AH 95-160 (ah95160-il)
AH 95-160 - Althaus AH 95-160 airfoil
| Details | Dat file | Parser | |
|
(ah95160-il) AH 95-160 Althaus AH 95-160 airfoil Max thickness 16% at 38.9% chord. Max camber 5.6% at 44.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH 95-160 1.00020 -0.00151 0.99043 0.00078 0.97609 0.00450 0.95715 0.00962 0.93617 0.01541 0.91469 0.02147 0.89312 0.02764 0.87154 0.03386 0.84996 0.04012 0.82838 0.04640 0.80681 0.05269 0.78524 0.05899 0.76367 0.06528 0.74209 0.07158 0.72058 0.07786 0.69922 0.08407 0.67810 0.09017 0.65730 0.09608 0.63695 0.10170 0.61707 0.10695 0.59763 0.11177 0.57854 0.11613 0.55967 0.12001 0.54089 0.12341 0.52210 0.12635 0.50324 0.12883 0.48429 0.13086 0.46525 0.13245 0.44616 0.13359 0.42704 0.13428 0.40789 0.13453 0.38868 0.13433 0.36939 0.13370 0.35001 0.13264 0.33058 0.13116 0.31113 0.12928 0.29170 0.12700 0.27233 0.12432 0.25307 0.12126 0.23393 0.11781 0.21496 0.11397 0.19621 0.10974 0.17773 0.10512 0.15956 0.10011 0.14177 0.09471 0.12444 0.08892 0.10769 0.08276 0.09162 0.07623 0.07638 0.06939 0.06220 0.06229 0.04931 0.05504 0.03799 0.04781 0.02846 0.04084 0.02080 0.03440 0.01489 0.02864 0.01041 0.02354 0.00707 0.01903 0.00458 0.01500 0.00276 0.01138 0.00147 0.00808 0.00061 0.00505 0.00013 0.00222 0.00000 -0.00043 0.00025 -0.00306 0.00097 -0.00571 0.00221 -0.00828 0.00399 -0.01068 0.00632 -0.01288 0.00921 -0.01489 0.01273 -0.01679 0.01707 -0.01865 0.02253 -0.02052 0.02956 -0.02239 0.03876 -0.02421 0.05086 -0.02585 0.06651 -0.02717 0.08566 -0.02816 0.10687 -0.02889 0.12869 -0.02935 0.15089 -0.02958 0.17339 -0.02964 0.19597 -0.02958 0.21855 -0.02940 0.24109 -0.02913 0.26357 -0.02877 0.28601 -0.02834 0.30841 -0.02785 0.33079 -0.02730 0.35315 -0.02670 0.37549 -0.02605 0.39782 -0.02534 0.42015 -0.02458 0.44247 -0.02376 0.46479 -0.02288 0.48711 -0.02194 0.50943 -0.02094 0.53175 -0.01987 0.55407 -0.01875 0.57639 -0.01755 0.59871 -0.01630 0.62103 -0.01502 0.64335 -0.01371 0.66567 -0.01241 0.68800 -0.01112 0.71036 -0.00987 0.73279 -0.00864 0.75530 -0.00743 0.77776 -0.00624 0.80018 -0.00508 0.82266 -0.00399 0.84497 -0.00301 0.86686 -0.00218 0.88812 -0.00154 0.90849 -0.00112 0.92790 -0.00095 0.94629 -0.00103 0.96329 -0.00140 0.97825 -0.00201 0.99040 -0.00281 0.99980 -0.00367 |
Dat file parser warnings
|
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for AH 95-160 (ah95160-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah95160-il | 50,000 | 9 | 5.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 50,000 | 5 | 12.8 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 100,000 | 9 | 23.9 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 100,000 | 5 | 24.8 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 200,000 | 9 | 65.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 200,000 | 5 | 73.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 500,000 | 9 | 130.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 500,000 | 5 | 128.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 1,000,000 | 9 | 173.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 1,000,000 | 5 | 163.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||