MH 104 15.28% (mh104-il)
MH 104 15.28% - Martin Hepperle MH 104 for stall controlled wind turbines
| Details | Dat file | Parser | |
|
(mh104-il) MH 104 15.28% Martin Hepperle MH 104 for stall controlled wind turbines Max thickness 15.2% at 26.4% chord. Max camber 1.9% at 31.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 104 15.28% 1.00000000 0.00000000 0.99619582 0.00017047 0.98515158 0.00100213 0.96764209 0.00285474 0.94421447 0.00556001 0.91510964 0.00906779 0.88074158 0.01357364 0.84177999 0.01916802 0.79894110 0.02580144 0.75297076 0.03334313 0.70461763 0.04158593 0.65461515 0.05026338 0.60366461 0.05906756 0.55242353 0.06766426 0.50149950 0.07571157 0.45144530 0.08287416 0.40276150 0.08882939 0.35589801 0.09329359 0.31131449 0.09592864 0.26917194 0.09626763 0.22927064 0.09424396 0.19167283 0.09023579 0.15672257 0.08451656 0.12469599 0.07727756 0.09585870 0.06875796 0.07046974 0.05918984 0.04874337 0.04880096 0.03081405 0.03786904 0.01681379 0.02676332 0.00687971 0.01592385 0.00143518 0.00647946 0.00053606 0.00370956 0.00006572 0.00112514 0.00001249 -0.00046881 0.00023032 -0.00191488 0.00079945 -0.00329201 0.00170287 -0.00470585 0.00354717 -0.00688469 0.00592084 -0.00912202 0.01810144 -0.01720842 0.03471169 -0.02488211 0.05589286 -0.03226730 0.08132751 -0.03908459 0.11073805 -0.04503763 0.14391397 -0.04986836 0.18067874 -0.05338180 0.22089879 -0.05551392 0.26433734 -0.05636585 0.31062190 -0.05605816 0.35933893 -0.05472399 0.40999990 -0.05254383 0.46204424 -0.04969990 0.51483073 -0.04637175 0.56767889 -0.04264894 0.61998250 -0.03859653 0.67114514 -0.03433153 0.72054815 -0.02996944 0.76758733 -0.02560890 0.81168064 -0.02134397 0.85227225 -0.01726049 0.88883823 -0.01343567 0.92088961 -0.00993849 0.94797259 -0.00679919 0.96977487 -0.00402321 0.98607009 -0.00180118 0.99640466 -0.00044469 1.00000000 0.00000000 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for MH 104 15.28% (mh104-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh104-il | 50,000 | 9 | 12 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 50,000 | 5 | 21.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 100,000 | 9 | 37.2 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 100,000 | 5 | 43.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 200,000 | 9 | 62.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 200,000 | 5 | 65 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 500,000 | 9 | 95.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 500,000 | 5 | 92.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 1,000,000 | 9 | 120.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 1,000,000 | 5 | 106.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||