MH 42 8.94% (mh42-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 42 8.94% (mh42-il) Reynolds number: 200,000 Max Cl/Cd: 66.96 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh42-il-200000.txt Download as CSV file: xf-mh42-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 42 8.94%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4348 0.11251 0.10930 -0.0051 1.0000 0.0352
-10.000 -0.4340 0.10810 0.10491 -0.0072 1.0000 0.0353
-9.000 -0.5104 0.09434 0.09102 -0.0118 1.0000 0.0363
-8.750 -0.5035 0.09120 0.08789 -0.0113 1.0000 0.0373
-8.500 -0.4989 0.08792 0.08464 -0.0122 1.0000 0.0381
-8.250 -0.4963 0.08438 0.08114 -0.0136 1.0000 0.0392
-8.000 -0.4965 0.08052 0.07732 -0.0158 1.0000 0.0401
-7.750 -0.5000 0.07641 0.07327 -0.0188 1.0000 0.0409
-7.500 -0.5034 0.07149 0.06838 -0.0235 1.0000 0.0418
-7.250 -0.5022 0.06625 0.06311 -0.0282 1.0000 0.0428
-7.000 -0.4995 0.06049 0.05724 -0.0327 1.0000 0.0448
-6.750 -0.4969 0.05644 0.05252 -0.0368 1.0000 0.0477
-6.500 -0.4929 0.04908 0.04530 -0.0376 1.0000 0.0496
-6.250 -0.4791 0.04618 0.04240 -0.0374 1.0000 0.0513
-6.000 -0.4659 0.04305 0.03913 -0.0371 1.0000 0.0536
-5.750 -0.4541 0.03294 0.02784 -0.0342 1.0000 0.0237
-5.500 -0.4475 0.02846 0.02304 -0.0320 1.0000 0.0215
-5.250 -0.4386 0.02531 0.01945 -0.0290 1.0000 0.0196
-5.000 -0.4282 0.02247 0.01607 -0.0258 1.0000 0.0181
-4.750 -0.4015 0.02012 0.01330 -0.0256 0.9969 0.0175
-4.500 -0.3619 0.01799 0.01090 -0.0278 0.9905 0.0182
-4.250 -0.3210 0.01651 0.00927 -0.0303 0.9839 0.0215
-4.000 -0.2820 0.01503 0.00771 -0.0327 0.9767 0.0276
-3.750 -0.2414 0.01346 0.00607 -0.0351 0.9701 0.0487
-3.500 -0.2070 0.01178 0.00505 -0.0369 0.9604 0.1682
-3.250 -0.1710 0.01108 0.00467 -0.0388 0.9508 0.2619
-3.000 -0.1386 0.01041 0.00440 -0.0399 0.9403 0.3720
-2.750 -0.1132 0.00971 0.00426 -0.0394 0.9277 0.5173
-2.500 -0.0916 0.00920 0.00417 -0.0375 0.9143 0.6453
-2.250 -0.0708 0.00887 0.00414 -0.0351 0.9010 0.7510
-2.000 -0.0477 0.00870 0.00412 -0.0329 0.8884 0.8356
-1.750 -0.0155 0.00866 0.00407 -0.0326 0.8767 0.9008
-1.500 0.0278 0.00867 0.00396 -0.0350 0.8661 0.9425
-1.250 0.0760 0.00869 0.00380 -0.0386 0.8557 0.9696
-1.000 0.1278 0.00866 0.00359 -0.0432 0.8452 0.9892
-0.750 0.1677 0.00862 0.00340 -0.0458 0.8324 1.0000
-0.500 0.1881 0.00863 0.00326 -0.0444 0.8186 1.0000
-0.250 0.2096 0.00866 0.00318 -0.0431 0.8051 1.0000
0.000 0.2318 0.00871 0.00311 -0.0419 0.7919 1.0000
0.250 0.2546 0.00877 0.00307 -0.0409 0.7789 1.0000
0.500 0.2779 0.00884 0.00304 -0.0399 0.7660 1.0000
0.750 0.3016 0.00891 0.00303 -0.0390 0.7533 1.0000
1.000 0.3257 0.00900 0.00304 -0.0381 0.7406 1.0000
1.250 0.3500 0.00909 0.00306 -0.0373 0.7279 1.0000
1.500 0.3745 0.00918 0.00310 -0.0365 0.7151 1.0000
1.750 0.3991 0.00928 0.00313 -0.0357 0.7023 1.0000
2.000 0.4239 0.00938 0.00318 -0.0350 0.6891 1.0000
2.250 0.4489 0.00949 0.00324 -0.0343 0.6756 1.0000
2.500 0.4740 0.00960 0.00331 -0.0336 0.6617 1.0000
2.750 0.4993 0.00970 0.00341 -0.0329 0.6472 1.0000
3.000 0.5246 0.00982 0.00350 -0.0323 0.6322 1.0000
3.250 0.5499 0.00993 0.00359 -0.0316 0.6166 1.0000
3.500 0.5753 0.01005 0.00368 -0.0310 0.6005 1.0000
3.750 0.6007 0.01018 0.00382 -0.0304 0.5831 1.0000
4.000 0.6261 0.01031 0.00396 -0.0298 0.5640 1.0000
4.250 0.6513 0.01046 0.00408 -0.0292 0.5448 1.0000
4.500 0.6766 0.01062 0.00425 -0.0286 0.5225 1.0000
4.750 0.7017 0.01081 0.00446 -0.0279 0.4991 1.0000
5.000 0.7265 0.01103 0.00465 -0.0273 0.4733 1.0000
5.250 0.7511 0.01128 0.00489 -0.0267 0.4447 1.0000
5.500 0.7754 0.01158 0.00515 -0.0260 0.4127 1.0000
5.750 0.7991 0.01196 0.00546 -0.0253 0.3776 1.0000
6.000 0.8222 0.01242 0.00583 -0.0246 0.3388 1.0000
6.250 0.8447 0.01298 0.00631 -0.0239 0.2946 1.0000
6.500 0.8663 0.01366 0.00684 -0.0231 0.2478 1.0000
6.750 0.8870 0.01448 0.00745 -0.0223 0.1987 1.0000
7.000 0.9071 0.01540 0.00818 -0.0215 0.1547 1.0000
7.250 0.9266 0.01643 0.00904 -0.0206 0.1185 1.0000
7.500 0.9449 0.01760 0.01006 -0.0195 0.0882 1.0000
7.750 0.9623 0.01886 0.01124 -0.0182 0.0650 1.0000
8.000 0.9786 0.02027 0.01265 -0.0167 0.0518 1.0000
8.250 0.9940 0.02181 0.01424 -0.0151 0.0433 1.0000
8.500 1.0070 0.02373 0.01612 -0.0134 0.0361 1.0000
8.750 1.0265 0.02451 0.01713 -0.0123 0.0295 1.0000
9.000 1.0379 0.02711 0.01981 -0.0104 0.0250 1.0000
9.250 1.0545 0.02786 0.02070 -0.0092 0.0197 1.0000
9.500 1.0636 0.03125 0.02421 -0.0074 0.0171 1.0000
9.750 1.0763 0.03398 0.02725 -0.0057 0.0162 1.0000
10.000 1.0869 0.03653 0.03013 -0.0038 0.0153 1.0000
10.250 1.0927 0.03956 0.03350 -0.0019 0.0149 1.0000
10.500 1.0924 0.04271 0.03699 0.0005 0.0148 1.0000
10.750 1.0851 0.04581 0.04040 0.0033 0.0147 1.0000
11.000 1.0743 0.04914 0.04400 0.0053 0.0148 1.0000
11.250 1.0607 0.05284 0.04797 0.0064 0.0148 1.0000
11.500 1.0461 0.05687 0.05224 0.0065 0.0149 1.0000
11.750 1.0298 0.06147 0.05706 0.0056 0.0151 1.0000
12.000 1.0123 0.06663 0.06243 0.0036 0.0152 1.0000
12.250 0.9939 0.07246 0.06844 0.0007 0.0153 1.0000
12.500 0.9752 0.07896 0.07511 -0.0032 0.0154 1.0000
12.750 0.9557 0.08629 0.08258 -0.0080 0.0156 1.0000
13.000 0.9351 0.09466 0.09109 -0.0138 0.0157 1.0000
13.250 0.9135 0.10420 0.10075 -0.0202 0.0159 1.0000
13.500 0.8944 0.11397 0.11058 -0.0264 0.0163 1.0000
13.750 0.7795 0.11669 0.11360 -0.0240 0.0169 1.0000
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Polar data table (+)
Polar graphs
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