0031 0.5704 0.9923
2.000 0.3162 0.00497 0.00112 -0.0055 0.5583 0.9962
2.250 0.3557 0.00504 0.00114 -0.0081 0.5449 0.9994
2.500 0.3858 0.00510 0.00116 -0.0086 0.5311 1.0000
2.750 0.4126 0.00518 0.00121 -0.0085 0.5164 1.0000
3.000 0.4395 0.00527 0.00125 -0.0084 0.5001 1.0000
3.250 0.4664 0.00538 0.00131 -0.0082 0.4828 1.0000
3.500 0.4934 0.00551 0.00138 -0.0082 0.4647 1.0000
3.750 0.5204 0.00565 0.00147 -0.0081 0.4448 1.0000
4.000 0.5474 0.00581 0.00157 -0.0080 0.4242 1.0000
4.250 0.5744 0.00599 0.00169 -0.0080 0.4026 1.0000
4.500 0.6013 0.00618 0.00182 -0.0079 0.3805 1.0000
4.750 0.6281 0.00641 0.00199 -0.0079 0.3572 1.0000
5.000 0.6548 0.00669 0.00216 -0.0079 0.3257 1.0000
5.250 0.6813 0.00696 0.00235 -0.0078 0.3003 1.0000
5.500 0.7077 0.00726 0.00256 -0.0078 0.2728 1.0000
5.750 0.7337 0.00769 0.00283 -0.0078 0.2322 1.0000
6.000 0.7589 0.00825 0.00317 -0.0078 0.1832 1.0000
6.250 0.7830 0.00905 0.00366 -0.0077 0.1204 1.0000
6.500 0.8070 0.00975 0.00413 -0.0076 0.0781 1.0000
6.750 0.8312 0.01031 0.00456 -0.0073 0.0516 1.0000
7.000 0.8554 0.01084 0.00499 -0.0070 0.0333 1.0000
7.250 0.8792 0.01136 0.00544 -0.0067 0.0202 1.0000
7.500 0.9013 0.01221 0.00621 -0.0061 0.0055 1.0000
7.750 0.9238 0.01292 0.00697 -0.0054 0.0037 1.0000
8.000 0.9429 0.01413 0.00839 -0.0043 0.0031 1.0000
8.250 0.9638 0.01489 0.00925 -0.0034 0.0030 1.0000
8.500 0.9831 0.01580 0.01027 -0.0024 0.0030 1.0000
8.750 1.0005 0.01685 0.01147 -0.0012 0.0029 1.0000
9.000 1.0155 0.01810 0.01285 0.0003 0.0029 1.0000
9.250 1.0292 0.01941 0.01429 0.0019 0.0029 1.0000
9.500 1.0427 0.02066 0.01565 0.0035 0.0029 1.0000
9.750 1.0560 0.02185 0.01696 0.0051 0.0028 1.0000
10.000 1.0680 0.02310 0.01831 0.0068 0.0027 1.0000
10.250 1.0789 0.02429 0.01961 0.0085 0.0026 1.0000
10.500 1.0865 0.02522 0.02062 0.0106 0.0025 1.0000
10.750 1.0892 0.02691 0.02245 0.0127 0.0025 1.0000
11.000 1.0895 0.02918 0.02490 0.0147 0.0025 1.0000
11.250 1.0922 0.03125 0.02712 0.0160 0.0025 1.0000
11.500 1.0926 0.03365 0.02969 0.0170 0.0025 1.0000
11.750 1.0914 0.03631 0.03252 0.0178 0.0025 1.0000
12.000 1.0882 0.03925 0.03563 0.0182 0.0025 1.0000
12.250 1.0804 0.04289 0.03947 0.0182 0.0025 1.0000
12.500 1.0717 0.04677 0.04353 0.0177 0.0025 1.0000
12.750 1.0496 0.05272 0.04972 0.0164 0.0026 1.0000
13.000 1.0357 0.05781 0.05498 0.0145 0.0026 1.0000
13.250 1.0325 0.06156 0.05886 0.0126 0.0025 1.0000
13.500 1.0177 0.06737 0.06482 0.0097 0.0026 1.0000
14.000 0.9765 0.08272 0.08047 0.0012 0.0027 1.0000
14.250 0.9715 0.08806 0.08589 -0.0020 0.0026 1.0000
14.500 0.9560 0.09578 0.09373 -0.0064 0.0025 1.0000
14.750 0.9319 0.10587 0.10394 -0.0121 0.0026 1.0000
15.000 0.9163 0.11444 0.11260 -0.0167 0.0026 1.0000
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Polar data table (+)
Polar graphs
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