MH 104 15.28% (mh104-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 104 15.28% (mh104-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.82 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh104-il-1000000.txt Download as CSV file: xf-mh104-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7385 0.12999 0.12810 0.0073 1.0000 0.0059
-16.250 -0.7849 0.11387 0.11177 -0.0019 1.0000 0.0058
-16.000 -0.8162 0.10236 0.10010 -0.0088 1.0000 0.0057
-15.750 -0.8767 0.08617 0.08355 -0.0185 1.0000 0.0054
-15.500 -0.8868 0.08028 0.07759 -0.0221 1.0000 0.0055
-15.250 -0.9122 0.07210 0.06921 -0.0269 1.0000 0.0054
-15.000 -0.9156 0.06778 0.06485 -0.0296 1.0000 0.0055
-14.750 -0.9433 0.06001 0.05684 -0.0338 1.0000 0.0053
-14.500 -0.9558 0.05471 0.05141 -0.0368 1.0000 0.0053
-14.250 -0.9618 0.05050 0.04709 -0.0391 1.0000 0.0054
-14.000 -0.9669 0.04662 0.04310 -0.0410 1.0000 0.0054
-13.750 -0.9728 0.04291 0.03926 -0.0426 1.0000 0.0054
-13.500 -0.9878 0.03844 0.03459 -0.0434 1.0000 0.0053
-13.250 -0.9845 0.03633 0.03243 -0.0438 1.0000 0.0054
-13.000 -0.9842 0.03411 0.03011 -0.0437 1.0000 0.0055
-12.750 -0.9876 0.03172 0.02759 -0.0428 1.0000 0.0055
-12.500 -0.9877 0.02983 0.02560 -0.0414 1.0000 0.0055
-12.250 -0.9871 0.02816 0.02382 -0.0396 1.0000 0.0055
-12.000 -0.9871 0.02652 0.02207 -0.0373 1.0000 0.0055
-11.750 -0.9839 0.02523 0.02068 -0.0348 1.0000 0.0055
-11.500 -0.9757 0.02435 0.01974 -0.0325 1.0000 0.0056
-11.250 -0.9714 0.02323 0.01853 -0.0295 1.0000 0.0056
-11.000 -0.9658 0.02224 0.01746 -0.0264 1.0000 0.0057
-10.750 -0.9560 0.02132 0.01647 -0.0238 1.0000 0.0057
-10.500 -0.9424 0.02049 0.01557 -0.0219 1.0000 0.0057
-10.250 -0.9271 0.01959 0.01460 -0.0203 0.9867 0.0058
-10.000 -0.8964 0.01874 0.01349 -0.0215 0.8890 0.0059
-9.750 -0.8835 0.01812 0.01265 -0.0190 0.8471 0.0060
-9.500 -0.8662 0.01757 0.01196 -0.0172 0.8187 0.0061
-9.250 -0.8485 0.01695 0.01119 -0.0156 0.7962 0.0061
-9.000 -0.8282 0.01647 0.01060 -0.0143 0.7766 0.0063
-8.750 -0.8074 0.01598 0.00999 -0.0131 0.7586 0.0064
-8.500 -0.7855 0.01556 0.00945 -0.0121 0.7418 0.0066
-8.250 -0.7657 0.01490 0.00868 -0.0108 0.7260 0.0067
-8.000 -0.7459 0.01420 0.00785 -0.0094 0.7117 0.0069
-7.750 -0.7238 0.01367 0.00724 -0.0084 0.6985 0.0073
-7.500 -0.7002 0.01327 0.00676 -0.0076 0.6857 0.0076
-7.250 -0.6761 0.01291 0.00631 -0.0069 0.6732 0.0080
-7.000 -0.6514 0.01259 0.00591 -0.0062 0.6605 0.0086
-6.750 -0.6274 0.01215 0.00540 -0.0055 0.6484 0.0098
-6.500 -0.6022 0.01186 0.00505 -0.0049 0.6370 0.0116
-6.250 -0.5776 0.01148 0.00463 -0.0042 0.6261 0.0157
-6.000 -0.5527 0.01113 0.00428 -0.0036 0.6154 0.0234
-5.750 -0.5278 0.01077 0.00395 -0.0031 0.6054 0.0356
-5.500 -0.5037 0.01035 0.00362 -0.0024 0.5954 0.0578
-5.250 -0.4800 0.00985 0.00327 -0.0017 0.5853 0.0935
-5.000 -0.4563 0.00938 0.00297 -0.0010 0.5759 0.1379
-4.750 -0.4318 0.00901 0.00274 -0.0005 0.5662 0.1785
-4.500 -0.4061 0.00872 0.00257 0.0000 0.5573 0.2133
-4.250 -0.3801 0.00851 0.00243 0.0003 0.5485 0.2421
-4.000 -0.3534 0.00833 0.00231 0.0006 0.5401 0.2661
-3.750 -0.3265 0.00821 0.00220 0.0008 0.5319 0.2856
-3.500 -0.2992 0.00809 0.00210 0.0010 0.5236 0.3035
-3.250 -0.2723 0.00797 0.00202 0.0013 0.5156 0.3264
-3.000 -0.2452 0.00785 0.00194 0.0015 0.5078 0.3475
-2.750 -0.2177 0.00778 0.00186 0.0017 0.5005 0.3637
-2.500 -0.1901 0.00770 0.00180 0.0018 0.4935 0.3792
-2.250 -0.1627 0.00764 0.00174 0.0020 0.4866 0.3952
-2.000 -0.1350 0.00756 0.00168 0.0021 0.4806 0.4118
-1.750 -0.1075 0.00751 0.00164 0.0022 0.4741 0.4292
-1.500 -0.0799 0.00745 0.00160 0.0024 0.4683 0.4470
-1.250 -0.0524 0.00738 0.00156 0.0025 0.4623 0.4661
-1.000 -0.0252 0.00733 0.00154 0.0027 0.4566 0.4865
-0.750 0.0023 0.00725 0.00152 0.0029 0.4521 0.5088
-0.500 0.0295 0.00718 0.00150 0.0031 0.4472 0.5332
-0.250 0.0565 0.00713 0.00149 0.0033 0.4422 0.5594
0.000 0.0834 0.00705 0.00149 0.0036 0.4379 0.5892
0.250 0.1101 0.00696 0.00149 0.0039 0.4336 0.6205
0.500 0.1366 0.00690 0.00151 0.0042 0.4293 0.6517
0.750 0.1627 0.00685 0.00153 0.0047 0.4249 0.6849
1.250 0.2154 0.00669 0.00159 0.0055 0.4177 0.7510
1.500 0.2412 0.00664 0.00163 0.0061 0.4137 0.7845
1.750 0.2670 0.00662 0.00169 0.0066 0.4096 0.8166
2.000 0.2938 0.00657 0.00174 0.0070 0.4067 0.8474
2.250 0.3211 0.00654 0.00181 0.0073 0.4032 0.8772
2.500 0.3503 0.00656 0.00189 0.0072 0.3995 0.9033
2.750 0.3813 0.00667 0.00200 0.0067 0.3952 0.9244
3.000 0.4156 0.00673 0.00210 0.0054 0.3922 0.9397
3.250 0.4526 0.00683 0.00221 0.0036 0.3887 0.9495
3.500 0.4868 0.00694 0.00231 0.0023 0.3851 0.9575
3.750 0.5209 0.00710 0.00243 0.0010 0.3810 0.9639
4.000 0.5530 0.00721 0.00255 0.0002 0.3777 0.9699
4.250 0.5913 0.00730 0.00265 -0.0020 0.3742 0.9722
4.500 0.6278 0.00741 0.00275 -0.0039 0.3701 0.9752
4.750 0.6610 0.00757 0.00288 -0.0050 0.3658 0.9794
5.000 0.6946 0.00768 0.00300 -0.0063 0.3621 0.9827
5.250 0.7330 0.00775 0.00308 -0.0085 0.3578 0.9843
5.500 0.7702 0.00786 0.00318 -0.0106 0.3531 0.9863
5.750 0.8064 0.00799 0.00330 -0.0125 0.3482 0.9887
6.000 0.8419 0.00805 0.00340 -0.0141 0.3438 0.9913
6.250 0.8765 0.00817 0.00351 -0.0157 0.3383 0.9937
6.500 0.9151 0.00827 0.00361 -0.0181 0.3326 0.9954
6.750 0.9545 0.00833 0.00369 -0.0207 0.3263 0.9976
7.000 0.9928 0.00847 0.00381 -0.0231 0.3193 0.9996
7.250 1.0205 0.00854 0.00391 -0.0232 0.3127 1.0000
7.750 1.0668 0.00883 0.00419 -0.0217 0.2969 1.0000
8.000 1.0895 0.00902 0.00437 -0.0209 0.2877 1.0000
8.250 1.1115 0.00926 0.00457 -0.0200 0.2759 1.0000
8.500 1.1335 0.00950 0.00479 -0.0190 0.2635 1.0000
8.750 1.1546 0.00981 0.00506 -0.0180 0.2499 1.0000
9.000 1.1749 0.01017 0.00537 -0.0169 0.2352 1.0000
9.250 1.1944 0.01057 0.00571 -0.0156 0.2204 1.0000
9.500 1.2133 0.01100 0.00608 -0.0143 0.2052 1.0000
9.750 1.2313 0.01148 0.00649 -0.0129 0.1894 1.0000
10.000 1.2487 0.01196 0.00692 -0.0113 0.1746 1.0000
10.250 1.2657 0.01245 0.00736 -0.0097 0.1617 1.0000
10.500 1.2815 0.01298 0.00784 -0.0080 0.1484 1.0000
10.750 1.2971 0.01349 0.00831 -0.0062 0.1372 1.0000
11.000 1.3114 0.01404 0.00883 -0.0043 0.1259 1.0000
11.250 1.3248 0.01460 0.00936 -0.0023 0.1161 1.0000
11.500 1.3351 0.01526 0.00997 0.0002 0.1051 1.0000
11.750 1.3426 0.01599 0.01066 0.0030 0.0943 1.0000
12.000 1.3427 0.01675 0.01138 0.0071 0.0853 1.0000
12.250 1.3435 0.01756 0.01219 0.0106 0.0776 1.0000
12.500 1.3439 0.01869 0.01330 0.0134 0.0696 1.0000
12.750 1.3450 0.02009 0.01470 0.0153 0.0628 1.0000
13.000 1.3483 0.02163 0.01626 0.0165 0.0564 1.0000
13.250 1.3499 0.02350 0.01814 0.0173 0.0510 1.0000
13.500 1.3515 0.02557 0.02023 0.0178 0.0457 1.0000
13.750 1.3497 0.02808 0.02275 0.0181 0.0397 1.0000
14.000 1.3491 0.03058 0.02528 0.0182 0.0363 1.0000
14.250 1.3465 0.03336 0.02809 0.0181 0.0321 1.0000
14.500 1.3437 0.03621 0.03098 0.0180 0.0296 1.0000
14.750 1.3392 0.03926 0.03408 0.0177 0.0266 1.0000
15.000 1.3357 0.04225 0.03713 0.0175 0.0247 1.0000
15.250 1.3292 0.04560 0.04052 0.0171 0.0227 1.0000
15.500 1.3252 0.04872 0.04370 0.0166 0.0213 1.0000
15.750 1.3196 0.05215 0.04719 0.0160 0.0197 1.0000
16.000 1.3122 0.05588 0.05097 0.0153 0.0181 1.0000
16.250 1.3083 0.05924 0.05440 0.0145 0.0170 1.0000
16.500 1.3035 0.06278 0.05801 0.0137 0.0159 1.0000
16.750 1.2982 0.06643 0.06171 0.0128 0.0151 1.0000
17.000 1.2910 0.07037 0.06570 0.0118 0.0139 1.0000
17.250 1.2872 0.07395 0.06936 0.0108 0.0133 1.0000
17.500 1.2819 0.07778 0.07325 0.0098 0.0126 1.0000
17.750 1.2763 0.08161 0.07715 0.0087 0.0120 1.0000
18.000 1.2686 0.08585 0.08143 0.0074 0.0113 1.0000
18.250 1.2620 0.09000 0.08565 0.0061 0.0106 1.0000
18.500 1.2579 0.09378 0.08951 0.0049 0.0101 1.0000
18.750 1.2510 0.09803 0.09382 0.0034 0.0094 1.0000
19.000 1.2439 0.10238 0.09824 0.0019 0.0092 1.0000
19.250 1.2352 0.10700 0.10292 0.0003 0.0087 1.0000
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