MH33 (mh33-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH33 (mh33-il) Reynolds number: 100,000 Max Cl/Cd: 46.12 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh33-il-100000.txt Download as CSV file: xf-mh33-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5351 0.10201 0.09713 -0.0097 1.0000 0.0887
-8.750 -0.5511 0.09905 0.09429 -0.0159 1.0000 0.0904
-8.500 -0.5692 0.09556 0.09090 -0.0223 1.0000 0.0908
-8.250 -0.5315 0.09068 0.08596 -0.0132 1.0000 0.0963
-8.000 -0.5341 0.08722 0.08256 -0.0151 1.0000 0.1001
-7.750 -0.5553 0.08327 0.07870 -0.0227 1.0000 0.1033
-7.500 -0.5583 0.07834 0.07380 -0.0251 1.0000 0.1055
-7.250 -0.5439 0.07538 0.07089 -0.0216 1.0000 0.1094
-7.000 -0.5665 0.07199 0.06712 -0.0306 1.0000 0.1175
-6.750 -0.5450 0.06702 0.06247 -0.0261 1.0000 0.1206
-6.250 -0.4874 0.04856 0.04425 -0.0256 1.0000 0.1396
-6.000 -0.4872 0.04416 0.03979 -0.0259 1.0000 0.1480
-5.750 -0.4851 0.04015 0.03565 -0.0260 1.0000 0.1598
-5.500 -0.5003 0.03999 0.03367 -0.0286 1.0000 0.0628
-5.250 -0.4838 0.03489 0.02785 -0.0266 1.0000 0.0496
-5.000 -0.4668 0.03113 0.02369 -0.0249 1.0000 0.0455
-4.750 -0.4458 0.02768 0.01938 -0.0226 1.0000 0.0408
-4.500 -0.4230 0.02593 0.01721 -0.0209 1.0000 0.0397
-4.250 -0.4004 0.02371 0.01467 -0.0194 1.0000 0.0395
-4.000 -0.3776 0.02113 0.01189 -0.0180 1.0000 0.0404
-3.750 -0.3558 0.01953 0.01030 -0.0168 1.0000 0.0479
-3.500 -0.3340 0.01797 0.00873 -0.0153 1.0000 0.0566
-3.250 -0.3131 0.01632 0.00723 -0.0135 1.0000 0.0874
-3.000 -0.2993 0.01308 0.00591 -0.0113 1.0000 0.3938
-2.750 -0.2864 0.01176 0.00581 -0.0075 1.0000 0.6655
-2.500 -0.2169 0.01172 0.00599 -0.0117 1.0000 0.9578
-2.250 -0.1281 0.01167 0.00533 -0.0239 1.0000 1.0000
-2.000 -0.1180 0.01154 0.00501 -0.0211 1.0000 1.0000
-1.750 -0.1060 0.01146 0.00476 -0.0186 1.0000 1.0000
-1.500 -0.0926 0.01142 0.00456 -0.0162 1.0000 1.0000
-1.250 -0.0783 0.01142 0.00437 -0.0140 1.0000 1.0000
-1.000 -0.0628 0.01145 0.00426 -0.0120 1.0000 1.0000
-0.750 -0.0465 0.01151 0.00420 -0.0102 1.0000 1.0000
-0.500 -0.0293 0.01159 0.00418 -0.0085 1.0000 1.0000
-0.250 -0.0115 0.01171 0.00421 -0.0071 1.0000 1.0000
0.000 0.0065 0.01185 0.00429 -0.0057 1.0000 1.0000
0.250 0.0247 0.01203 0.00437 -0.0044 1.0000 1.0000
0.500 0.0430 0.01225 0.00455 -0.0033 1.0000 1.0000
0.750 0.0611 0.01251 0.00477 -0.0022 1.0000 1.0000
1.000 0.0789 0.01281 0.00506 -0.0012 1.0000 1.0000
1.250 0.1089 0.01323 0.00550 -0.0028 0.9958 1.0000
1.500 0.1714 0.01377 0.00611 -0.0104 0.9810 1.0000
1.750 0.2297 0.01403 0.00645 -0.0168 0.9631 1.0000
2.000 0.2898 0.01409 0.00666 -0.0232 0.9450 1.0000
2.250 0.3530 0.01388 0.00668 -0.0297 0.9267 1.0000
2.500 0.4084 0.01347 0.00647 -0.0342 0.9041 1.0000
2.750 0.4548 0.01299 0.00616 -0.0365 0.8766 1.0000
3.000 0.4905 0.01259 0.00596 -0.0365 0.8402 1.0000
3.250 0.5225 0.01229 0.00571 -0.0356 0.7949 1.0000
3.500 0.5487 0.01223 0.00561 -0.0338 0.7378 1.0000
3.750 0.5714 0.01243 0.00564 -0.0315 0.6718 1.0000
4.000 0.5917 0.01283 0.00580 -0.0291 0.5991 1.0000
4.250 0.6108 0.01340 0.00613 -0.0267 0.5235 1.0000
4.500 0.6291 0.01410 0.00651 -0.0245 0.4462 1.0000
4.750 0.6471 0.01493 0.00700 -0.0225 0.3699 1.0000
5.000 0.6652 0.01588 0.00761 -0.0207 0.2988 1.0000
5.250 0.6835 0.01700 0.00840 -0.0191 0.2358 1.0000
5.500 0.7021 0.01821 0.00933 -0.0176 0.1819 1.0000
5.750 0.7213 0.01961 0.01052 -0.0160 0.1401 1.0000
6.000 0.7405 0.02124 0.01188 -0.0147 0.1084 1.0000
6.250 0.7615 0.02272 0.01340 -0.0133 0.0852 1.0000
6.500 0.7835 0.02471 0.01547 -0.0122 0.0709 1.0000
6.750 0.8079 0.02721 0.01831 -0.0109 0.0637 1.0000
7.000 0.8305 0.03025 0.02145 -0.0099 0.0579 1.0000
7.250 0.8490 0.03241 0.02422 -0.0080 0.0507 1.0000
7.500 0.8670 0.03565 0.02778 -0.0064 0.0473 1.0000
7.750 0.8767 0.04133 0.03383 -0.0047 0.0450 1.0000
8.000 0.8842 0.04380 0.03715 -0.0018 0.0416 1.0000
8.250 0.8877 0.04809 0.04199 0.0004 0.0403 1.0000
8.500 0.8863 0.05307 0.04741 0.0023 0.0412 1.0000
8.750 0.8801 0.05822 0.05292 0.0039 0.0419 1.0000
9.000 0.8725 0.06304 0.05797 0.0050 0.0429 1.0000
9.250 0.8630 0.06795 0.06302 0.0058 0.0439 1.0000
9.500 0.8019 0.08174 0.07733 0.0000 0.0738 1.0000
9.750 0.7947 0.08668 0.08227 -0.0022 0.0722 1.0000
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Polar data table (+)
Polar graphs
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