MH 44 9.66% (mh44-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 44 9.66% (mh44-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.57 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh44-il-1000000.txt Download as CSV file: xf-mh44-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 44 9.66%
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5669 0.07971 0.07821 -0.0101 1.0000 0.0069
-9.000 -0.5780 0.07293 0.07147 -0.0144 1.0000 0.0069
-8.750 -0.6292 0.05430 0.05274 -0.0289 1.0000 0.0065
-8.500 -0.6461 0.04917 0.04745 -0.0294 1.0000 0.0065
-7.250 -0.6260 0.02459 0.02108 -0.0264 0.9533 0.0054
-7.000 -0.6170 0.02078 0.01673 -0.0234 0.9338 0.0053
-6.750 -0.5894 0.02200 0.01787 -0.0228 0.9228 0.0059
-6.500 -0.5739 0.01920 0.01467 -0.0207 0.9120 0.0060
-6.250 -0.5531 0.01758 0.01281 -0.0194 0.9029 0.0060
-6.000 -0.5310 0.01610 0.01113 -0.0183 0.8947 0.0060
-5.750 -0.5089 0.01467 0.00951 -0.0171 0.8871 0.0060
-5.500 -0.4855 0.01352 0.00821 -0.0162 0.8797 0.0060
-5.250 -0.4623 0.01255 0.00712 -0.0151 0.8727 0.0060
-5.000 -0.4399 0.01139 0.00584 -0.0140 0.8654 0.0063
-4.750 -0.4157 0.01076 0.00511 -0.0132 0.8586 0.0067
-4.500 -0.3902 0.01025 0.00453 -0.0126 0.8514 0.0069
-4.250 -0.3649 0.00977 0.00395 -0.0119 0.8445 0.0070
-4.000 -0.3387 0.00935 0.00345 -0.0114 0.8371 0.0071
-3.500 -0.2857 0.00872 0.00268 -0.0104 0.8219 0.0083
-3.250 -0.2601 0.00823 0.00220 -0.0097 0.8144 0.0275
-3.000 -0.2357 0.00759 0.00188 -0.0091 0.8057 0.1034
-2.750 -0.2102 0.00719 0.00168 -0.0087 0.7973 0.1648
-2.500 -0.1846 0.00684 0.00154 -0.0083 0.7882 0.2276
-2.250 -0.1588 0.00651 0.00142 -0.0079 0.7779 0.2893
-2.000 -0.1325 0.00628 0.00131 -0.0075 0.7672 0.3391
-1.750 -0.1062 0.00606 0.00121 -0.0072 0.7555 0.3893
-1.500 -0.0805 0.00582 0.00113 -0.0067 0.7427 0.4533
-1.250 -0.0544 0.00563 0.00106 -0.0063 0.7287 0.5054
-1.000 -0.0283 0.00548 0.00100 -0.0058 0.7137 0.5548
-0.750 -0.0027 0.00532 0.00095 -0.0053 0.6981 0.6068
-0.500 0.0225 0.00515 0.00091 -0.0046 0.6821 0.6645
-0.250 0.0467 0.00498 0.00089 -0.0037 0.6656 0.7294
0.000 0.0696 0.00476 0.00087 -0.0025 0.6488 0.8058
0.250 0.0960 0.00455 0.00089 -0.0018 0.6318 0.8933
0.500 0.1574 0.00459 0.00095 -0.0092 0.6097 0.9478
0.750 0.2048 0.00474 0.00101 -0.0134 0.5884 0.9644
1.000 0.2395 0.00489 0.00107 -0.0148 0.5679 0.9765
1.250 0.2734 0.00505 0.00113 -0.0160 0.5475 0.9851
1.500 0.3113 0.00518 0.00118 -0.0182 0.5265 0.9906
1.750 0.3484 0.00533 0.00124 -0.0203 0.5060 0.9947
2.000 0.3881 0.00545 0.00126 -0.0229 0.4839 0.9979
2.250 0.4249 0.00558 0.00130 -0.0249 0.4623 1.0000
2.500 0.4505 0.00568 0.00133 -0.0245 0.4440 1.0000
2.750 0.4761 0.00579 0.00138 -0.0241 0.4245 1.0000
3.250 0.5273 0.00606 0.00151 -0.0232 0.3867 1.0000
3.500 0.5529 0.00621 0.00160 -0.0228 0.3668 1.0000
3.750 0.5784 0.00639 0.00169 -0.0223 0.3456 1.0000
4.000 0.6039 0.00657 0.00180 -0.0219 0.3245 1.0000
4.250 0.6294 0.00677 0.00193 -0.0215 0.3049 1.0000
4.500 0.6547 0.00698 0.00206 -0.0211 0.2827 1.0000
4.750 0.6799 0.00721 0.00221 -0.0206 0.2610 1.0000
5.000 0.7049 0.00748 0.00239 -0.0202 0.2376 1.0000
5.250 0.7301 0.00772 0.00257 -0.0197 0.2187 1.0000
5.500 0.7550 0.00799 0.00277 -0.0193 0.1983 1.0000
5.750 0.7797 0.00829 0.00299 -0.0188 0.1783 1.0000
6.000 0.8043 0.00859 0.00322 -0.0183 0.1588 1.0000
6.250 0.8288 0.00891 0.00347 -0.0178 0.1422 1.0000
6.500 0.8531 0.00924 0.00374 -0.0172 0.1243 1.0000
6.750 0.8773 0.00959 0.00402 -0.0167 0.1074 1.0000
7.000 0.9014 0.00994 0.00432 -0.0161 0.0937 1.0000
7.250 0.9253 0.01031 0.00464 -0.0155 0.0807 1.0000
7.500 0.9489 0.01070 0.00500 -0.0149 0.0683 1.0000
7.750 0.9721 0.01114 0.00537 -0.0143 0.0559 1.0000
8.000 0.9954 0.01154 0.00574 -0.0136 0.0466 1.0000
8.250 1.0182 0.01199 0.00616 -0.0129 0.0376 1.0000
8.500 1.0405 0.01249 0.00661 -0.0122 0.0294 1.0000
8.750 1.0629 0.01294 0.00705 -0.0114 0.0243 1.0000
9.000 1.0852 0.01341 0.00752 -0.0107 0.0201 1.0000
9.250 1.1067 0.01393 0.00805 -0.0098 0.0167 1.0000
9.500 1.1284 0.01442 0.00857 -0.0090 0.0141 1.0000
9.750 1.1501 0.01489 0.00907 -0.0081 0.0126 1.0000
10.000 1.1703 0.01548 0.00968 -0.0071 0.0106 1.0000
10.250 1.1908 0.01603 0.01028 -0.0062 0.0097 1.0000
10.500 1.2118 0.01648 0.01079 -0.0053 0.0089 1.0000
10.750 1.2316 0.01704 0.01137 -0.0043 0.0077 1.0000
11.000 1.2501 0.01769 0.01206 -0.0032 0.0063 1.0000
11.250 1.2692 0.01824 0.01265 -0.0021 0.0051 1.0000
11.500 1.2812 0.01941 0.01383 -0.0002 0.0022 1.0000
11.750 1.2969 0.02017 0.01468 0.0012 0.0021 1.0000
12.000 1.3094 0.02115 0.01574 0.0030 0.0016 1.0000
12.250 1.3159 0.02246 0.01718 0.0055 0.0013 1.0000
12.500 1.3135 0.02392 0.01881 0.0092 0.0012 1.0000
12.750 1.3174 0.02520 0.02020 0.0115 0.0012 1.0000
13.000 1.3215 0.02664 0.02175 0.0132 0.0012 1.0000
13.250 1.3234 0.02840 0.02364 0.0147 0.0012 1.0000
13.500 1.3266 0.03021 0.02556 0.0157 0.0011 1.0000
13.750 1.3254 0.03257 0.02807 0.0164 0.0011 1.0000
14.000 1.3249 0.03508 0.03071 0.0166 0.0011 1.0000
14.250 1.3241 0.03781 0.03356 0.0164 0.0011 1.0000
14.500 1.3160 0.04164 0.03755 0.0155 0.0011 1.0000
14.750 1.3068 0.04595 0.04201 0.0141 0.0011 1.0000
15.000 1.2967 0.05065 0.04686 0.0121 0.0011 1.0000
15.250 1.2886 0.05530 0.05164 0.0100 0.0011 1.0000
15.500 1.2696 0.06186 0.05836 0.0068 0.0011 1.0000
15.750 1.2536 0.06813 0.06476 0.0037 0.0011 1.0000
16.000 1.2326 0.07552 0.07230 0.0000 0.0011 1.0000
16.250 1.2128 0.08287 0.07977 -0.0037 0.0011 1.0000
16.500 1.1918 0.09063 0.08766 -0.0075 0.0011 1.0000
16.750 1.1657 0.09952 0.09667 -0.0118 0.0011 1.0000
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Polar data table (+)
Polar graphs
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