MH 91 14.98% (mh91-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 91 14.98% (mh91-il) Reynolds number: 50,000 Max Cl/Cd: 25.16 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh91-il-50000-n5.txt Download as CSV file: xf-mh91-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 91 14.98%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6941 0.07958 0.07218 -0.0232 1.0000 0.0406
-11.250 -0.7119 0.07452 0.06697 -0.0254 1.0000 0.0404
-11.000 -0.7316 0.06990 0.06217 -0.0266 1.0000 0.0403
-10.750 -0.7497 0.06592 0.05796 -0.0265 1.0000 0.0404
-10.500 -0.7642 0.06244 0.05424 -0.0254 1.0000 0.0404
-10.250 -0.7757 0.05930 0.05083 -0.0235 1.0000 0.0406
-10.000 -0.7809 0.05636 0.04763 -0.0216 1.0000 0.0409
-9.750 -0.7737 0.05376 0.04492 -0.0205 1.0000 0.0416
-9.500 -0.7666 0.05115 0.04212 -0.0192 1.0000 0.0421
-9.250 -0.7569 0.04854 0.03928 -0.0179 1.0000 0.0427
-9.000 -0.7440 0.04603 0.03653 -0.0168 1.0000 0.0435
-8.750 -0.7279 0.04362 0.03385 -0.0158 1.0000 0.0446
-8.500 -0.7095 0.04138 0.03128 -0.0149 1.0000 0.0464
-8.250 -0.6886 0.03950 0.02934 -0.0143 1.0000 0.0486
-8.000 -0.6665 0.03780 0.02755 -0.0138 1.0000 0.0517
-7.750 -0.6403 0.03605 0.02562 -0.0134 1.0000 0.0547
-7.500 -0.6180 0.03454 0.02419 -0.0129 1.0000 0.0582
-7.250 -0.5958 0.03320 0.02274 -0.0121 1.0000 0.0633
-7.000 -0.5777 0.03190 0.02150 -0.0111 1.0000 0.0689
-6.750 -0.5620 0.03065 0.02031 -0.0097 1.0000 0.0761
-6.500 -0.5502 0.02951 0.01922 -0.0078 1.0000 0.0855
-6.250 -0.5449 0.02852 0.01833 -0.0050 1.0000 0.0971
-6.000 -0.5473 0.02770 0.01766 -0.0009 1.0000 0.1107
-5.750 -0.5190 0.02549 0.01609 -0.0031 0.9765 0.1785
-5.500 -0.4946 0.02363 0.01520 -0.0044 0.9556 0.3229
-5.250 -0.4684 0.02285 0.01491 -0.0045 0.9355 0.4343
-5.000 -0.4405 0.02263 0.01499 -0.0038 0.9170 0.5188
-4.750 -0.4102 0.02280 0.01531 -0.0027 0.8996 0.5825
-4.500 -0.3794 0.02308 0.01553 -0.0017 0.8823 0.6259
-4.250 -0.3468 0.02342 0.01575 -0.0009 0.8654 0.6563
-4.000 -0.3188 0.02367 0.01581 0.0004 0.8482 0.6826
-3.750 -0.2878 0.02401 0.01598 0.0014 0.8315 0.7041
-3.500 -0.2590 0.02428 0.01606 0.0026 0.8149 0.7242
-3.250 -0.2310 0.02451 0.01609 0.0038 0.7984 0.7427
-3.000 -0.2027 0.02471 0.01610 0.0048 0.7824 0.7599
-2.750 -0.1742 0.02488 0.01607 0.0057 0.7666 0.7760
-2.500 -0.1460 0.02500 0.01600 0.0066 0.7512 0.7916
-2.000 -0.0917 0.02514 0.01577 0.0084 0.7214 0.8222
-1.750 -0.0587 0.02525 0.01570 0.0082 0.7055 0.8350
-1.500 -0.0248 0.02532 0.01561 0.0077 0.6898 0.8472
-1.250 0.0053 0.02534 0.01547 0.0077 0.6747 0.8606
-1.000 0.0335 0.02534 0.01531 0.0079 0.6604 0.8747
-0.750 0.0751 0.02530 0.01508 0.0059 0.6453 0.8844
-0.500 0.1079 0.02525 0.01488 0.0053 0.6309 0.8965
-0.250 0.1373 0.02525 0.01477 0.0049 0.6159 0.9095
0.000 0.1783 0.02517 0.01455 0.0025 0.6004 0.9185
0.250 0.2109 0.02512 0.01439 0.0016 0.5861 0.9295
0.500 0.2449 0.02504 0.01418 0.0003 0.5724 0.9398
0.750 0.2815 0.02492 0.01392 -0.0014 0.5591 0.9488
1.000 0.3149 0.02492 0.01385 -0.0029 0.5445 0.9586
1.250 0.3516 0.02487 0.01372 -0.0050 0.5304 0.9673
1.500 0.3875 0.02481 0.01358 -0.0069 0.5174 0.9756
1.750 0.4223 0.02473 0.01336 -0.0085 0.5055 0.9840
2.000 0.4590 0.02473 0.01334 -0.0109 0.4917 0.9920
2.250 0.4954 0.02476 0.01334 -0.0132 0.4788 0.9997
2.500 0.5155 0.02486 0.01334 -0.0122 0.4694 1.0000
2.750 0.5349 0.02511 0.01360 -0.0113 0.4585 1.0000
3.000 0.5542 0.02534 0.01379 -0.0103 0.4491 1.0000
3.250 0.5734 0.02558 0.01401 -0.0092 0.4395 1.0000
3.500 0.5922 0.02593 0.01435 -0.0082 0.4301 1.0000
3.750 0.6111 0.02620 0.01458 -0.0070 0.4217 1.0000
4.000 0.6293 0.02663 0.01505 -0.0059 0.4126 1.0000
4.250 0.6479 0.02694 0.01533 -0.0046 0.4046 1.0000
4.500 0.6654 0.02745 0.01588 -0.0034 0.3961 1.0000
4.750 0.6834 0.02785 0.01628 -0.0021 0.3885 1.0000
5.000 0.7005 0.02836 0.01680 -0.0008 0.3809 1.0000
5.250 0.7171 0.02890 0.01741 0.0006 0.3730 1.0000
5.500 0.7353 0.02929 0.01774 0.0021 0.3669 1.0000
5.750 0.7489 0.03011 0.01871 0.0036 0.3586 1.0000
6.000 0.7670 0.03049 0.01905 0.0051 0.3527 1.0000
6.250 0.7795 0.03139 0.02007 0.0068 0.3453 1.0000
6.500 0.7944 0.03204 0.02077 0.0084 0.3389 1.0000
6.750 0.8126 0.03248 0.02114 0.0099 0.3337 1.0000
7.000 0.8199 0.03370 0.02259 0.0120 0.3262 1.0000
7.250 0.8364 0.03424 0.02312 0.0136 0.3205 1.0000
7.500 0.8486 0.03515 0.02410 0.0154 0.3148 1.0000
7.750 0.8553 0.03641 0.02551 0.0175 0.3083 1.0000
8.000 0.8737 0.03688 0.02597 0.0189 0.3032 1.0000
8.250 0.8792 0.03825 0.02747 0.0210 0.2973 1.0000
8.500 0.8832 0.03972 0.02907 0.0231 0.2913 1.0000
8.750 0.9042 0.04012 0.02944 0.0242 0.2866 1.0000
9.000 0.9013 0.04211 0.03161 0.0264 0.2808 1.0000
9.250 0.8977 0.04412 0.03376 0.0285 0.2750 1.0000
9.500 0.9228 0.04430 0.03392 0.0293 0.2703 1.0000
9.750 0.9033 0.04747 0.03726 0.0316 0.2651 1.0000
10.000 0.8469 0.05341 0.04332 0.0338 0.2595 1.0000
10.250 0.8793 0.05280 0.04272 0.0349 0.2551 1.0000
10.500 0.7379 0.07216 0.06213 0.0275 0.2424 1.0000
10.750 0.7616 0.07190 0.06193 0.0288 0.2393 1.0000
11.000 0.8001 0.06955 0.05962 0.0312 0.2371 1.0000
11.500 0.7470 0.08424 0.07436 0.0252 0.2218 1.0000
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Polar data table (+)
Polar graphs
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