MH 104 15.28% (mh104-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 104 15.28% (mh104-il) Reynolds number: 500,000 Max Cl/Cd: 92.63 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh104-il-500000-n5.txt Download as CSV file: xf-mh104-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 104 15.28%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.7583 0.14080 0.13807 0.0143 1.0000 0.0048
-17.000 -0.7823 0.12986 0.12696 0.0083 1.0000 0.0047
-16.750 -0.8004 0.12081 0.11779 0.0032 1.0000 0.0047
-16.500 -0.8177 0.11246 0.10931 -0.0015 1.0000 0.0046
-16.250 -0.8318 0.10492 0.10166 -0.0059 1.0000 0.0046
-16.000 -0.8453 0.09785 0.09447 -0.0100 1.0000 0.0046
-15.750 -0.8661 0.08987 0.08635 -0.0145 1.0000 0.0046
-15.500 -0.8785 0.08342 0.07977 -0.0183 1.0000 0.0046
-15.250 -0.8927 0.07712 0.07335 -0.0218 1.0000 0.0046
-15.000 -0.9017 0.07175 0.06787 -0.0250 1.0000 0.0046
-14.750 -0.9161 0.06595 0.06195 -0.0281 1.0000 0.0046
-14.500 -0.9272 0.06060 0.05645 -0.0311 1.0000 0.0046
-14.250 -0.9335 0.05613 0.05186 -0.0335 1.0000 0.0046
-14.000 -0.9385 0.05194 0.04755 -0.0358 1.0000 0.0047
-13.750 -0.9457 0.04767 0.04315 -0.0379 1.0000 0.0047
-13.500 -0.9538 0.04358 0.03892 -0.0395 1.0000 0.0046
-13.250 -0.9559 0.04044 0.03567 -0.0406 1.0000 0.0047
-13.000 -0.9593 0.03742 0.03254 -0.0413 1.0000 0.0048
-12.750 -0.9648 0.03451 0.02950 -0.0412 1.0000 0.0048
-12.500 -0.9651 0.03236 0.02723 -0.0406 1.0000 0.0048
-12.250 -0.9666 0.03033 0.02511 -0.0394 1.0000 0.0049
-12.000 -0.9658 0.02865 0.02333 -0.0377 1.0000 0.0050
-11.750 -0.9619 0.02731 0.02190 -0.0357 1.0000 0.0050
-11.500 -0.9565 0.02615 0.02067 -0.0336 1.0000 0.0051
-11.250 -0.9509 0.02506 0.01951 -0.0312 1.0000 0.0051
-11.000 -0.9447 0.02405 0.01843 -0.0285 1.0000 0.0052
-10.750 -0.9369 0.02316 0.01746 -0.0258 1.0000 0.0053
-10.500 -0.9077 0.02214 0.01625 -0.0273 0.8945 0.0054
-10.250 -0.8978 0.02148 0.01535 -0.0244 0.8456 0.0054
-10.000 -0.8845 0.02084 0.01453 -0.0222 0.8154 0.0055
-9.750 -0.8695 0.02017 0.01369 -0.0203 0.7909 0.0058
-9.500 -0.8528 0.01954 0.01291 -0.0186 0.7702 0.0058
-9.250 -0.8348 0.01892 0.01215 -0.0171 0.7525 0.0060
-9.000 -0.8156 0.01835 0.01144 -0.0157 0.7361 0.0062
-8.750 -0.7958 0.01778 0.01073 -0.0145 0.7208 0.0064
-8.500 -0.7748 0.01727 0.01010 -0.0133 0.7060 0.0066
-8.250 -0.7545 0.01666 0.00939 -0.0122 0.6921 0.0069
-8.000 -0.7325 0.01618 0.00881 -0.0112 0.6793 0.0073
-7.750 -0.7096 0.01575 0.00830 -0.0104 0.6674 0.0078
-7.500 -0.6863 0.01535 0.00779 -0.0096 0.6553 0.0084
-7.000 -0.6390 0.01458 0.00685 -0.0081 0.6318 0.0102
-6.750 -0.6146 0.01423 0.00643 -0.0075 0.6213 0.0119
-6.500 -0.5901 0.01390 0.00604 -0.0068 0.6113 0.0145
-6.250 -0.5653 0.01357 0.00567 -0.0063 0.6014 0.0182
-6.000 -0.5406 0.01323 0.00530 -0.0057 0.5918 0.0241
-5.750 -0.5162 0.01287 0.00495 -0.0051 0.5818 0.0344
-5.500 -0.4921 0.01244 0.00458 -0.0044 0.5723 0.0533
-5.250 -0.4688 0.01194 0.00419 -0.0037 0.5635 0.0849
-5.000 -0.4457 0.01139 0.00383 -0.0030 0.5550 0.1302
-4.750 -0.4220 0.01094 0.00356 -0.0024 0.5472 0.1764
-4.500 -0.3967 0.01064 0.00336 -0.0019 0.5391 0.2101
-4.250 -0.3704 0.01047 0.00319 -0.0016 0.5313 0.2315
-4.000 -0.3442 0.01027 0.00304 -0.0013 0.5231 0.2537
-3.750 -0.3182 0.01008 0.00291 -0.0009 0.5156 0.2817
-3.500 -0.2917 0.00992 0.00278 -0.0006 0.5081 0.3039
-3.250 -0.2648 0.00982 0.00267 -0.0003 0.5015 0.3187
-3.000 -0.2376 0.00972 0.00256 -0.0001 0.4949 0.3323
-2.750 -0.2105 0.00965 0.00246 0.0001 0.4886 0.3457
-2.500 -0.1832 0.00956 0.00238 0.0003 0.4825 0.3597
-2.250 -0.1559 0.00949 0.00230 0.0005 0.4760 0.3737
-2.000 -0.1287 0.00943 0.00223 0.0007 0.4702 0.3880
-1.750 -0.1013 0.00936 0.00217 0.0009 0.4645 0.4032
-1.500 -0.0741 0.00930 0.00212 0.0011 0.4592 0.4186
-1.250 -0.0470 0.00925 0.00207 0.0013 0.4546 0.4351
-1.000 -0.0197 0.00918 0.00204 0.0014 0.4499 0.4520
-0.750 0.0074 0.00912 0.00200 0.0017 0.4449 0.4705
-0.500 0.0343 0.00908 0.00198 0.0019 0.4402 0.4899
-0.250 0.0615 0.00901 0.00197 0.0021 0.4358 0.5106
0.000 0.0882 0.00894 0.00196 0.0024 0.4316 0.5339
0.250 0.1149 0.00889 0.00196 0.0027 0.4276 0.5586
0.500 0.1413 0.00883 0.00197 0.0030 0.4240 0.5857
0.750 0.1677 0.00876 0.00199 0.0034 0.4200 0.6149
1.000 0.1939 0.00869 0.00202 0.0038 0.4160 0.6444
1.250 0.2199 0.00865 0.00205 0.0042 0.4124 0.6756
1.500 0.2456 0.00860 0.00210 0.0048 0.4090 0.7082
1.750 0.2716 0.00853 0.00216 0.0053 0.4055 0.7417
2.000 0.2976 0.00848 0.00222 0.0058 0.4017 0.7748
2.250 0.3239 0.00846 0.00230 0.0063 0.3981 0.8073
2.500 0.3509 0.00847 0.00238 0.0066 0.3945 0.8393
2.750 0.3805 0.00847 0.00249 0.0064 0.3912 0.8691
3.000 0.4130 0.00852 0.00261 0.0055 0.3873 0.8946
3.250 0.4491 0.00863 0.00274 0.0039 0.3834 0.9136
3.500 0.4861 0.00878 0.00287 0.0020 0.3795 0.9279
3.750 0.5213 0.00888 0.00300 0.0005 0.3759 0.9395
4.000 0.5590 0.00900 0.00313 -0.0016 0.3719 0.9466
4.250 0.5912 0.00913 0.00326 -0.0025 0.3679 0.9552
4.500 0.6266 0.00929 0.00340 -0.0042 0.3641 0.9604
4.750 0.6563 0.00940 0.00354 -0.0045 0.3603 0.9682
5.000 0.6920 0.00952 0.00368 -0.0062 0.3557 0.9720
5.250 0.7260 0.00968 0.00382 -0.0076 0.3510 0.9767
5.500 0.7568 0.00982 0.00398 -0.0083 0.3466 0.9821
5.750 0.7946 0.00993 0.00412 -0.0105 0.3408 0.9851
6.000 0.8317 0.01009 0.00427 -0.0126 0.3352 0.9891
6.250 0.8671 0.01022 0.00444 -0.0143 0.3292 0.9929
6.500 0.9027 0.01035 0.00458 -0.0162 0.3224 0.9955
6.750 0.9374 0.01049 0.00474 -0.0178 0.3158 0.9979
7.000 0.9717 0.01064 0.00491 -0.0194 0.3075 0.9999
7.250 0.9950 0.01081 0.00509 -0.0187 0.3002 1.0000
7.500 1.0170 0.01102 0.00529 -0.0178 0.2913 1.0000
7.750 1.0393 0.01122 0.00552 -0.0169 0.2821 1.0000
8.000 1.0608 0.01148 0.00576 -0.0159 0.2717 1.0000
8.250 1.0816 0.01178 0.00604 -0.0148 0.2605 1.0000
8.500 1.1017 0.01213 0.00636 -0.0137 0.2480 1.0000
8.750 1.1213 0.01250 0.00671 -0.0125 0.2350 1.0000
9.000 1.1401 0.01292 0.00710 -0.0111 0.2221 1.0000
9.250 1.1583 0.01336 0.00752 -0.0097 0.2093 1.0000
9.500 1.1755 0.01385 0.00797 -0.0082 0.1963 1.0000
9.750 1.1917 0.01437 0.00846 -0.0066 0.1832 1.0000
10.000 1.2065 0.01495 0.00900 -0.0048 0.1695 1.0000
10.250 1.2201 0.01556 0.00958 -0.0028 0.1566 1.0000
10.500 1.2322 0.01620 0.01018 -0.0006 0.1444 1.0000
10.750 1.2418 0.01692 0.01086 0.0018 0.1320 1.0000
11.000 1.2492 0.01769 0.01160 0.0045 0.1215 1.0000
11.250 1.2510 0.01841 0.01232 0.0082 0.1122 1.0000
11.500 1.2525 0.01926 0.01318 0.0115 0.1053 1.0000
11.750 1.2543 0.02035 0.01428 0.0140 0.0981 1.0000
12.000 1.2574 0.02163 0.01558 0.0159 0.0910 1.0000
12.250 1.2591 0.02323 0.01720 0.0172 0.0847 1.0000
12.500 1.2630 0.02488 0.01889 0.0181 0.0786 1.0000
13.000 1.2647 0.02914 0.02320 0.0191 0.0664 1.0000
13.250 1.2631 0.03167 0.02575 0.0193 0.0614 1.0000
13.500 1.2628 0.03417 0.02830 0.0194 0.0562 1.0000
14.000 1.2570 0.03983 0.03405 0.0191 0.0479 1.0000
14.250 1.2504 0.04312 0.03737 0.0189 0.0434 1.0000
14.500 1.2464 0.04619 0.04049 0.0185 0.0399 1.0000
14.750 1.2415 0.04938 0.04374 0.0181 0.0371 1.0000
15.000 1.2343 0.05293 0.04733 0.0176 0.0340 1.0000
15.250 1.2298 0.05630 0.05075 0.0169 0.0310 1.0000
15.500 1.2229 0.06002 0.05450 0.0161 0.0283 1.0000
15.750 1.2198 0.06336 0.05791 0.0154 0.0267 1.0000
16.000 1.2138 0.06709 0.06169 0.0145 0.0241 1.0000
16.250 1.2075 0.07093 0.06557 0.0135 0.0221 1.0000
16.500 1.2043 0.07445 0.06916 0.0125 0.0208 1.0000
16.750 1.2006 0.07808 0.07286 0.0115 0.0198 1.0000
17.000 1.1930 0.08225 0.07706 0.0103 0.0179 1.0000
17.250 1.1893 0.08597 0.08087 0.0092 0.0168 1.0000
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Polar data table (+)
Polar graphs
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