A Semiempirical Method for Predicting Aerodynamics of Trailing Edge Flaps
Abstract
An Improved Semi empirical Method has been developed to estimate the static aerodynamics of configurations that use a trailing edge flap for control. The method is based on deflecting the full aft-located lifting surface an amount that allows the normal force coefficient to be equal to that generated by the deflected flap. A transfer in pitching moments and a modified axial force coefficient is derived to complete the set of static aerodynamics. The method is derived using theoretical methods that are a part of the 1998 version of the Naval Surface Warfare Center aeroprediction code and two sets of experimental data. Comparison of the improved method to available data shows the method to give satisfactory results over the practical range that trailing edge flaps are contemplated for use. However, additional wind tunnel data is needed to refine and expand the applicability of the method. This is particularly true for transonic Mach numbers and for supersonic Mach numbers where the angle of attack and control deflection are of the same sign.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 2001
- Accession Number
- ADA396632
Entities
People
- Frankie G. Moore
- Tom C. Hymer
Organizations
- Naval Surface Warfare Center