MH 108 11.98% (mh108-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 108 11.98% (mh108-il) Reynolds number: 200,000 Max Cl/Cd: 58.51 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh108-il-200000-n5.txt Download as CSV file: xf-mh108-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 108 11.98%
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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7603 0.12627 0.12257 0.0238 1.0000 0.0094
-14.250 -0.7928 0.11305 0.10927 0.0167 1.0000 0.0092
-14.000 -0.8208 0.10198 0.09810 0.0104 1.0000 0.0088
-13.750 -0.8529 0.09047 0.08644 0.0035 1.0000 0.0084
-13.500 -0.8755 0.08124 0.07706 -0.0024 1.0000 0.0084
-13.250 -0.8963 0.07268 0.06834 -0.0084 1.0000 0.0086
-13.000 -0.9184 0.06453 0.06000 -0.0137 1.0000 0.0081
-12.750 -0.9348 0.05786 0.05314 -0.0182 1.0000 0.0080
-12.500 -0.9452 0.05280 0.04789 -0.0217 1.0000 0.0083
-12.250 -0.9584 0.04801 0.04290 -0.0238 1.0000 0.0082
-12.000 -0.9670 0.04446 0.03916 -0.0247 1.0000 0.0083
-11.750 -0.9727 0.04164 0.03612 -0.0245 1.0000 0.0086
-11.500 -0.9779 0.03909 0.03338 -0.0232 1.0000 0.0087
-11.250 -0.9796 0.03705 0.03114 -0.0213 1.0000 0.0090
-11.000 -0.9793 0.03521 0.02910 -0.0190 1.0000 0.0092
-10.750 -0.9772 0.03350 0.02721 -0.0164 1.0000 0.0094
-10.500 -0.9722 0.03174 0.02530 -0.0141 1.0000 0.0097
-10.250 -0.9642 0.03011 0.02354 -0.0121 1.0000 0.0099
-10.000 -0.9535 0.02865 0.02197 -0.0103 1.0000 0.0103
-9.750 -0.9400 0.02735 0.02056 -0.0087 1.0000 0.0106
-9.500 -0.9253 0.02610 0.01918 -0.0071 1.0000 0.0112
-9.250 -0.9095 0.02490 0.01784 -0.0056 1.0000 0.0118
-9.000 -0.8926 0.02378 0.01655 -0.0042 1.0000 0.0125
-8.750 -0.8756 0.02262 0.01527 -0.0027 1.0000 0.0134
-8.500 -0.8571 0.02161 0.01418 -0.0014 1.0000 0.0146
-8.250 -0.8367 0.02079 0.01326 -0.0003 1.0000 0.0167
-8.000 -0.8170 0.01985 0.01229 0.0008 1.0000 0.0195
-7.750 -0.7958 0.01907 0.01142 0.0019 1.0000 0.0232
-7.500 -0.7751 0.01822 0.01057 0.0030 1.0000 0.0287
-7.250 -0.7536 0.01749 0.00984 0.0040 1.0000 0.0368
-7.000 -0.7314 0.01684 0.00921 0.0049 1.0000 0.0465
-6.750 -0.7088 0.01627 0.00867 0.0058 1.0000 0.0573
-6.500 -0.6860 0.01574 0.00818 0.0066 1.0000 0.0694
-6.250 -0.6630 0.01525 0.00772 0.0075 1.0000 0.0825
-6.000 -0.6400 0.01480 0.00729 0.0083 1.0000 0.0960
-5.750 -0.6170 0.01437 0.00689 0.0092 1.0000 0.1097
-5.500 -0.5941 0.01396 0.00653 0.0101 1.0000 0.1235
-5.000 -0.5161 0.01313 0.00574 0.0053 0.9094 0.1651
-4.750 -0.4832 0.01286 0.00538 0.0045 0.8597 0.1858
-4.500 -0.4576 0.01264 0.00509 0.0052 0.8182 0.2064
-4.250 -0.4333 0.01245 0.00483 0.0062 0.7833 0.2277
-4.000 -0.4094 0.01225 0.00458 0.0072 0.7530 0.2508
-3.750 -0.3851 0.01208 0.00433 0.0081 0.7254 0.2748
-3.500 -0.3607 0.01190 0.00412 0.0089 0.7005 0.3011
-3.250 -0.3362 0.01171 0.00392 0.0097 0.6774 0.3295
-3.000 -0.3115 0.01154 0.00374 0.0105 0.6560 0.3602
-2.750 -0.2867 0.01136 0.00356 0.0112 0.6355 0.3914
-2.500 -0.2620 0.01120 0.00341 0.0120 0.6161 0.4244
-2.250 -0.2373 0.01104 0.00328 0.0128 0.5981 0.4594
-2.000 -0.2124 0.01088 0.00315 0.0136 0.5808 0.4953
-1.750 -0.1878 0.01071 0.00306 0.0144 0.5640 0.5335
-1.500 -0.1633 0.01055 0.00297 0.0153 0.5477 0.5744
-1.250 -0.1388 0.01040 0.00291 0.0162 0.5325 0.6177
-1.000 -0.1140 0.01027 0.00287 0.0171 0.5184 0.6623
-0.750 -0.0888 0.01016 0.00286 0.0180 0.5045 0.7073
-0.500 -0.0627 0.01009 0.00286 0.0188 0.4907 0.7513
-0.250 -0.0347 0.01006 0.00289 0.0192 0.4775 0.7932
0.000 -0.0034 0.01010 0.00295 0.0189 0.4649 0.8311
0.250 0.0314 0.01020 0.00302 0.0179 0.4522 0.8630
0.500 0.0688 0.01033 0.00311 0.0163 0.4396 0.8877
0.750 0.1056 0.01047 0.00319 0.0148 0.4276 0.9076
1.000 0.1419 0.01063 0.00328 0.0133 0.4170 0.9232
1.250 0.1787 0.01080 0.00336 0.0117 0.4070 0.9358
1.500 0.2155 0.01095 0.00346 0.0100 0.3968 0.9465
1.750 0.2501 0.01111 0.00355 0.0087 0.3877 0.9568
2.000 0.2860 0.01127 0.00364 0.0072 0.3791 0.9657
2.250 0.3230 0.01141 0.00374 0.0053 0.3707 0.9730
2.500 0.3581 0.01157 0.00383 0.0038 0.3628 0.9809
2.750 0.3967 0.01167 0.00391 0.0016 0.3547 0.9865
3.000 0.4335 0.01182 0.00400 -0.0004 0.3476 0.9926
3.250 0.4722 0.01189 0.00408 -0.0027 0.3395 0.9978
3.500 0.5023 0.01203 0.00418 -0.0033 0.3332 1.0000
3.750 0.5259 0.01214 0.00431 -0.0025 0.3267 1.0000
4.000 0.5493 0.01228 0.00443 -0.0017 0.3206 1.0000
4.250 0.5729 0.01244 0.00459 -0.0009 0.3146 1.0000
4.500 0.5965 0.01259 0.00476 -0.0002 0.3083 1.0000
4.750 0.6199 0.01278 0.00493 0.0006 0.3027 1.0000
5.000 0.6438 0.01293 0.00514 0.0014 0.2961 1.0000
5.250 0.6673 0.01314 0.00534 0.0022 0.2901 1.0000
5.500 0.6911 0.01332 0.00558 0.0029 0.2838 1.0000
5.750 0.7147 0.01352 0.00580 0.0037 0.2772 1.0000
6.000 0.7384 0.01374 0.00606 0.0045 0.2708 1.0000
6.250 0.7620 0.01395 0.00633 0.0053 0.2637 1.0000
6.500 0.7854 0.01419 0.00660 0.0061 0.2568 1.0000
6.750 0.8089 0.01441 0.00688 0.0068 0.2490 1.0000
7.000 0.8323 0.01466 0.00719 0.0076 0.2413 1.0000
7.250 0.8554 0.01493 0.00749 0.0084 0.2328 1.0000
7.500 0.8787 0.01519 0.00785 0.0092 0.2238 1.0000
7.750 0.9014 0.01549 0.00819 0.0101 0.2144 1.0000
8.000 0.9238 0.01582 0.00855 0.0109 0.2039 1.0000
8.250 0.9461 0.01617 0.00896 0.0118 0.1928 1.0000
8.500 0.9679 0.01657 0.00939 0.0127 0.1811 1.0000
8.750 0.9890 0.01703 0.00990 0.0136 0.1693 1.0000
9.000 1.0093 0.01755 0.01043 0.0146 0.1574 1.0000
9.250 1.0289 0.01813 0.01102 0.0157 0.1459 1.0000
9.500 1.0476 0.01878 0.01168 0.0168 0.1344 1.0000
9.750 1.0661 0.01943 0.01237 0.0180 0.1232 1.0000
10.000 1.0841 0.02011 0.01310 0.0191 0.1128 1.0000
10.250 1.1011 0.02086 0.01391 0.0204 0.1033 1.0000
10.500 1.1164 0.02171 0.01478 0.0217 0.0940 1.0000
10.750 1.1311 0.02258 0.01568 0.0231 0.0844 1.0000
11.000 1.1446 0.02349 0.01665 0.0246 0.0753 1.0000
11.250 1.1555 0.02453 0.01772 0.0262 0.0670 1.0000
11.500 1.1630 0.02574 0.01894 0.0280 0.0593 1.0000
11.750 1.1690 0.02690 0.02017 0.0301 0.0523 1.0000
12.000 1.1668 0.02837 0.02167 0.0327 0.0476 1.0000
12.250 1.1664 0.02999 0.02340 0.0343 0.0430 1.0000
12.500 1.1618 0.03236 0.02584 0.0349 0.0392 1.0000
12.750 1.1586 0.03503 0.02863 0.0347 0.0361 1.0000
13.000 1.1543 0.03816 0.03185 0.0338 0.0331 1.0000
13.250 1.1464 0.04195 0.03573 0.0324 0.0308 1.0000
13.500 1.1367 0.04616 0.04003 0.0307 0.0291 1.0000
13.750 1.1297 0.05013 0.04414 0.0291 0.0275 1.0000
14.000 1.1198 0.05455 0.04867 0.0272 0.0258 1.0000
14.250 1.1075 0.05939 0.05359 0.0251 0.0242 1.0000
14.500 1.0946 0.06438 0.05869 0.0229 0.0236 1.0000
14.750 1.0799 0.06974 0.06414 0.0205 0.0228 1.0000
15.000 1.0662 0.07508 0.06956 0.0181 0.0220 1.0000
15.250 1.0559 0.08015 0.07475 0.0157 0.0212 1.0000
15.500 1.0450 0.08546 0.08017 0.0133 0.0202 1.0000
15.750 1.0338 0.09095 0.08578 0.0107 0.0196 1.0000
16.000 1.0217 0.09680 0.09171 0.0079 0.0185 1.0000
16.250 1.0089 0.10284 0.09783 0.0050 0.0179 1.0000
16.500 0.9980 0.10869 0.10376 0.0021 0.0175 1.0000
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Polar data table (+)
Polar graphs
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