ESDU 74010:1974
$62.40
Low-speed drag coefficient increment at zero lift due to full-span split flaps
| Published By | Publication Date | Number of Pages |
| ESDU | 1974-11-01 | 16 |
ESDU 74010 gives curves of drag increment at zero lift as a function of wing thickness/chord ratio and flap deflection for various flap chord/wing chord ratios between 0.1 and 0.4. The curves are based on a correlation of experimental data from 10 sources, and are accurate to within 10 per cent for rectangular wings and within 20 per cent for straight-tapered swept and unswept wings. To correct the data for application to part-span flaps, ESDU Aero F.02.01.07 is used.
