Aerodynamic optimization, comparison, and trim design of canard and conventional high performance general aviation configurationsA design study has been conducted to optimize trim cruise flight of high performance general aviation canard aircraft which achieve minimum drag. In order to investigate the advantages and disadvantages of canard configured aircraft, corresponding conventional tail-aft 'baseline' aircraft were designed and used for comparison. Two-dimensional predictions were obtained by coupling inviscid results from a vortex panel multi-element program to a momentum integral boundary layer analysis. Using the results of the two-dimensional vortex panel analysis, a vortex lattice method was employed to predict the finite wing results. The analysis utilized a turbulent airfoil and a natural laminar airfoil which are two NASA state-of-the-art airfoil sections. The canard aircraft designs give quantitative results of wing and canard loadings, wing-to-canard moment arm ratios, and aspect ratio effects for trim cruise flight for a wide range of wing-to-canard area ratios. Both canard and baseline aircraft achieved a 25 to 30 percent improvement in performance over typical current technology aircraft, but high canard loading necessary for trim resulted in slightly poorer performance of the canard aircraft as compared to the baseline designs.
Document ID
19830035272
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Keith, M. W. (Gates Learjet Corp. Wichita, KS, United States)
Selberg, B. P. (Missouri-Rolla, University Rolla, MO, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1983
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 83-0058
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting