MH 104 15.28% (mh104-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 104 15.28% (mh104-il) Reynolds number: 500,000 Max Cl/Cd: 95.55 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh104-il-500000.txt Download as CSV file: xf-mh104-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.6441 0.11991 0.11753 0.0003 1.0000 0.0114
-14.500 -0.6796 0.10640 0.10393 -0.0073 1.0000 0.0110
-14.250 -0.7089 0.09516 0.09257 -0.0145 1.0000 0.0108
-14.000 -0.7359 0.08531 0.08257 -0.0211 1.0000 0.0108
-13.750 -0.7613 0.07656 0.07367 -0.0271 1.0000 0.0106
-13.500 -0.7960 0.06687 0.06375 -0.0335 1.0000 0.0101
-13.250 -0.8075 0.06169 0.05844 -0.0371 1.0000 0.0102
-13.000 -0.8257 0.05591 0.05248 -0.0406 1.0000 0.0102
-12.750 -0.8523 0.04958 0.04588 -0.0435 1.0000 0.0099
-12.500 -0.8807 0.04378 0.03969 -0.0446 1.0000 0.0096
-12.250 -0.8978 0.03984 0.03546 -0.0441 1.0000 0.0095
-12.000 -0.9072 0.03672 0.03208 -0.0426 1.0000 0.0093
-11.750 -0.9090 0.03464 0.02980 -0.0408 1.0000 0.0092
-11.500 -0.9049 0.03336 0.02851 -0.0392 1.0000 0.0095
-11.250 -0.9033 0.03146 0.02645 -0.0368 1.0000 0.0095
-11.000 -0.8986 0.03000 0.02488 -0.0344 1.0000 0.0096
-10.750 -0.8921 0.02879 0.02358 -0.0320 1.0000 0.0098
-10.500 -0.8832 0.02769 0.02238 -0.0297 1.0000 0.0099
-10.250 -0.8715 0.02650 0.02110 -0.0277 1.0000 0.0101
-10.000 -0.8580 0.02530 0.01981 -0.0260 1.0000 0.0102
-9.750 -0.8438 0.02399 0.01840 -0.0242 1.0000 0.0104
-9.500 -0.8285 0.02282 0.01714 -0.0226 1.0000 0.0104
-9.250 -0.8128 0.02170 0.01595 -0.0210 0.9997 0.0105
-9.000 -0.7737 0.02030 0.01438 -0.0241 0.9182 0.0107
-8.750 -0.7590 0.01955 0.01339 -0.0217 0.8692 0.0110
-8.500 -0.7438 0.01886 0.01251 -0.0194 0.8380 0.0112
-8.250 -0.7266 0.01821 0.01169 -0.0176 0.8141 0.0114
-8.000 -0.7100 0.01740 0.01074 -0.0157 0.7935 0.0117
-7.750 -0.6938 0.01651 0.00974 -0.0138 0.7751 0.0123
-7.500 -0.6733 0.01595 0.00907 -0.0125 0.7579 0.0130
-7.250 -0.6518 0.01544 0.00843 -0.0113 0.7419 0.0140
-7.000 -0.6305 0.01486 0.00773 -0.0101 0.7269 0.0152
-6.750 -0.6083 0.01433 0.00713 -0.0091 0.7130 0.0175
-6.500 -0.5861 0.01376 0.00648 -0.0080 0.6999 0.0217
-6.250 -0.5638 0.01317 0.00585 -0.0070 0.6874 0.0307
-6.000 -0.5421 0.01253 0.00528 -0.0059 0.6751 0.0538
-5.750 -0.5221 0.01168 0.00472 -0.0048 0.6629 0.1098
-5.500 -0.5004 0.01104 0.00434 -0.0039 0.6512 0.1704
-5.250 -0.4763 0.01067 0.00408 -0.0032 0.6402 0.2107
-5.000 -0.4510 0.01042 0.00388 -0.0027 0.6292 0.2407
-4.750 -0.4252 0.01021 0.00372 -0.0023 0.6186 0.2670
-4.500 -0.3990 0.01006 0.00356 -0.0019 0.6086 0.2900
-4.250 -0.3725 0.00993 0.00341 -0.0016 0.5982 0.3082
-4.000 -0.3461 0.00978 0.00328 -0.0012 0.5882 0.3271
-3.750 -0.3199 0.00966 0.00316 -0.0008 0.5789 0.3507
-3.500 -0.2932 0.00954 0.00305 -0.0005 0.5694 0.3713
-3.250 -0.2666 0.00943 0.00294 -0.0002 0.5610 0.3884
-3.000 -0.2399 0.00933 0.00283 0.0001 0.5524 0.4053
-2.750 -0.2131 0.00923 0.00273 0.0004 0.5445 0.4230
-2.500 -0.1864 0.00914 0.00264 0.0007 0.5364 0.4416
-2.250 -0.1595 0.00906 0.00257 0.0010 0.5287 0.4612
-2.000 -0.1328 0.00897 0.00249 0.0013 0.5213 0.4817
-1.750 -0.1064 0.00888 0.00243 0.0017 0.5147 0.5040
-1.500 -0.0798 0.00879 0.00238 0.0020 0.5079 0.5284
-1.250 -0.0539 0.00872 0.00234 0.0025 0.5020 0.5551
-1.000 -0.0276 0.00859 0.00232 0.0029 0.4959 0.5843
-0.750 -0.0019 0.00851 0.00230 0.0034 0.4900 0.6160
-0.500 0.0238 0.00843 0.00230 0.0040 0.4846 0.6497
-0.250 0.0496 0.00832 0.00230 0.0046 0.4792 0.6842
0.000 0.0750 0.00826 0.00232 0.0052 0.4743 0.7199
0.250 0.1005 0.00821 0.00236 0.0059 0.4698 0.7551
0.500 0.1266 0.00813 0.00241 0.0065 0.4649 0.7897
0.750 0.1533 0.00810 0.00246 0.0069 0.4602 0.8235
1.000 0.1810 0.00816 0.00254 0.0072 0.4559 0.8541
1.250 0.2115 0.00817 0.00264 0.0069 0.4517 0.8815
1.500 0.2446 0.00824 0.00274 0.0061 0.4471 0.9045
1.750 0.2793 0.00838 0.00285 0.0048 0.4428 0.9223
2.000 0.3168 0.00855 0.00300 0.0030 0.4386 0.9344
2.250 0.3534 0.00867 0.00313 0.0013 0.4342 0.9443
2.500 0.3861 0.00882 0.00325 0.0004 0.4300 0.9547
2.750 0.4274 0.00905 0.00340 -0.0023 0.4257 0.9587
3.000 0.4654 0.00918 0.00354 -0.0044 0.4217 0.9645
3.250 0.5016 0.00930 0.00367 -0.0061 0.4175 0.9704
3.500 0.5421 0.00944 0.00377 -0.0087 0.4133 0.9739
3.750 0.5791 0.00963 0.00392 -0.0106 0.4093 0.9790
4.000 0.6167 0.00971 0.00404 -0.0127 0.4052 0.9833
4.250 0.6576 0.00978 0.00411 -0.0155 0.4009 0.9864
4.500 0.6961 0.00991 0.00420 -0.0178 0.3966 0.9903
4.750 0.7344 0.01002 0.00433 -0.0201 0.3924 0.9940
5.000 0.7752 0.01003 0.00438 -0.0230 0.3874 0.9972
5.250 0.8140 0.01010 0.00443 -0.0254 0.3826 1.0000
5.500 0.8368 0.01022 0.00454 -0.0246 0.3784 1.0000
5.750 0.8601 0.01026 0.00464 -0.0239 0.3740 1.0000
6.000 0.8832 0.01033 0.00474 -0.0231 0.3694 1.0000
6.250 0.9058 0.01050 0.00487 -0.0223 0.3648 1.0000
6.500 0.9291 0.01056 0.00501 -0.0215 0.3602 1.0000
6.750 0.9523 0.01065 0.00514 -0.0207 0.3550 1.0000
7.000 0.9748 0.01083 0.00528 -0.0198 0.3498 1.0000
7.250 0.9982 0.01091 0.00545 -0.0191 0.3443 1.0000
7.500 1.0211 0.01103 0.00560 -0.0183 0.3381 1.0000
7.750 1.0437 0.01119 0.00579 -0.0174 0.3321 1.0000
8.000 1.0667 0.01131 0.00596 -0.0166 0.3249 1.0000
8.250 1.0888 0.01150 0.00616 -0.0157 0.3179 1.0000
8.500 1.1113 0.01166 0.00636 -0.0148 0.3092 1.0000
8.750 1.1332 0.01186 0.00660 -0.0139 0.3001 1.0000
9.000 1.1541 0.01212 0.00685 -0.0128 0.2896 1.0000
9.250 1.1749 0.01239 0.00713 -0.0117 0.2778 1.0000
9.500 1.1947 0.01272 0.00745 -0.0105 0.2648 1.0000
9.750 1.2132 0.01313 0.00784 -0.0092 0.2506 1.0000
10.000 1.2302 0.01361 0.00828 -0.0076 0.2359 1.0000
10.250 1.2460 0.01414 0.00877 -0.0059 0.2213 1.0000
10.500 1.2603 0.01472 0.00932 -0.0040 0.2065 1.0000
10.750 1.2732 0.01536 0.00991 -0.0020 0.1919 1.0000
11.000 1.2851 0.01600 0.01052 0.0002 0.1788 1.0000
11.250 1.2950 0.01669 0.01120 0.0026 0.1661 1.0000
11.500 1.3026 0.01740 0.01191 0.0053 0.1556 1.0000
11.750 1.3021 0.01820 0.01269 0.0093 0.1464 1.0000
12.000 1.3020 0.01919 0.01366 0.0126 0.1368 1.0000
12.250 1.3048 0.02029 0.01480 0.0149 0.1285 1.0000
12.500 1.3050 0.02181 0.01632 0.0167 0.1204 1.0000
12.750 1.3069 0.02347 0.01800 0.0180 0.1120 1.0000
13.000 1.3078 0.02540 0.01995 0.0188 0.1040 1.0000
13.500 1.3059 0.03007 0.02467 0.0197 0.0892 1.0000
13.750 1.3018 0.03287 0.02749 0.0198 0.0825 1.0000
14.000 1.2995 0.03557 0.03023 0.0198 0.0768 1.0000
14.250 1.2930 0.03877 0.03345 0.0196 0.0707 1.0000
14.500 1.2878 0.04188 0.03660 0.0194 0.0653 1.0000
14.750 1.2795 0.04537 0.04012 0.0190 0.0605 1.0000
15.000 1.2732 0.04869 0.04348 0.0186 0.0556 1.0000
15.250 1.2626 0.05261 0.04742 0.0180 0.0513 1.0000
15.500 1.2576 0.05601 0.05088 0.0173 0.0472 1.0000
15.750 1.2479 0.06004 0.05494 0.0165 0.0438 1.0000
16.000 1.2412 0.06381 0.05876 0.0156 0.0400 1.0000
16.250 1.2330 0.06781 0.06279 0.0146 0.0367 1.0000
16.500 1.2239 0.07203 0.06705 0.0135 0.0341 1.0000
16.750 1.2190 0.07576 0.07085 0.0125 0.0319 1.0000
17.000 1.2103 0.08003 0.07517 0.0112 0.0294 1.0000
17.250 1.2012 0.08447 0.07965 0.0099 0.0275 1.0000
17.500 1.1966 0.08835 0.08361 0.0087 0.0255 1.0000
17.750 1.1890 0.09266 0.08797 0.0073 0.0242 1.0000
18.000 1.1783 0.09752 0.09288 0.0057 0.0229 1.0000
18.250 1.1700 0.10212 0.09756 0.0041 0.0218 1.0000
18.500 1.1673 0.10590 0.10141 0.0027 0.0201 1.0000
18.750 1.1586 0.11067 0.10623 0.0009 0.0191 1.0000
19.000 1.1487 0.11570 0.11132 -0.0011 0.0184 1.0000
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Polar data table (+)
Polar graphs
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