MH33 (mh33-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH33 (mh33-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.17 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh33-il-1000000.txt Download as CSV file: xf-mh33-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5502 0.07941 0.07784 -0.0177 1.0000 0.0048
-8.500 -0.5549 0.07464 0.07310 -0.0206 1.0000 0.0049
-8.250 -0.5655 0.06936 0.06786 -0.0248 1.0000 0.0048
-8.000 -0.5737 0.06298 0.06145 -0.0299 1.0000 0.0048
-7.750 -0.5777 0.05641 0.05479 -0.0331 1.0000 0.0048
-7.500 -0.5805 0.05059 0.04885 -0.0341 1.0000 0.0048
-7.250 -0.5823 0.04557 0.04368 -0.0335 1.0000 0.0049
-7.000 -0.5826 0.04134 0.03928 -0.0318 1.0000 0.0050
-6.750 -0.5808 0.03761 0.03536 -0.0295 1.0000 0.0051
-6.500 -0.5755 0.03477 0.03234 -0.0273 1.0000 0.0053
-6.250 -0.5676 0.03219 0.02959 -0.0250 1.0000 0.0055
-6.000 -0.5565 0.02930 0.02647 -0.0231 0.9998 0.0057
-5.750 -0.5288 0.02578 0.02262 -0.0243 0.9981 0.0062
-5.500 -0.4995 0.02246 0.01893 -0.0252 0.9962 0.0069
-5.250 -0.4706 0.01728 0.01310 -0.0253 0.9944 0.0061
-5.000 -0.4398 0.01551 0.01110 -0.0259 0.9926 0.0066
-4.750 -0.4099 0.01369 0.00900 -0.0262 0.9903 0.0066
-4.500 -0.3793 0.01189 0.00698 -0.0265 0.9882 0.0062
-4.250 -0.3460 0.01137 0.00641 -0.0278 0.9863 0.0072
-4.000 -0.3126 0.01043 0.00538 -0.0289 0.9846 0.0075
-3.750 -0.2787 0.00927 0.00405 -0.0300 0.9831 0.0070
-3.500 -0.2430 0.00856 0.00322 -0.0316 0.9819 0.0068
-3.250 -0.2115 0.00808 0.00263 -0.0322 0.9788 0.0068
-3.000 -0.1787 0.00775 0.00219 -0.0331 0.9756 0.0073
-2.750 -0.1454 0.00732 0.00181 -0.0342 0.9726 0.0320
-2.500 -0.1145 0.00650 0.00153 -0.0352 0.9694 0.1697
-2.250 -0.0882 0.00606 0.00139 -0.0350 0.9634 0.2525
-1.750 -0.0375 0.00498 0.00116 -0.0343 0.9501 0.5064
-1.500 -0.0121 0.00466 0.00106 -0.0337 0.9425 0.5850
-1.250 0.0120 0.00436 0.00099 -0.0328 0.9328 0.6618
-1.000 0.0363 0.00408 0.00093 -0.0318 0.9223 0.7379
-0.750 0.0597 0.00381 0.00089 -0.0306 0.9100 0.8143
-0.500 0.0825 0.00365 0.00090 -0.0290 0.8953 0.8828
-0.250 0.1066 0.00363 0.00091 -0.0277 0.8774 0.9203
0.000 0.1313 0.00368 0.00090 -0.0267 0.8555 0.9414
0.250 0.1568 0.00376 0.00089 -0.0258 0.8283 0.9561
0.500 0.1833 0.00388 0.00089 -0.0252 0.7961 0.9673
0.750 0.2146 0.00404 0.00091 -0.0258 0.7590 0.9751
1.000 0.2458 0.00423 0.00094 -0.0265 0.7186 0.9823
1.250 0.2842 0.00444 0.00097 -0.0288 0.6714 0.9852
1.500 0.3204 0.00468 0.00100 -0.0307 0.6192 0.9888
1.750 0.3542 0.00493 0.00107 -0.0321 0.5665 0.9926
2.000 0.3896 0.00517 0.00112 -0.0339 0.5164 0.9954
2.250 0.4258 0.00543 0.00117 -0.0359 0.4628 0.9983
2.500 0.4578 0.00569 0.00125 -0.0371 0.4111 1.0000
2.750 0.4802 0.00595 0.00135 -0.0361 0.3648 1.0000
3.000 0.5027 0.00621 0.00146 -0.0351 0.3237 1.0000
3.250 0.5252 0.00647 0.00158 -0.0341 0.2843 1.0000
3.500 0.5476 0.00675 0.00172 -0.0331 0.2454 1.0000
3.750 0.5700 0.00704 0.00187 -0.0321 0.2099 1.0000
4.000 0.5920 0.00738 0.00205 -0.0311 0.1712 1.0000
4.250 0.6144 0.00771 0.00227 -0.0301 0.1391 1.0000
4.500 0.6369 0.00803 0.00248 -0.0291 0.1117 1.0000
4.750 0.6592 0.00840 0.00271 -0.0281 0.0834 1.0000
5.000 0.6814 0.00882 0.00298 -0.0271 0.0552 1.0000
5.250 0.7046 0.00914 0.00324 -0.0263 0.0408 1.0000
5.500 0.7280 0.00946 0.00352 -0.0255 0.0295 1.0000
5.750 0.7517 0.00981 0.00383 -0.0247 0.0201 1.0000
6.000 0.7755 0.01019 0.00421 -0.0240 0.0128 1.0000
6.250 0.7998 0.01052 0.00454 -0.0234 0.0099 1.0000
6.500 0.8227 0.01112 0.00511 -0.0226 0.0031 1.0000
6.750 0.8465 0.01163 0.00571 -0.0218 0.0024 1.0000
7.000 0.8698 0.01223 0.00642 -0.0209 0.0021 1.0000
7.250 0.8927 0.01290 0.00721 -0.0200 0.0019 1.0000
7.500 0.9148 0.01371 0.00816 -0.0190 0.0019 1.0000
7.750 0.9357 0.01473 0.00934 -0.0178 0.0018 1.0000
8.000 0.9550 0.01600 0.01081 -0.0163 0.0018 1.0000
8.250 0.9730 0.01757 0.01261 -0.0146 0.0019 1.0000
8.500 0.9878 0.01978 0.01513 -0.0125 0.0019 1.0000
8.750 0.9954 0.02362 0.01951 -0.0094 0.0021 1.0000
9.000 0.9980 0.02804 0.02445 -0.0061 0.0024 1.0000
9.250 0.9909 0.03331 0.03025 -0.0023 0.0026 1.0000
9.500 0.9824 0.03772 0.03504 0.0009 0.0027 1.0000
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Polar data table (+)
Polar graphs
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