Wave Drag Reduction for Aircraft Fuselage-Wing Configurations. Volume I. Analyses and Results
Abstract
An optimization procedure has been developed to minimize the wave drag of an aircraft fuselage-wing configuration subject to constraints imposed by design requirements. The theory, methods, computer programs and results are presented in this report in two volumes. This volume describes analyses, results and the optimization procedure. The procedure makes use of the Latin Square sampling technique and the Three-Dimensional Method of Characteristics. The former is used to efficiently sample the family of configurations, and the latter is used to accurately calculate the wave drags of the sampled configurations. The calculated wave drag coefficients are then used to derive a functional dependence of the wave drag on the geometric variables that define the family of configurations. The minimum wave drag configuration can be obtained by minimizing the wave drag function subject to a given set of constraints. The wave drag reduction procedure is demonstrated using an F-4 type configuration as the baseline. The results are presented and discussed.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1976
- Accession Number
- ADA040997
Entities
People
- C. W. Chu
- H. Ziegler
- J. Der Jr.