MH 44 9.66% (mh44-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 44 9.66% (mh44-il) Reynolds number: 500,000 Max Cl/Cd: 74.53 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh44-il-500000-n5.txt Download as CSV file: xf-mh44-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6746 0.05336 0.05119 -0.0270 1.0000 0.0035
-9.250 -0.6960 0.04834 0.04602 -0.0291 1.0000 0.0035
-9.000 -0.7207 0.04167 0.03900 -0.0291 1.0000 0.0035
-8.750 -0.7289 0.03642 0.03335 -0.0282 1.0000 0.0035
-8.500 -0.7267 0.03215 0.02861 -0.0268 1.0000 0.0036
-8.250 -0.7172 0.02903 0.02511 -0.0256 1.0000 0.0036
-8.000 -0.7076 0.02557 0.02120 -0.0241 1.0000 0.0037
-7.750 -0.6852 0.02282 0.01806 -0.0245 0.9712 0.0038
-7.500 -0.6602 0.02107 0.01605 -0.0248 0.9534 0.0040
-7.250 -0.6382 0.01973 0.01446 -0.0240 0.9378 0.0040
-7.000 -0.6168 0.01883 0.01338 -0.0230 0.9247 0.0042
-6.750 -0.5945 0.01828 0.01271 -0.0221 0.9136 0.0046
-6.500 -0.5721 0.01748 0.01176 -0.0211 0.9032 0.0049
-6.250 -0.5495 0.01659 0.01069 -0.0200 0.8940 0.0051
-6.000 -0.5270 0.01569 0.00962 -0.0190 0.8854 0.0052
-5.750 -0.5039 0.01477 0.00855 -0.0180 0.8766 0.0053
-5.500 -0.4806 0.01399 0.00762 -0.0170 0.8688 0.0053
-5.250 -0.4568 0.01328 0.00679 -0.0161 0.8607 0.0054
-5.000 -0.4325 0.01265 0.00605 -0.0153 0.8531 0.0056
-4.750 -0.4078 0.01213 0.00542 -0.0146 0.8454 0.0057
-4.500 -0.3823 0.01166 0.00486 -0.0140 0.8378 0.0059
-4.250 -0.3572 0.01118 0.00425 -0.0133 0.8302 0.0063
-4.000 -0.3311 0.01078 0.00377 -0.0128 0.8219 0.0071
-3.750 -0.3050 0.01048 0.00339 -0.0123 0.8140 0.0087
-3.500 -0.2789 0.01011 0.00303 -0.0118 0.8051 0.0169
-3.250 -0.2529 0.00976 0.00273 -0.0113 0.7962 0.0368
-3.000 -0.2293 0.00908 0.00240 -0.0107 0.7866 0.1190
-2.750 -0.2045 0.00858 0.00218 -0.0102 0.7760 0.1978
-2.500 -0.1781 0.00836 0.00202 -0.0099 0.7648 0.2308
-2.250 -0.1520 0.00811 0.00188 -0.0095 0.7529 0.2745
-2.000 -0.1263 0.00784 0.00175 -0.0091 0.7402 0.3287
-1.750 -0.1001 0.00765 0.00162 -0.0087 0.7266 0.3696
-1.500 -0.0737 0.00750 0.00152 -0.0083 0.7121 0.4050
-1.250 -0.0474 0.00737 0.00143 -0.0079 0.6968 0.4422
-1.000 -0.0213 0.00724 0.00136 -0.0075 0.6809 0.4809
-0.750 0.0046 0.00712 0.00129 -0.0070 0.6647 0.5223
-0.500 0.0303 0.00700 0.00124 -0.0065 0.6484 0.5679
-0.250 0.0555 0.00688 0.00120 -0.0058 0.6319 0.6162
0.250 0.1041 0.00655 0.00117 -0.0041 0.5982 0.7342
0.500 0.1280 0.00637 0.00117 -0.0030 0.5806 0.8072
0.750 0.1618 0.00624 0.00122 -0.0040 0.5613 0.8887
1.000 0.2235 0.00635 0.00130 -0.0114 0.5364 0.9382
1.250 0.2685 0.00650 0.00135 -0.0151 0.5144 0.9577
1.500 0.3040 0.00666 0.00142 -0.0167 0.4938 0.9715
2.000 0.3717 0.00698 0.00156 -0.0193 0.4548 0.9915
2.250 0.4084 0.00714 0.00162 -0.0213 0.4340 0.9969
2.500 0.4439 0.00728 0.00169 -0.0231 0.4132 1.0000
2.750 0.4692 0.00744 0.00176 -0.0226 0.3939 1.0000
3.000 0.4946 0.00760 0.00185 -0.0222 0.3757 1.0000
3.250 0.5199 0.00777 0.00196 -0.0217 0.3564 1.0000
3.500 0.5452 0.00796 0.00208 -0.0213 0.3363 1.0000
3.750 0.5704 0.00816 0.00221 -0.0208 0.3172 1.0000
4.000 0.5956 0.00837 0.00235 -0.0203 0.2969 1.0000
4.250 0.6206 0.00861 0.00252 -0.0199 0.2766 1.0000
4.500 0.6456 0.00886 0.00270 -0.0194 0.2553 1.0000
4.750 0.6704 0.00913 0.00290 -0.0189 0.2360 1.0000
5.000 0.6952 0.00940 0.00311 -0.0184 0.2163 1.0000
5.250 0.7197 0.00970 0.00335 -0.0179 0.1970 1.0000
5.500 0.7442 0.01001 0.00360 -0.0174 0.1790 1.0000
5.750 0.7686 0.01032 0.00386 -0.0169 0.1618 1.0000
6.000 0.7930 0.01064 0.00414 -0.0163 0.1467 1.0000
6.250 0.8169 0.01100 0.00446 -0.0158 0.1298 1.0000
6.500 0.8407 0.01139 0.00479 -0.0152 0.1141 1.0000
6.750 0.8643 0.01178 0.00514 -0.0146 0.1001 1.0000
7.250 0.9108 0.01262 0.00590 -0.0133 0.0736 1.0000
7.500 0.9336 0.01308 0.00632 -0.0126 0.0622 1.0000
7.750 0.9566 0.01350 0.00676 -0.0119 0.0539 1.0000
8.000 0.9792 0.01394 0.00721 -0.0112 0.0466 1.0000
8.250 1.0012 0.01446 0.00772 -0.0104 0.0389 1.0000
8.500 1.0230 0.01496 0.00823 -0.0096 0.0326 1.0000
8.750 1.0447 0.01547 0.00878 -0.0087 0.0281 1.0000
9.000 1.0658 0.01603 0.00935 -0.0078 0.0240 1.0000
9.250 1.0862 0.01663 0.01002 -0.0068 0.0206 1.0000
9.500 1.1064 0.01722 0.01063 -0.0059 0.0173 1.0000
9.750 1.1250 0.01796 0.01141 -0.0047 0.0148 1.0000
10.000 1.1451 0.01849 0.01200 -0.0038 0.0127 1.0000
10.250 1.1631 0.01919 0.01273 -0.0026 0.0108 1.0000
10.500 1.1810 0.01987 0.01347 -0.0014 0.0092 1.0000
10.750 1.1981 0.02057 0.01421 -0.0002 0.0077 1.0000
11.000 1.2135 0.02139 0.01509 0.0013 0.0067 1.0000
11.250 1.2288 0.02215 0.01596 0.0027 0.0061 1.0000
11.500 1.2431 0.02293 0.01683 0.0042 0.0053 1.0000
11.750 1.2544 0.02381 0.01780 0.0061 0.0048 1.0000
12.000 1.2607 0.02481 0.01886 0.0087 0.0041 1.0000
12.250 1.2676 0.02583 0.02000 0.0108 0.0035 1.0000
12.500 1.2741 0.02702 0.02128 0.0126 0.0030 1.0000
12.750 1.2787 0.02848 0.02283 0.0142 0.0026 1.0000
13.000 1.2825 0.03013 0.02459 0.0154 0.0023 1.0000
13.250 1.2853 0.03201 0.02660 0.0164 0.0021 1.0000
13.500 1.2880 0.03403 0.02874 0.0170 0.0020 1.0000
13.750 1.2875 0.03653 0.03137 0.0173 0.0016 1.0000
14.000 1.2878 0.03911 0.03410 0.0172 0.0018 1.0000
14.250 1.2864 0.04206 0.03721 0.0167 0.0017 1.0000
14.500 1.2798 0.04588 0.04116 0.0156 0.0014 1.0000
14.750 1.2716 0.05014 0.04558 0.0141 0.0014 1.0000
15.000 1.2597 0.05519 0.05078 0.0119 0.0013 1.0000
15.250 1.2562 0.05916 0.05490 0.0101 0.0015 1.0000
15.500 1.2352 0.06607 0.06196 0.0067 0.0013 1.0000
15.750 1.2219 0.07192 0.06796 0.0039 0.0013 1.0000
16.000 1.2017 0.07923 0.07542 0.0002 0.0013 1.0000
16.250 1.1872 0.08567 0.08200 -0.0030 0.0014 1.0000
16.500 1.1671 0.09332 0.08978 -0.0068 0.0014 1.0000
16.750 1.1443 0.10166 0.09827 -0.0109 0.0014 1.0000
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Polar data table (+)
Polar graphs
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