FX 78-K-140 A/20 (fx78k140a20-il)
FX 78-K-140 A/20 - Wortmann FX 78-K-140 airfoil for use with flaps (K) A/20
| Details | Dat file | Parser | |
|
(fx78k140a20-il) FX 78-K-140 A/20 Wortmann FX 78-K-140 airfoil for use with flaps (K) A/20 Max thickness 14.1% at 43.5% chord. Max camber 4.4% at 43.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
FX 78-K-140 A/20 1.00000 0.00000 0.99893 0.00115 0.99572 0.00198 0.99039 0.00325 0.98296 0.00491 0.97347 0.00691 0.96194 0.00922 0.94844 0.01188 0.93301 0.01489 0.91573 0.01827 0.89668 0.02200 0.87592 0.02603 0.85355 0.03038 0.82967 0.03496 0.80438 0.03976 0.77779 0.04822 0.75000 0.05740 0.72114 0.06691 0.69134 0.07637 0.66072 0.08536 0.62941 0.09335 0.59755 0.10011 0.56526 0.10541 0.53270 0.10936 0.50000 0.11209 0.46730 0.11372 0.43474 0.11427 0.40245 0.11391 0.37059 0.11266 0.33928 0.11059 0.30866 0.10772 0.27886 0.10408 0.25000 0.09975 0.22221 0.09473 0.19562 0.08914 0.17033 0.08304 0.14645 0.07656 0.12408 0.06979 0.10332 0.06276 0.08427 0.05556 0.06699 0.04828 0.05156 0.04099 0.03806 0.03378 0.02653 0.02676 0.01704 0.02004 0.00961 0.01384 0.00428 0.00839 0.00107 0.00393 0.00000 0.00000 0.00107 -0.00244 0.00428 -0.00542 0.00961 -0.00833 0.01704 -0.01101 0.02653 -0.01346 0.03806 -0.01555 0.05156 -0.01732 0.06699 -0.01886 0.08427 -0.02025 0.10332 -0.02148 0.12408 -0.02253 0.14645 -0.02340 0.17033 -0.02418 0.19562 -0.02484 0.22221 -0.02537 0.25000 -0.02579 0.27886 -0.02610 0.30866 -0.02633 0.33928 -0.02651 0.37059 -0.02663 0.40245 -0.02669 0.43474 -0.02668 0.46730 -0.02660 0.50000 -0.02639 0.53270 -0.02609 0.56526 -0.02566 0.59755 -0.02512 0.62941 -0.02438 0.66072 -0.02348 0.69134 -0.02237 0.72114 -0.02109 0.75000 -0.01965 0.77779 -0.01773 0.80438 -0.01509 0.82967 -0.01188 0.85355 -0.00832 0.87592 -0.00543 0.89668 -0.00319 0.91573 -0.00150 0.93301 -0.00035 0.94844 0.00030 0.96194 0.00051 0.97347 0.00040 0.98296 0.00006 0.99039 -0.00032 0.99572 -0.00065 0.99893 -0.00082 1.00000 0.00000 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for FX 78-K-140 A/20 (fx78k140a20-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx78k140a20-il | 50,000 | 9 | 16.8 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140a20-il | 50,000 | 5 | 15.8 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140a20-il | 100,000 | 9 | 25.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140a20-il | 100,000 | 5 | 27.8 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140a20-il | 200,000 | 9 | 54.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140a20-il | 200,000 | 5 | 57.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140a20-il | 500,000 | 9 | 118.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140a20-il | 500,000 | 5 | 111.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140a20-il | 1,000,000 | 9 | 147.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140a20-il | 1,000,000 | 5 | 142.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||