MH 22 7.2% (mh22-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 22 7.2% (mh22-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.94 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh22-il-1000000-n5.txt Download as CSV file: xf-mh22-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 22 7.2%
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4553 0.08400 0.08258 0.0042 1.0000 0.0022
-8.250 -0.4563 0.07922 0.07781 0.0024 1.0000 0.0021
-8.000 -0.4603 0.07406 0.07266 0.0004 1.0000 0.0020
-7.750 -0.5223 0.07913 0.07764 -0.0022 1.0000 0.0021
-7.500 -0.5189 0.07635 0.07489 -0.0038 1.0000 0.0024
-7.250 -0.5256 0.07071 0.06926 -0.0087 1.0000 0.0022
-7.000 -0.5238 0.06457 0.06310 -0.0141 1.0000 0.0020
-6.750 -0.5179 0.05810 0.05656 -0.0190 1.0000 0.0019
-6.500 -0.5087 0.05147 0.04982 -0.0228 1.0000 0.0018
-6.250 -0.4875 0.04299 0.04094 -0.0282 0.8966 0.0016
-6.000 -0.4774 0.03666 0.03420 -0.0281 0.8515 0.0016
-5.750 -0.4656 0.02910 0.02611 -0.0271 0.8231 0.0014
-5.500 -0.4525 0.02156 0.01781 -0.0251 0.8015 0.0012
-5.250 -0.4341 0.01672 0.01223 -0.0231 0.7829 0.0011
-5.000 -0.4113 0.01417 0.00920 -0.0219 0.7660 0.0011
-4.750 -0.3869 0.01254 0.00722 -0.0209 0.7505 0.0011
-4.500 -0.3617 0.01146 0.00589 -0.0202 0.7355 0.0011
-4.250 -0.3360 0.01065 0.00488 -0.0196 0.7216 0.0012
-4.000 -0.3099 0.01002 0.00409 -0.0191 0.7092 0.0014
-3.750 -0.2833 0.00957 0.00347 -0.0187 0.6985 0.0017
-3.500 -0.2565 0.00928 0.00308 -0.0185 0.6885 0.0021
-3.250 -0.2293 0.00907 0.00281 -0.0183 0.6790 0.0023
-3.000 -0.2021 0.00887 0.00256 -0.0181 0.6705 0.0024
-2.750 -0.1752 0.00846 0.00199 -0.0178 0.6628 0.0033
-2.500 -0.1479 0.00823 0.00170 -0.0176 0.6551 0.0046
-2.250 -0.1204 0.00807 0.00146 -0.0174 0.6482 0.0052
-2.000 -0.0934 0.00775 0.00122 -0.0171 0.6411 0.0355
-1.750 -0.0667 0.00744 0.00108 -0.0170 0.6344 0.0882
-1.500 -0.0397 0.00720 0.00095 -0.0169 0.6271 0.1351
-1.250 -0.0127 0.00697 0.00086 -0.0167 0.6202 0.1868
-1.000 0.0144 0.00679 0.00079 -0.0166 0.6126 0.2349
-0.750 0.0417 0.00662 0.00073 -0.0165 0.6051 0.2794
-0.500 0.0689 0.00649 0.00067 -0.0165 0.5972 0.3222
-0.250 0.0956 0.00625 0.00061 -0.0163 0.5885 0.3968
0.000 0.1219 0.00597 0.00058 -0.0161 0.5797 0.4892
0.250 0.1478 0.00569 0.00056 -0.0158 0.5695 0.5873
0.500 0.1728 0.00538 0.00055 -0.0153 0.5580 0.6943
0.750 0.1964 0.00506 0.00056 -0.0143 0.5453 0.8049
1.000 0.2213 0.00478 0.00061 -0.0133 0.5297 0.9220
1.250 0.2697 0.00487 0.00066 -0.0179 0.5059 0.9733
1.500 0.3045 0.00500 0.00069 -0.0194 0.4817 0.9854
1.750 0.3377 0.00515 0.00074 -0.0207 0.4561 0.9929
2.000 0.3758 0.00530 0.00079 -0.0231 0.4297 0.9979
2.250 0.4087 0.00545 0.00086 -0.0243 0.4054 1.0000
2.500 0.4344 0.00561 0.00094 -0.0239 0.3834 1.0000
2.750 0.4602 0.00576 0.00102 -0.0235 0.3625 1.0000
3.000 0.4859 0.00593 0.00111 -0.0231 0.3404 1.0000
3.250 0.5091 0.00660 0.00132 -0.0226 0.2384 1.0000
3.500 0.5332 0.00708 0.00157 -0.0221 0.1765 1.0000
3.750 0.5567 0.00771 0.00186 -0.0216 0.1018 1.0000
4.000 0.5799 0.00839 0.00222 -0.0210 0.0346 1.0000
4.250 0.6040 0.00891 0.00259 -0.0204 0.0015 1.0000
4.500 0.6295 0.00912 0.00282 -0.0199 0.0012 1.0000
4.750 0.6550 0.00935 0.00309 -0.0195 0.0010 1.0000
5.000 0.6803 0.00962 0.00341 -0.0190 0.0010 1.0000
5.250 0.7054 0.00993 0.00379 -0.0184 0.0010 1.0000
5.500 0.7302 0.01033 0.00432 -0.0178 0.0010 1.0000
5.750 0.7545 0.01084 0.00492 -0.0171 0.0010 1.0000
6.000 0.7781 0.01150 0.00572 -0.0163 0.0010 1.0000
6.250 0.8006 0.01236 0.00672 -0.0153 0.0010 1.0000
6.500 0.8216 0.01350 0.00803 -0.0140 0.0011 1.0000
6.750 0.8414 0.01489 0.00959 -0.0126 0.0012 1.0000
7.000 0.8603 0.01664 0.01152 -0.0110 0.0013 1.0000
7.250 0.8789 0.01871 0.01380 -0.0094 0.0014 1.0000
7.500 0.8959 0.02150 0.01688 -0.0077 0.0016 1.0000
8.000 0.9263 0.02976 0.02593 -0.0029 0.0037 1.0000
8.250 0.9379 0.03294 0.02941 -0.0012 0.0037 1.0000
8.500 0.9475 0.03595 0.03268 0.0004 0.0035 1.0000
8.750 0.9530 0.03934 0.03633 0.0022 0.0034 1.0000
9.000 0.9543 0.04280 0.04004 0.0039 0.0034 1.0000
9.250 0.9526 0.04589 0.04333 0.0055 0.0032 1.0000
9.500 0.9430 0.04928 0.04691 0.0076 0.0032 1.0000
9.750 0.9247 0.05239 0.05016 0.0099 0.0032 1.0000
10.000 0.9103 0.05560 0.05349 0.0096 0.0031 1.0000
10.250 0.8947 0.05992 0.05793 0.0075 0.0031 1.0000
10.500 0.8738 0.06636 0.06450 0.0033 0.0032 1.0000
10.750 0.8530 0.07428 0.07255 -0.0027 0.0034 1.0000
11.000 0.8368 0.08295 0.08131 -0.0096 0.0034 1.0000
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Polar data table (+)
Polar graphs
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