MH 106 13.07% (mh106-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 106 13.07% (mh106-il) Reynolds number: 200,000 Max Cl/Cd: 60.63 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh106-il-200000-n5.txt Download as CSV file: xf-mh106-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6491 0.13878 0.13517 0.0210 1.0000 0.0095
-13.750 -0.6577 0.13054 0.12696 0.0174 1.0000 0.0094
-13.250 -0.8060 0.08122 0.07694 -0.0105 1.0000 0.0073
-12.750 -0.8363 0.06806 0.06349 -0.0192 1.0000 0.0072
-12.250 -0.8631 0.05719 0.05226 -0.0256 1.0000 0.0072
-12.000 -0.8763 0.05254 0.04738 -0.0277 1.0000 0.0072
-11.750 -0.8895 0.04842 0.04306 -0.0288 1.0000 0.0074
-11.500 -0.8955 0.04551 0.04001 -0.0288 1.0000 0.0075
-11.250 -0.8971 0.04349 0.03792 -0.0283 1.0000 0.0077
-11.000 -0.8994 0.04149 0.03580 -0.0270 1.0000 0.0080
-10.750 -0.9015 0.03938 0.03352 -0.0251 1.0000 0.0081
-10.500 -0.9016 0.03750 0.03145 -0.0227 1.0000 0.0082
-10.250 -0.8984 0.03597 0.02978 -0.0203 1.0000 0.0085
-10.000 -0.8924 0.03427 0.02786 -0.0181 1.0000 0.0088
-9.750 -0.8829 0.03251 0.02589 -0.0162 1.0000 0.0091
-9.500 -0.8712 0.03076 0.02395 -0.0144 1.0000 0.0092
-9.250 -0.8576 0.02914 0.02215 -0.0128 1.0000 0.0094
-9.000 -0.8431 0.02758 0.02044 -0.0111 1.0000 0.0096
-8.750 -0.8278 0.02619 0.01891 -0.0095 1.0000 0.0098
-8.500 -0.8118 0.02492 0.01753 -0.0079 1.0000 0.0100
-8.250 -0.7964 0.02367 0.01619 -0.0062 1.0000 0.0103
-8.000 -0.7816 0.02243 0.01488 -0.0045 1.0000 0.0107
-7.750 -0.7648 0.02142 0.01382 -0.0029 1.0000 0.0112
-7.500 -0.7470 0.02051 0.01284 -0.0015 1.0000 0.0118
-7.250 -0.7288 0.01965 0.01190 0.0000 1.0000 0.0126
-7.000 -0.7098 0.01885 0.01100 0.0015 1.0000 0.0137
-6.750 -0.6911 0.01804 0.01016 0.0029 1.0000 0.0155
-6.500 -0.6708 0.01742 0.00949 0.0041 1.0000 0.0182
-6.250 -0.6439 0.01659 0.00860 0.0039 0.9788 0.0228
-6.000 -0.6065 0.01565 0.00765 0.0016 0.9244 0.0369
-5.750 -0.5754 0.01460 0.00678 0.0005 0.8769 0.0812
-5.250 -0.5329 0.01309 0.00579 0.0025 0.8046 0.2234
-5.000 -0.5102 0.01279 0.00550 0.0036 0.7761 0.2641
-4.750 -0.4866 0.01259 0.00525 0.0045 0.7505 0.2932
-4.500 -0.4629 0.01240 0.00503 0.0054 0.7274 0.3229
-4.250 -0.4386 0.01225 0.00482 0.0063 0.7066 0.3487
-4.000 -0.4137 0.01210 0.00458 0.0070 0.6870 0.3666
-3.750 -0.3884 0.01197 0.00437 0.0076 0.6681 0.3828
-3.500 -0.3630 0.01185 0.00416 0.0082 0.6503 0.3989
-3.250 -0.3374 0.01173 0.00397 0.0088 0.6339 0.4152
-3.000 -0.3116 0.01162 0.00379 0.0093 0.6189 0.4323
-2.750 -0.2858 0.01151 0.00363 0.0098 0.6044 0.4501
-2.500 -0.2601 0.01140 0.00348 0.0104 0.5905 0.4687
-2.250 -0.2344 0.01129 0.00335 0.0109 0.5772 0.4887
-2.000 -0.2086 0.01120 0.00323 0.0114 0.5649 0.5105
-1.750 -0.1831 0.01109 0.00314 0.0120 0.5538 0.5333
-1.500 -0.1574 0.01100 0.00306 0.0126 0.5431 0.5584
-1.250 -0.1318 0.01090 0.00299 0.0132 0.5327 0.5856
-1.000 -0.1063 0.01082 0.00294 0.0138 0.5231 0.6144
-0.500 -0.0549 0.01066 0.00290 0.0151 0.5053 0.6753
-0.250 -0.0291 0.01061 0.00291 0.0157 0.4978 0.7071
0.000 -0.0025 0.01056 0.00294 0.0162 0.4899 0.7389
0.250 0.0245 0.01055 0.00297 0.0167 0.4829 0.7706
0.500 0.0531 0.01055 0.00305 0.0168 0.4754 0.8016
0.750 0.0834 0.01061 0.00312 0.0166 0.4691 0.8303
1.000 0.1163 0.01068 0.00323 0.0158 0.4624 0.8562
1.250 0.1507 0.01080 0.00333 0.0147 0.4558 0.8785
1.500 0.1860 0.01093 0.00345 0.0134 0.4498 0.8970
1.750 0.2220 0.01106 0.00358 0.0119 0.4435 0.9122
2.000 0.2569 0.01123 0.00369 0.0106 0.4382 0.9257
2.250 0.2938 0.01136 0.00383 0.0088 0.4318 0.9364
2.500 0.3301 0.01151 0.00396 0.0072 0.4260 0.9458
2.750 0.3636 0.01166 0.00410 0.0060 0.4204 0.9558
3.000 0.4007 0.01180 0.00425 0.0041 0.4141 0.9631
3.250 0.4354 0.01196 0.00436 0.0027 0.4088 0.9711
3.500 0.4723 0.01207 0.00453 0.0008 0.4021 0.9781
3.750 0.5090 0.01221 0.00465 -0.0011 0.3960 0.9846
4.000 0.5473 0.01231 0.00480 -0.0034 0.3891 0.9908
4.250 0.5858 0.01241 0.00490 -0.0058 0.3819 0.9966
4.500 0.6197 0.01249 0.00505 -0.0072 0.3745 1.0000
4.750 0.6425 0.01261 0.00518 -0.0064 0.3678 1.0000
5.000 0.6655 0.01273 0.00534 -0.0055 0.3609 1.0000
5.250 0.6884 0.01286 0.00551 -0.0047 0.3533 1.0000
5.500 0.7115 0.01300 0.00570 -0.0038 0.3455 1.0000
5.750 0.7344 0.01315 0.00587 -0.0029 0.3373 1.0000
6.000 0.7575 0.01329 0.00609 -0.0021 0.3279 1.0000
6.250 0.7804 0.01346 0.00632 -0.0013 0.3183 1.0000
6.500 0.8031 0.01364 0.00653 -0.0004 0.3070 1.0000
6.750 0.8258 0.01384 0.00678 0.0005 0.2942 1.0000
7.000 0.8480 0.01407 0.00704 0.0014 0.2789 1.0000
7.250 0.8700 0.01435 0.00734 0.0024 0.2612 1.0000
7.500 0.8910 0.01471 0.00769 0.0034 0.2412 1.0000
7.750 0.9111 0.01516 0.00810 0.0045 0.2212 1.0000
8.000 0.9305 0.01569 0.00859 0.0057 0.2002 1.0000
8.250 0.9488 0.01631 0.00915 0.0070 0.1806 1.0000
8.500 0.9672 0.01692 0.00974 0.0083 0.1628 1.0000
8.750 0.9846 0.01759 0.01041 0.0096 0.1461 1.0000
9.000 1.0015 0.01829 0.01110 0.0110 0.1314 1.0000
9.250 1.0175 0.01903 0.01183 0.0125 0.1179 1.0000
9.500 1.0329 0.01978 0.01259 0.0141 0.1061 1.0000
9.750 1.0474 0.02057 0.01340 0.0157 0.0957 1.0000
10.000 1.0603 0.02144 0.01427 0.0174 0.0865 1.0000
10.250 1.0731 0.02227 0.01514 0.0192 0.0777 1.0000
10.500 1.0841 0.02318 0.01612 0.0211 0.0700 1.0000
10.750 1.0912 0.02426 0.01720 0.0232 0.0630 1.0000
11.000 1.0982 0.02520 0.01822 0.0255 0.0571 1.0000
11.250 1.0977 0.02644 0.01948 0.0284 0.0523 1.0000
11.500 1.0999 0.02777 0.02090 0.0303 0.0481 1.0000
11.750 1.1006 0.02947 0.02267 0.0315 0.0441 1.0000
12.000 1.0986 0.03171 0.02494 0.0321 0.0406 1.0000
12.250 1.1008 0.03382 0.02718 0.0323 0.0376 1.0000
12.500 1.1002 0.03636 0.02981 0.0321 0.0346 1.0000
12.750 1.0958 0.03947 0.03296 0.0315 0.0320 1.0000
13.000 1.0952 0.04226 0.03586 0.0310 0.0297 1.0000
13.250 1.0934 0.04526 0.03896 0.0303 0.0274 1.0000
13.500 1.0883 0.04871 0.04247 0.0293 0.0256 1.0000
13.750 1.0798 0.05264 0.04645 0.0280 0.0241 1.0000
14.000 1.0770 0.05593 0.04989 0.0271 0.0227 1.0000
14.250 1.0726 0.05947 0.05354 0.0260 0.0213 1.0000
14.500 1.0657 0.06342 0.05759 0.0246 0.0199 1.0000
14.750 1.0584 0.06753 0.06178 0.0231 0.0191 1.0000
15.000 1.0480 0.07228 0.06660 0.0212 0.0183 1.0000
15.250 1.0418 0.07658 0.07100 0.0194 0.0173 1.0000
15.500 1.0355 0.08097 0.07552 0.0176 0.0166 1.0000
15.750 1.0289 0.08558 0.08023 0.0156 0.0155 1.0000
16.000 1.0203 0.09061 0.08537 0.0134 0.0149 1.0000
16.250 1.0130 0.09555 0.09041 0.0112 0.0146 1.0000
16.500 1.0024 0.10119 0.09613 0.0085 0.0140 1.0000
16.750 0.9913 0.10707 0.10208 0.0056 0.0134 1.0000
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