MH 106 13.07% (mh106-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 106 13.07% (mh106-il) Reynolds number: 100,000 Max Cl/Cd: 44.6 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh106-il-100000-n5.txt Download as CSV file: xf-mh106-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 106 13.07%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6861 0.09952 0.09454 -0.0010 1.0000 0.0166
-12.250 -0.7155 0.08817 0.08308 -0.0088 1.0000 0.0161
-12.000 -0.7442 0.07836 0.07309 -0.0160 1.0000 0.0158
-11.750 -0.7687 0.07059 0.06512 -0.0217 1.0000 0.0156
-11.500 -0.7892 0.06449 0.05880 -0.0255 1.0000 0.0154
-11.250 -0.8072 0.05952 0.05359 -0.0278 1.0000 0.0153
-11.000 -0.8229 0.05540 0.04924 -0.0285 1.0000 0.0153
-10.750 -0.8345 0.05209 0.04570 -0.0279 1.0000 0.0153
-10.500 -0.8434 0.04918 0.04256 -0.0264 1.0000 0.0154
-10.250 -0.8494 0.04651 0.03965 -0.0241 1.0000 0.0154
-10.000 -0.8507 0.04406 0.03696 -0.0218 1.0000 0.0156
-9.750 -0.8463 0.04164 0.03428 -0.0199 1.0000 0.0158
-9.500 -0.8382 0.03932 0.03171 -0.0182 1.0000 0.0161
-9.250 -0.8269 0.03717 0.02933 -0.0166 1.0000 0.0164
-9.000 -0.8134 0.03511 0.02705 -0.0151 1.0000 0.0169
-8.750 -0.7981 0.03331 0.02504 -0.0137 1.0000 0.0177
-8.500 -0.7813 0.03181 0.02330 -0.0123 1.0000 0.0189
-8.250 -0.7673 0.03010 0.02158 -0.0109 1.0000 0.0200
-8.000 -0.7515 0.02879 0.02023 -0.0095 1.0000 0.0215
-7.750 -0.7354 0.02744 0.01879 -0.0079 1.0000 0.0230
-7.500 -0.7196 0.02615 0.01738 -0.0061 1.0000 0.0244
-7.250 -0.7053 0.02482 0.01596 -0.0042 1.0000 0.0261
-7.000 -0.6896 0.02368 0.01479 -0.0026 1.0000 0.0298
-6.750 -0.6732 0.02259 0.01360 -0.0008 1.0000 0.0345
-6.500 -0.6568 0.02144 0.01236 0.0009 1.0000 0.0417
-6.250 -0.6413 0.02017 0.01119 0.0027 1.0000 0.0571
-6.000 -0.6282 0.01863 0.01006 0.0047 1.0000 0.1055
-5.750 -0.6151 0.01736 0.00941 0.0066 1.0000 0.1977
-5.500 -0.5980 0.01678 0.00907 0.0082 1.0000 0.2567
-5.250 -0.5655 0.01635 0.00874 0.0068 0.9737 0.3060
-5.000 -0.5280 0.01604 0.00845 0.0047 0.9339 0.3501
-4.750 -0.4898 0.01577 0.00811 0.0027 0.8977 0.3806
-4.500 -0.4567 0.01553 0.00775 0.0020 0.8630 0.4019
-4.250 -0.4284 0.01534 0.00740 0.0023 0.8309 0.4208
-4.000 -0.4027 0.01517 0.00708 0.0031 0.8019 0.4384
-3.750 -0.3778 0.01500 0.00681 0.0040 0.7761 0.4563
-3.500 -0.3531 0.01485 0.00655 0.0050 0.7524 0.4754
-3.250 -0.3281 0.01471 0.00630 0.0058 0.7308 0.4957
-3.000 -0.3032 0.01455 0.00608 0.0067 0.7106 0.5166
-2.750 -0.2780 0.01442 0.00588 0.0075 0.6922 0.5397
-2.500 -0.2527 0.01429 0.00572 0.0083 0.6752 0.5640
-2.250 -0.2271 0.01417 0.00557 0.0091 0.6588 0.5901
-2.000 -0.2012 0.01407 0.00546 0.0098 0.6436 0.6185
-1.750 -0.1749 0.01399 0.00537 0.0105 0.6295 0.6481
-1.500 -0.1481 0.01393 0.00532 0.0111 0.6162 0.6792
-1.250 -0.1205 0.01390 0.00528 0.0115 0.6032 0.7109
-1.000 -0.0920 0.01389 0.00528 0.0118 0.5909 0.7428
-0.750 -0.0623 0.01393 0.00531 0.0119 0.5797 0.7740
-0.500 -0.0310 0.01401 0.00535 0.0117 0.5697 0.8034
-0.250 0.0024 0.01412 0.00543 0.0111 0.5590 0.8302
0.000 0.0367 0.01426 0.00552 0.0102 0.5488 0.8544
0.250 0.0725 0.01443 0.00560 0.0090 0.5401 0.8752
0.500 0.1072 0.01459 0.00571 0.0079 0.5310 0.8950
0.750 0.1437 0.01478 0.00582 0.0064 0.5227 0.9118
1.000 0.1807 0.01496 0.00593 0.0048 0.5144 0.9266
1.250 0.2184 0.01514 0.00606 0.0029 0.5066 0.9401
1.500 0.2586 0.01531 0.00616 0.0005 0.4991 0.9513
1.750 0.2981 0.01547 0.00629 -0.0019 0.4914 0.9624
2.000 0.3370 0.01561 0.00638 -0.0042 0.4844 0.9733
2.250 0.3765 0.01574 0.00651 -0.0068 0.4772 0.9838
2.500 0.4175 0.01584 0.00658 -0.0097 0.4701 0.9933
2.750 0.4549 0.01593 0.00669 -0.0120 0.4632 1.0000
3.000 0.4768 0.01606 0.00682 -0.0111 0.4570 1.0000
3.250 0.4989 0.01621 0.00695 -0.0102 0.4516 1.0000
3.500 0.5211 0.01638 0.00719 -0.0094 0.4447 1.0000
3.750 0.5434 0.01656 0.00733 -0.0085 0.4393 1.0000
4.000 0.5658 0.01676 0.00762 -0.0077 0.4323 1.0000
4.250 0.5883 0.01695 0.00781 -0.0068 0.4260 1.0000
4.500 0.6108 0.01717 0.00811 -0.0059 0.4192 1.0000
4.750 0.6333 0.01737 0.00834 -0.0050 0.4121 1.0000
5.000 0.6558 0.01760 0.00863 -0.0041 0.4048 1.0000
5.250 0.6783 0.01780 0.00888 -0.0032 0.3971 1.0000
5.500 0.7006 0.01804 0.00922 -0.0023 0.3889 1.0000
5.750 0.7232 0.01823 0.00944 -0.0013 0.3809 1.0000
6.000 0.7452 0.01847 0.00982 -0.0004 0.3713 1.0000
6.250 0.7675 0.01869 0.01009 0.0006 0.3626 1.0000
6.500 0.7895 0.01890 0.01040 0.0016 0.3525 1.0000
6.750 0.8112 0.01914 0.01079 0.0026 0.3413 1.0000
7.000 0.8328 0.01938 0.01114 0.0037 0.3297 1.0000
7.250 0.8541 0.01962 0.01148 0.0047 0.3170 1.0000
7.500 0.8750 0.01988 0.01187 0.0058 0.3028 1.0000
7.750 0.8955 0.02018 0.01227 0.0070 0.2869 1.0000
8.000 0.9151 0.02052 0.01268 0.0082 0.2694 1.0000
8.250 0.9336 0.02095 0.01312 0.0096 0.2507 1.0000
8.500 0.9512 0.02151 0.01371 0.0109 0.2304 1.0000
8.750 0.9667 0.02222 0.01438 0.0125 0.2106 1.0000
9.000 0.9812 0.02305 0.01524 0.0141 0.1922 1.0000
9.250 0.9942 0.02398 0.01617 0.0157 0.1744 1.0000
9.500 1.0057 0.02500 0.01720 0.0175 0.1589 1.0000
9.750 1.0157 0.02610 0.01832 0.0194 0.1451 1.0000
10.000 1.0238 0.02727 0.01952 0.0213 0.1328 1.0000
10.250 1.0297 0.02853 0.02081 0.0234 0.1224 1.0000
10.500 1.0316 0.02993 0.02221 0.0257 0.1138 1.0000
10.750 1.0318 0.03130 0.02368 0.0282 0.1055 1.0000
11.000 1.0272 0.03312 0.02547 0.0302 0.0997 1.0000
11.250 1.0269 0.03503 0.02756 0.0313 0.0927 1.0000
11.500 1.0222 0.03753 0.03006 0.0317 0.0876 1.0000
11.750 1.0221 0.03991 0.03257 0.0319 0.0818 1.0000
12.000 1.0185 0.04277 0.03548 0.0316 0.0769 1.0000
12.250 1.0157 0.04565 0.03840 0.0312 0.0727 1.0000
12.500 1.0136 0.04862 0.04151 0.0306 0.0676 1.0000
12.750 1.0083 0.05199 0.04489 0.0297 0.0640 1.0000
13.000 1.0052 0.05520 0.04820 0.0291 0.0599 1.0000
13.250 1.0023 0.05849 0.05160 0.0282 0.0563 1.0000
13.500 0.9965 0.06220 0.05536 0.0269 0.0533 1.0000
13.750 0.9913 0.06583 0.05901 0.0258 0.0503 1.0000
14.000 0.9876 0.06947 0.06282 0.0247 0.0473 1.0000
14.250 0.9826 0.07332 0.06677 0.0233 0.0448 1.0000
14.500 0.9752 0.07772 0.07121 0.0214 0.0424 1.0000
14.750 0.9712 0.08155 0.07506 0.0201 0.0405 1.0000
15.000 0.9650 0.08617 0.07988 0.0183 0.0383 1.0000
15.250 0.9590 0.09078 0.08463 0.0163 0.0365 1.0000
15.500 0.9522 0.09563 0.08958 0.0141 0.0348 1.0000
15.750 0.9450 0.10067 0.09466 0.0117 0.0333 1.0000
16.000 0.9398 0.10520 0.09918 0.0097 0.0317 1.0000
16.250 0.9304 0.11106 0.10524 0.0069 0.0309 1.0000
16.500 0.9162 0.11819 0.11256 0.0032 0.0299 1.0000
16.750 0.9026 0.12534 0.11989 -0.0004 0.0294 1.0000
17.000 0.8834 0.13418 0.12888 -0.0051 0.0287 1.0000
17.250 0.8575 0.14524 0.14011 -0.0109 0.0290 1.0000
17.500 0.8075 0.16451 0.15943 -0.0205 0.0297 1.0000
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Polar data table (+)
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