MH33 (mh33-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH33 (mh33-il) Reynolds number: 50,000 Max Cl/Cd: 31.86 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh33-il-50000-n5.txt Download as CSV file: xf-mh33-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH33
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5379 0.09348 0.08655 -0.0144 1.0000 0.0327
-8.500 -0.5400 0.08890 0.08205 -0.0170 1.0000 0.0317
-8.250 -0.5440 0.08407 0.07731 -0.0201 1.0000 0.0309
-8.000 -0.5517 0.07833 0.07165 -0.0245 1.0000 0.0297
-7.750 -0.5595 0.07131 0.06454 -0.0296 1.0000 0.0280
-7.250 -0.5582 0.06287 0.05578 -0.0317 1.0000 0.0272
-7.000 -0.5558 0.05865 0.05137 -0.0320 1.0000 0.0271
-6.750 -0.5512 0.05453 0.04696 -0.0320 1.0000 0.0273
-6.250 -0.5361 0.04658 0.03844 -0.0309 1.0000 0.0282
-6.000 -0.5248 0.04347 0.03511 -0.0301 1.0000 0.0296
-5.750 -0.5107 0.04061 0.03196 -0.0291 1.0000 0.0313
-5.500 -0.4946 0.03756 0.02848 -0.0279 1.0000 0.0326
-5.250 -0.4763 0.03459 0.02502 -0.0265 1.0000 0.0336
-5.000 -0.4559 0.03182 0.02164 -0.0251 1.0000 0.0345
-4.750 -0.4338 0.02932 0.01869 -0.0236 1.0000 0.0360
-4.500 -0.4108 0.02721 0.01617 -0.0220 1.0000 0.0383
-4.250 -0.3898 0.02546 0.01435 -0.0207 1.0000 0.0459
-4.000 -0.3676 0.02384 0.01256 -0.0193 1.0000 0.0558
-3.750 -0.3449 0.02222 0.01081 -0.0179 1.0000 0.0772
-3.500 -0.3224 0.02030 0.00929 -0.0171 1.0000 0.1385
-3.250 -0.3040 0.01845 0.00835 -0.0160 1.0000 0.2945
-3.000 -0.2891 0.01708 0.00787 -0.0135 1.0000 0.4813
-2.750 -0.2747 0.01611 0.00765 -0.0094 1.0000 0.6669
-2.500 -0.2153 0.01584 0.00738 -0.0123 1.0000 0.9090
-2.250 -0.1304 0.01574 0.00656 -0.0233 1.0000 1.0000
-2.000 -0.1167 0.01560 0.00616 -0.0212 1.0000 1.0000
-1.750 -0.1021 0.01551 0.00583 -0.0192 1.0000 1.0000
-1.500 -0.0869 0.01546 0.00556 -0.0172 1.0000 1.0000
-1.250 -0.0709 0.01544 0.00528 -0.0154 1.0000 1.0000
-1.000 -0.0543 0.01545 0.00512 -0.0136 1.0000 1.0000
-0.750 -0.0371 0.01549 0.00500 -0.0120 1.0000 1.0000
-0.500 -0.0194 0.01555 0.00493 -0.0105 1.0000 1.0000
-0.250 -0.0013 0.01564 0.00490 -0.0090 1.0000 1.0000
0.000 0.0170 0.01576 0.00493 -0.0077 1.0000 1.0000
0.250 0.0354 0.01591 0.00496 -0.0064 1.0000 1.0000
0.500 0.0539 0.01609 0.00508 -0.0053 1.0000 1.0000
0.750 0.0723 0.01630 0.00526 -0.0042 1.0000 1.0000
1.000 0.0906 0.01655 0.00549 -0.0031 1.0000 1.0000
1.250 0.1367 0.01697 0.00595 -0.0076 0.9854 1.0000
1.500 0.1868 0.01735 0.00640 -0.0126 0.9687 1.0000
1.750 0.2330 0.01758 0.00673 -0.0165 0.9489 1.0000
2.000 0.2820 0.01773 0.00703 -0.0208 0.9289 1.0000
2.250 0.3265 0.01777 0.00729 -0.0239 0.9052 1.0000
2.500 0.3691 0.01771 0.00743 -0.0263 0.8790 1.0000
2.750 0.4089 0.01759 0.00750 -0.0278 0.8491 1.0000
3.000 0.4443 0.01747 0.00756 -0.0282 0.8127 1.0000
3.250 0.4795 0.01736 0.00768 -0.0283 0.7702 1.0000
3.500 0.5110 0.01735 0.00774 -0.0277 0.7202 1.0000
3.750 0.5386 0.01749 0.00785 -0.0263 0.6625 1.0000
4.000 0.5622 0.01781 0.00806 -0.0244 0.5996 1.0000
4.250 0.5833 0.01831 0.00839 -0.0222 0.5343 1.0000
4.500 0.6029 0.01894 0.00892 -0.0201 0.4686 1.0000
4.750 0.6223 0.01971 0.00949 -0.0183 0.4038 1.0000
5.000 0.6417 0.02057 0.01018 -0.0168 0.3411 1.0000
5.250 0.6610 0.02157 0.01098 -0.0154 0.2826 1.0000
5.500 0.6807 0.02268 0.01193 -0.0142 0.2294 1.0000
5.750 0.7008 0.02390 0.01303 -0.0131 0.1823 1.0000
6.000 0.7210 0.02531 0.01433 -0.0121 0.1455 1.0000
6.250 0.7412 0.02680 0.01583 -0.0109 0.1149 1.0000
6.500 0.7612 0.02850 0.01765 -0.0097 0.0931 1.0000
6.750 0.7816 0.03022 0.01954 -0.0086 0.0757 1.0000
7.000 0.8030 0.03249 0.02199 -0.0073 0.0660 1.0000
7.250 0.8216 0.03442 0.02403 -0.0062 0.0557 1.0000
7.500 0.8415 0.03686 0.02691 -0.0049 0.0488 1.0000
7.750 0.8589 0.03988 0.03007 -0.0038 0.0451 1.0000
8.000 0.8738 0.04374 0.03462 -0.0021 0.0431 1.0000
8.250 0.8828 0.04791 0.03943 -0.0003 0.0412 1.0000
8.500 0.8878 0.05152 0.04352 0.0013 0.0380 1.0000
8.750 0.8950 0.05374 0.04574 0.0023 0.0338 1.0000
9.000 0.8916 0.05801 0.05038 0.0037 0.0327 1.0000
9.250 0.8832 0.06243 0.05520 0.0049 0.0324 1.0000
9.500 0.8716 0.06668 0.05972 0.0057 0.0324 1.0000
9.750 0.8547 0.07087 0.06408 0.0063 0.0324 1.0000
10.000 0.8388 0.07537 0.06869 0.0053 0.0326 1.0000
10.250 0.8218 0.08090 0.07431 0.0024 0.0328 1.0000
10.500 0.8079 0.08706 0.08050 -0.0018 0.0330 1.0000
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Polar data table (+)
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