MH 46 9.1% (mh46-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 46 9.1% (mh46-il) Reynolds number: 500,000 Max Cl/Cd: 74.08 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh46-il-500000-n5.txt Download as CSV file: xf-mh46-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 46 9.1%
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5841 0.08106 0.07894 -0.0053 1.0000 0.0040
-9.000 -0.5959 0.07435 0.07227 -0.0095 1.0000 0.0039
-8.750 -0.6120 0.06689 0.06487 -0.0153 1.0000 0.0039
-8.500 -0.6335 0.05667 0.05461 -0.0237 1.0000 0.0038
-8.250 -0.6525 0.04697 0.04463 -0.0270 1.0000 0.0037
-8.000 -0.6645 0.03893 0.03617 -0.0273 1.0000 0.0035
-7.750 -0.6740 0.03036 0.02686 -0.0257 1.0000 0.0033
-7.500 -0.6670 0.02531 0.02117 -0.0239 1.0000 0.0031
-7.250 -0.6514 0.02232 0.01773 -0.0225 1.0000 0.0031
-7.000 -0.6304 0.02006 0.01511 -0.0217 0.9894 0.0030
-6.750 -0.6004 0.01823 0.01293 -0.0227 0.9659 0.0030
-6.500 -0.5732 0.01679 0.01123 -0.0228 0.9460 0.0030
-6.250 -0.5498 0.01573 0.00996 -0.0219 0.9269 0.0031
-6.000 -0.5277 0.01481 0.00885 -0.0207 0.9094 0.0031
-5.750 -0.5053 0.01402 0.00790 -0.0195 0.8936 0.0032
-5.500 -0.4822 0.01333 0.00705 -0.0185 0.8790 0.0033
-5.250 -0.4585 0.01271 0.00629 -0.0176 0.8654 0.0034
-5.000 -0.4340 0.01218 0.00562 -0.0168 0.8525 0.0035
-4.750 -0.4090 0.01170 0.00499 -0.0160 0.8403 0.0037
-4.500 -0.3836 0.01129 0.00444 -0.0154 0.8286 0.0041
-4.250 -0.3578 0.01095 0.00397 -0.0148 0.8172 0.0046
-4.000 -0.3319 0.01056 0.00348 -0.0143 0.8058 0.0061
-3.750 -0.3058 0.01021 0.00310 -0.0138 0.7949 0.0121
-3.500 -0.2799 0.00986 0.00279 -0.0134 0.7844 0.0291
-3.250 -0.2554 0.00926 0.00246 -0.0129 0.7740 0.0906
-3.000 -0.2298 0.00888 0.00224 -0.0125 0.7632 0.1405
-2.750 -0.2033 0.00865 0.00206 -0.0122 0.7525 0.1734
-2.500 -0.1766 0.00845 0.00190 -0.0120 0.7420 0.2044
-2.250 -0.1505 0.00819 0.00176 -0.0116 0.7316 0.2524
-2.000 -0.1244 0.00793 0.00162 -0.0113 0.7209 0.3051
-1.750 -0.0977 0.00776 0.00151 -0.0110 0.7099 0.3437
-1.500 -0.0712 0.00757 0.00142 -0.0107 0.6990 0.3879
-1.250 -0.0448 0.00740 0.00135 -0.0104 0.6880 0.4319
-1.000 -0.0184 0.00725 0.00127 -0.0101 0.6765 0.4765
-0.750 0.0078 0.00710 0.00122 -0.0097 0.6646 0.5224
-0.500 0.0337 0.00695 0.00117 -0.0092 0.6521 0.5699
-0.250 0.0594 0.00679 0.00114 -0.0087 0.6391 0.6215
0.000 0.0842 0.00661 0.00111 -0.0080 0.6257 0.6807
0.250 0.1081 0.00639 0.00110 -0.0069 0.6118 0.7522
0.500 0.1325 0.00614 0.00111 -0.0059 0.5972 0.8384
0.750 0.1808 0.00607 0.00117 -0.0101 0.5787 0.9246
1.000 0.2361 0.00617 0.00120 -0.0161 0.5574 0.9577
1.250 0.2745 0.00630 0.00123 -0.0183 0.5377 0.9744
1.500 0.3077 0.00644 0.00128 -0.0195 0.5172 0.9879
1.750 0.3431 0.00658 0.00133 -0.0211 0.4975 0.9958
2.000 0.3789 0.00670 0.00137 -0.0230 0.4770 1.0000
2.500 0.4302 0.00697 0.00151 -0.0221 0.4395 1.0000
2.750 0.4558 0.00712 0.00159 -0.0217 0.4197 1.0000
3.000 0.4814 0.00729 0.00168 -0.0212 0.4003 1.0000
3.250 0.5071 0.00746 0.00179 -0.0208 0.3802 1.0000
3.500 0.5326 0.00765 0.00192 -0.0204 0.3596 1.0000
3.750 0.5582 0.00786 0.00206 -0.0200 0.3375 1.0000
4.000 0.5836 0.00808 0.00221 -0.0196 0.3157 1.0000
4.250 0.6088 0.00834 0.00239 -0.0192 0.2922 1.0000
4.500 0.6341 0.00860 0.00259 -0.0188 0.2682 1.0000
4.750 0.6590 0.00890 0.00281 -0.0183 0.2428 1.0000
5.000 0.6838 0.00923 0.00304 -0.0179 0.2166 1.0000
5.250 0.7084 0.00958 0.00331 -0.0174 0.1905 1.0000
5.500 0.7328 0.00996 0.00359 -0.0169 0.1656 1.0000
5.750 0.7570 0.01036 0.00390 -0.0164 0.1418 1.0000
6.000 0.7809 0.01080 0.00426 -0.0159 0.1171 1.0000
6.250 0.8046 0.01126 0.00463 -0.0153 0.0939 1.0000
6.500 0.8282 0.01172 0.00502 -0.0147 0.0754 1.0000
6.750 0.8515 0.01220 0.00544 -0.0141 0.0585 1.0000
7.000 0.8745 0.01272 0.00590 -0.0135 0.0437 1.0000
7.250 0.8976 0.01320 0.00637 -0.0128 0.0340 1.0000
7.500 0.9207 0.01368 0.00686 -0.0122 0.0275 1.0000
7.750 0.9430 0.01426 0.00747 -0.0114 0.0210 1.0000
8.000 0.9659 0.01472 0.00799 -0.0107 0.0180 1.0000
8.250 0.9876 0.01533 0.00862 -0.0099 0.0147 1.0000
8.500 1.0096 0.01587 0.00921 -0.0091 0.0122 1.0000
8.750 1.0313 0.01641 0.00978 -0.0084 0.0099 1.0000
9.000 1.0517 0.01711 0.01051 -0.0075 0.0079 1.0000
9.250 1.0729 0.01769 0.01118 -0.0066 0.0070 1.0000
9.500 1.0932 0.01832 0.01188 -0.0057 0.0059 1.0000
9.750 1.1110 0.01923 0.01287 -0.0045 0.0046 1.0000
10.000 1.1299 0.01996 0.01371 -0.0035 0.0038 1.0000
10.250 1.1471 0.02082 0.01469 -0.0022 0.0034 1.0000
10.500 1.1631 0.02176 0.01571 -0.0009 0.0029 1.0000
10.750 1.1758 0.02295 0.01702 0.0008 0.0026 1.0000
11.000 1.1852 0.02432 0.01854 0.0027 0.0024 1.0000
11.250 1.1946 0.02554 0.01990 0.0047 0.0023 1.0000
11.500 1.1988 0.02677 0.02127 0.0073 0.0023 1.0000
11.750 1.2002 0.02827 0.02291 0.0098 0.0022 1.0000
12.000 1.2018 0.02995 0.02474 0.0116 0.0021 1.0000
12.250 1.2006 0.03211 0.02705 0.0130 0.0021 1.0000
12.500 1.1996 0.03447 0.02958 0.0138 0.0020 1.0000
12.750 1.1984 0.03706 0.03234 0.0140 0.0020 1.0000
13.000 1.1929 0.04037 0.03584 0.0138 0.0019 1.0000
13.250 1.1889 0.04375 0.03937 0.0131 0.0019 1.0000
13.500 1.1809 0.04789 0.04369 0.0117 0.0019 1.0000
13.750 1.1739 0.05214 0.04810 0.0100 0.0019 1.0000
14.000 1.1630 0.05722 0.05335 0.0077 0.0019 1.0000
14.250 1.1493 0.06302 0.05931 0.0048 0.0019 1.0000
14.500 1.1358 0.06902 0.06547 0.0017 0.0019 1.0000
14.750 1.1215 0.07539 0.07198 -0.0016 0.0019 1.0000
15.000 1.1034 0.08274 0.07948 -0.0055 0.0019 1.0000
15.250 1.0835 0.09075 0.08764 -0.0097 0.0019 1.0000
15.500 1.0641 0.09893 0.09595 -0.0140 0.0019 1.0000
15.750 1.0452 0.10723 0.10437 -0.0182 0.0019 1.0000
16.000 1.0279 0.11544 0.11268 -0.0223 0.0020 1.0000
16.250 1.0058 0.12505 0.12240 -0.0272 0.0020 1.0000
16.500 0.9891 0.13370 0.13111 -0.0315 0.0021 1.0000
16.750 0.9679 0.14382 0.14134 -0.0365 0.0020 1.0000
17.000 0.9492 0.15384 0.15144 -0.0414 0.0021 1.0000
17.250 0.9284 0.16503 0.16270 -0.0469 0.0022 1.0000
17.500 0.9015 0.17924 0.17698 -0.0535 0.0023 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 46 9.1% (mh46-il)