AH 93-157 (ah93157-il)
AH 93-157 - Althaus AH 93-157 airfoil
| Details | Dat file | Parser | |
|
(ah93157-il) AH 93-157 Althaus AH 93-157 airfoil Max thickness 15.7% at 39.6% chord. Max camber 3.5% at 41.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH 93-157 1.00000 -0.00221 0.99124 0.00018 0.97859 0.00326 0.96180 0.00711 0.94302 0.01149 0.92371 0.01612 0.90430 0.02092 0.88486 0.02584 0.86540 0.03089 0.84592 0.03606 0.82641 0.04134 0.80686 0.04672 0.78725 0.05218 0.76758 0.05769 0.74797 0.06318 0.72855 0.06856 0.70932 0.07374 0.69025 0.07869 0.67128 0.08336 0.65236 0.08773 0.63345 0.09179 0.61452 0.09553 0.59556 0.09894 0.57653 0.10204 0.55746 0.10480 0.53831 0.10725 0.51912 0.10938 0.49987 0.11120 0.48058 0.11271 0.46126 0.11391 0.44191 0.11479 0.42256 0.11538 0.40320 0.11565 0.38386 0.11561 0.36453 0.11525 0.34523 0.11458 0.32598 0.11358 0.30679 0.11226 0.28766 0.11059 0.26863 0.10858 0.24973 0.10621 0.23098 0.10347 0.21237 0.10033 0.19395 0.09679 0.17573 0.09283 0.15777 0.08842 0.14011 0.08356 0.12281 0.07823 0.10595 0.07241 0.08960 0.06612 0.07388 0.05934 0.05894 0.05207 0.04501 0.04440 0.03256 0.03656 0.02223 0.02906 0.01443 0.02244 0.00893 0.01688 0.00514 0.01223 0.00256 0.00824 0.00092 0.00470 0.00010 0.00147 0.00010 -0.00155 0.00094 -0.00462 0.00275 -0.00765 0.00557 -0.01058 0.00953 -0.01341 0.01491 -0.01621 0.02219 -0.01906 0.03205 -0.02197 0.04489 -0.02486 0.06042 -0.02753 0.07777 -0.02987 0.09618 -0.03185 0.11521 -0.03351 0.13463 -0.03491 0.15429 -0.03609 0.17413 -0.03710 0.19410 -0.03796 0.21414 -0.03869 0.23426 -0.03930 0.25442 -0.03981 0.27462 -0.04022 0.29486 -0.04055 0.31514 -0.04081 0.33544 -0.04099 0.35577 -0.04112 0.37612 -0.04118 0.39649 -0.04120 0.41687 -0.04117 0.43725 -0.04109 0.45762 -0.04097 0.47799 -0.04080 0.49834 -0.04058 0.51867 -0.04030 0.53897 -0.03996 0.55923 -0.03955 0.57946 -0.03906 0.59965 -0.03848 0.61979 -0.03781 0.63988 -0.03703 0.65991 -0.03613 0.67987 -0.03509 0.69974 -0.03389 0.71952 -0.03253 0.73917 -0.03097 0.75866 -0.02919 0.77795 -0.02715 0.79703 -0.02482 0.81595 -0.02213 0.83491 -0.01905 0.85411 -0.01562 0.87350 -0.01201 0.89232 -0.00868 0.91048 -0.00593 0.92814 -0.00385 0.94541 -0.00252 0.96226 -0.00196 0.97822 -0.00206 0.99105 -0.00225 1.00000 -0.00221 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for AH 93-157 (ah93157-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah93157-il | 50,000 | 9 | 4.7 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93157-il | 50,000 | 5 | 14.4 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93157-il | 100,000 | 9 | 40 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93157-il | 100,000 | 5 | 37.5 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93157-il | 200,000 | 9 | 74.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93157-il | 200,000 | 5 | 66.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93157-il | 500,000 | 9 | 100.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93157-il | 500,000 | 5 | 92 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93157-il | 1,000,000 | 9 | 120.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93157-il | 1,000,000 | 5 | 112.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||