EH 2.0/7.0 (eh2070-il)
EH 2.0/7.0 - John Yost EH 2.0/7.0 for tailless R/C aircraft
| Details | Dat file | Parser | |
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(eh2070-il) EH 2.0/7.0 John Yost EH 2.0/7.0 for tailless R/C aircraft Max thickness 7% at 28.7% chord. Max camber 2% at 25.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
EH 2.0/7.0 1.00000 0.00000 0.99901 0.00003 0.99606 0.00014 0.99114 0.00036 0.98429 0.00071 0.97553 0.00121 0.96489 0.00186 0.95241 0.00267 0.93815 0.00362 0.92216 0.00471 0.90451 0.00595 0.88526 0.00737 0.86448 0.00894 0.84227 0.01076 0.81871 0.01262 0.79389 0.01472 0.76791 0.01698 0.74088 0.01941 0.71289 0.02198 0.68406 0.02468 0.65451 0.02749 0.62435 0.03041 0.59369 0.03337 0.56267 0.03634 0.53140 0.03928 0.50000 0.04213 0.46861 0.04484 0.43733 0.04734 0.40631 0.04958 0.37566 0.05150 0.34549 0.05301 0.31549 0.05409 0.28711 0.05467 0.25912 0.05472 0.23209 0.05421 0.20611 0.05312 0.18129 0.05146 0.15773 0.04923 0.13522 0.04647 0.11474 0.04323 0.09549 0.03956 0.07784 0.03554 0.06185 0.03126 0.04759 0.02679 0.03511 0.02224 0.02447 0.01772 0.01571 0.01333 0.00886 0.00926 0.00394 0.00564 0.00099 0.00257 0.00000 0.00000 0.00099 -0.00220 0.00394 -0.00418 0.00886 -0.00600 0.01571 -0.00768 0.02447 -0.00913 0.03511 -0.01031 0.04759 -0.01125 0.06185 -0.01196 0.07784 -0.01247 0.09549 -0.01285 0.11474 -0.01314 0.13552 -0.01336 0.15773 -0.01360 0.18129 -0.01384 0.20611 -0.01412 0.23209 -0.01446 0.25912 -0.01487 0.28711 -0.01533 0.31594 -0.01583 0.34549 -0.01636 0.37566 -0.01689 0.40631 -0.01740 0.43733 -0.01785 0.46861 -0.01822 0.50000 -0.01846 0.53140 -0.01857 0.56267 -0.01851 0.59369 -0.01828 0.62435 -0.01787 0.65451 -0.01729 0.68406 -0.01651 0.71289 -0.01558 0.74088 -0.01452 0.76791 -0.01335 0.79389 -0.01209 0.81871 -0.01078 0.84227 -0.00921 0.86448 -0.00814 0.88526 -0.00687 0.90451 -0.00566 0.92216 -0.00455 0.93815 -0.00354 0.95241 -0.00264 0.96489 -0.00185 0.97553 -0.00120 0.98429 -0.00071 0.99114 -0.00036 0.99606 -0.00014 0.99901 -0.00004 1.00000 0.00000 |
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Similar airfoils
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Polars for EH 2.0/7.0 (eh2070-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| eh2070-il | 50,000 | 9 | 33.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2070-il | 50,000 | 5 | 33.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2070-il | 100,000 | 9 | 46.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2070-il | 100,000 | 5 | 45.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2070-il | 200,000 | 9 | 60 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2070-il | 200,000 | 5 | 58.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2070-il | 500,000 | 9 | 79.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2070-il | 500,000 | 5 | 75.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2070-il | 1,000,000 | 9 | 94.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2070-il | 1,000,000 | 5 | 86.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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