MH 104 15.28% (mh104-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 104 15.28% (mh104-il) Reynolds number: 100,000 Max Cl/Cd: 43.74 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh104-il-100000-n5.txt Download as CSV file: xf-mh104-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 104 15.28%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6160 0.11137 0.10630 -0.0073 1.0000 0.0185
-13.500 -0.6357 0.10216 0.09704 -0.0127 1.0000 0.0183
-13.250 -0.6521 0.09428 0.08910 -0.0176 1.0000 0.0179
-13.000 -0.6734 0.08585 0.08055 -0.0232 1.0000 0.0175
-12.750 -0.6984 0.07735 0.07187 -0.0292 1.0000 0.0175
-12.500 -0.7165 0.07073 0.06508 -0.0337 1.0000 0.0172
-12.250 -0.7356 0.06460 0.05873 -0.0377 1.0000 0.0172
-12.000 -0.7509 0.05959 0.05351 -0.0405 1.0000 0.0173
-11.750 -0.7617 0.05554 0.04926 -0.0420 1.0000 0.0172
-11.500 -0.7725 0.05189 0.04539 -0.0428 1.0000 0.0174
-11.250 -0.7808 0.04875 0.04200 -0.0426 1.0000 0.0177
-11.000 -0.7871 0.04595 0.03893 -0.0415 1.0000 0.0181
-10.750 -0.7916 0.04347 0.03616 -0.0398 1.0000 0.0186
-10.500 -0.7868 0.04148 0.03408 -0.0384 1.0000 0.0189
-10.250 -0.7820 0.03974 0.03229 -0.0366 1.0000 0.0195
-10.000 -0.7752 0.03813 0.03057 -0.0348 1.0000 0.0201
-9.750 -0.7658 0.03640 0.02871 -0.0331 1.0000 0.0209
-9.500 -0.7533 0.03470 0.02685 -0.0317 1.0000 0.0214
-9.250 -0.7398 0.03307 0.02509 -0.0302 1.0000 0.0222
-9.000 -0.7258 0.03159 0.02346 -0.0286 1.0000 0.0230
-8.750 -0.7143 0.03013 0.02202 -0.0269 1.0000 0.0239
-8.500 -0.7020 0.02895 0.02086 -0.0252 1.0000 0.0253
-8.250 -0.6888 0.02787 0.01971 -0.0235 1.0000 0.0273
-8.000 -0.6634 0.02647 0.01825 -0.0244 0.9494 0.0302
-7.500 -0.6127 0.02402 0.01546 -0.0251 0.8769 0.0387
-7.250 -0.5956 0.02303 0.01433 -0.0234 0.8500 0.0457
-7.000 -0.5795 0.02205 0.01328 -0.0215 0.8273 0.0561
-6.750 -0.5640 0.02098 0.01224 -0.0196 0.8072 0.0771
-6.500 -0.5495 0.01977 0.01130 -0.0177 0.7893 0.1267
-6.250 -0.5319 0.01898 0.01074 -0.0161 0.7729 0.1877
-6.000 -0.5112 0.01856 0.01034 -0.0149 0.7573 0.2312
-5.750 -0.4899 0.01825 0.01002 -0.0137 0.7425 0.2653
-5.500 -0.4680 0.01800 0.00974 -0.0125 0.7285 0.2969
-5.250 -0.4455 0.01781 0.00947 -0.0114 0.7153 0.3250
-5.000 -0.4225 0.01761 0.00921 -0.0103 0.7030 0.3475
-4.750 -0.3986 0.01742 0.00890 -0.0094 0.6912 0.3669
-4.500 -0.3737 0.01721 0.00859 -0.0087 0.6790 0.3842
-4.250 -0.3486 0.01702 0.00830 -0.0080 0.6677 0.4009
-4.000 -0.3235 0.01684 0.00801 -0.0073 0.6574 0.4175
-3.750 -0.2982 0.01665 0.00777 -0.0067 0.6466 0.4344
-3.500 -0.2727 0.01647 0.00754 -0.0061 0.6366 0.4518
-3.250 -0.2474 0.01631 0.00731 -0.0054 0.6279 0.4703
-3.000 -0.2217 0.01615 0.00714 -0.0048 0.6178 0.4897
-2.750 -0.1962 0.01602 0.00694 -0.0042 0.6094 0.5109
-2.500 -0.1704 0.01588 0.00680 -0.0036 0.6003 0.5326
-2.250 -0.1447 0.01576 0.00668 -0.0030 0.5924 0.5568
-2.000 -0.1187 0.01565 0.00659 -0.0024 0.5844 0.5822
-1.750 -0.0926 0.01557 0.00651 -0.0018 0.5772 0.6101
-1.500 -0.0662 0.01549 0.00647 -0.0013 0.5693 0.6397
-1.250 -0.0392 0.01544 0.00642 -0.0008 0.5626 0.6711
-1.000 -0.0113 0.01541 0.00646 -0.0005 0.5551 0.7034
-0.750 0.0177 0.01541 0.00646 -0.0003 0.5495 0.7364
-0.500 0.0483 0.01547 0.00657 -0.0005 0.5424 0.7689
-0.250 0.0806 0.01555 0.00664 -0.0009 0.5362 0.7998
0.000 0.1148 0.01568 0.00675 -0.0018 0.5299 0.8283
0.250 0.1517 0.01585 0.00690 -0.0032 0.5234 0.8523
0.500 0.1876 0.01603 0.00698 -0.0044 0.5185 0.8745
0.750 0.2240 0.01624 0.00718 -0.0060 0.5122 0.8940
1.000 0.2615 0.01643 0.00731 -0.0077 0.5065 0.9107
1.250 0.2991 0.01663 0.00740 -0.0094 0.5017 0.9257
1.500 0.3365 0.01686 0.00764 -0.0114 0.4956 0.9395
1.750 0.3775 0.01705 0.00776 -0.0140 0.4904 0.9506
2.000 0.4170 0.01722 0.00784 -0.0164 0.4858 0.9619
2.250 0.4560 0.01741 0.00806 -0.0189 0.4798 0.9731
2.500 0.4956 0.01755 0.00816 -0.0214 0.4749 0.9834
2.750 0.5371 0.01766 0.00821 -0.0244 0.4703 0.9925
3.000 0.5768 0.01780 0.00842 -0.0273 0.4643 1.0000
3.250 0.5980 0.01795 0.00855 -0.0264 0.4600 1.0000
3.500 0.6198 0.01810 0.00863 -0.0255 0.4564 1.0000
3.750 0.6406 0.01836 0.00898 -0.0246 0.4512 1.0000
4.000 0.6619 0.01859 0.00923 -0.0237 0.4465 1.0000
4.250 0.6840 0.01878 0.00938 -0.0227 0.4425 1.0000
4.500 0.7055 0.01905 0.00969 -0.0218 0.4381 1.0000
4.750 0.7265 0.01935 0.01008 -0.0209 0.4328 1.0000
5.000 0.7486 0.01957 0.01030 -0.0200 0.4284 1.0000
5.250 0.7710 0.01981 0.01052 -0.0191 0.4244 1.0000
5.500 0.7912 0.02019 0.01105 -0.0181 0.4186 1.0000
5.750 0.8131 0.02046 0.01134 -0.0172 0.4138 1.0000
6.000 0.8361 0.02066 0.01151 -0.0163 0.4097 1.0000
6.250 0.8554 0.02110 0.01214 -0.0152 0.4034 1.0000
6.500 0.8772 0.02136 0.01243 -0.0142 0.3982 1.0000
6.750 0.8995 0.02161 0.01270 -0.0133 0.3934 1.0000
7.000 0.9183 0.02205 0.01329 -0.0121 0.3867 1.0000
7.250 0.9407 0.02224 0.01351 -0.0112 0.3813 1.0000
7.500 0.9599 0.02265 0.01405 -0.0100 0.3749 1.0000
7.750 0.9800 0.02295 0.01443 -0.0089 0.3683 1.0000
8.000 1.0009 0.02321 0.01476 -0.0078 0.3623 1.0000
8.250 1.0184 0.02364 0.01534 -0.0064 0.3546 1.0000
8.500 1.0396 0.02382 0.01554 -0.0053 0.3485 1.0000
8.750 1.0550 0.02434 0.01626 -0.0037 0.3401 1.0000
9.000 1.0746 0.02457 0.01652 -0.0024 0.3332 1.0000
9.250 1.0889 0.02510 0.01724 -0.0007 0.3243 1.0000
9.500 1.1051 0.02547 0.01770 0.0008 0.3162 1.0000
9.750 1.1195 0.02591 0.01824 0.0026 0.3073 1.0000
10.000 1.1313 0.02650 0.01896 0.0045 0.2979 1.0000
10.250 1.1443 0.02694 0.01944 0.0064 0.2890 1.0000
10.500 1.1522 0.02766 0.02029 0.0086 0.2791 1.0000
10.750 1.1578 0.02845 0.02117 0.0111 0.2694 1.0000
11.000 1.1603 0.02921 0.02193 0.0140 0.2605 1.0000
11.250 1.1584 0.03041 0.02321 0.0167 0.2511 1.0000
11.500 1.1570 0.03183 0.02468 0.0187 0.2419 1.0000
11.750 1.1566 0.03335 0.02617 0.0202 0.2328 1.0000
12.000 1.1519 0.03551 0.02844 0.0213 0.2232 1.0000
12.250 1.1484 0.03774 0.03070 0.0221 0.2141 1.0000
12.500 1.1450 0.04007 0.03305 0.0226 0.2052 1.0000
12.750 1.1387 0.04296 0.03603 0.0227 0.1964 1.0000
13.000 1.1342 0.04567 0.03874 0.0228 0.1880 1.0000
13.250 1.1273 0.04883 0.04195 0.0226 0.1795 1.0000
13.500 1.1214 0.05196 0.04513 0.0223 0.1715 1.0000
13.750 1.1157 0.05509 0.04826 0.0219 0.1637 1.0000
14.000 1.1082 0.05863 0.05189 0.0213 0.1561 1.0000
14.250 1.1036 0.06174 0.05496 0.0208 0.1489 1.0000
14.500 1.0958 0.06563 0.05898 0.0198 0.1416 1.0000
14.750 1.0923 0.06884 0.06213 0.0191 0.1349 1.0000
15.000 1.0845 0.07300 0.06643 0.0178 0.1280 1.0000
15.250 1.0812 0.07632 0.06969 0.0170 0.1217 1.0000
15.500 1.0734 0.08069 0.07422 0.0155 0.1152 1.0000
15.750 1.0696 0.08430 0.07779 0.0143 0.1092 1.0000
16.000 1.0622 0.08877 0.08239 0.0127 0.1033 1.0000
16.250 1.0574 0.09275 0.08641 0.0113 0.0977 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 104 15.28% (mh104-il)