Selecting Principal Parameters of Baseline Design Configuration for Light General Aviation Aircraft

descriptionPublicationkeyboard_double_arrow_right Article , Other literature type 05 Jun 2006Publisher:American Institute of Aeronautics and Astronautics (AIAA)Journal:24th AIAA Applied Aerodynamics Conference

Authors: K Ibrahim; Anshul Mohnot;

doi: 10.2514/6.2006-3316

Selecting Principal Parameters of Baseline Design Configuration for Light General Aviation Aircraft

- Summary
- Metrics

Abstract

Design and performance data of light general aviation aircraft (4 to 8 Pax including crew) have been analyzed employing figure of merit expressions and heuristic approach. Simple and effective correlations have been evolved for selecting principal parameters - take-off weight, empty weight, fuel weight, wing area and span, taper ratio, dihedral, flap and aileron areas, fuselage length, area of horizontal and vertical tailplanes, elevator and rudder, engine power and propeller diameter - of baseline design configuration for light general aviation aircraft. Nomenclature A

Impact byBIP!

	selected citations These citations are derived from selected sources. This is an alternative to the "Influence" indicator, which also reflects the overall/total impact of an article in the research community at large, based on the underlying citation network (diachronically).	3
	popularity This indicator reflects the "current" impact/attention (the "hype") of an article in the research community at large, based on the underlying citation network.	Average
	influence This indicator reflects the overall/total impact of an article in the research community at large, based on the underlying citation network (diachronically).	Top 10%
	impulse This indicator reflects the initial momentum of an article directly after its publication, based on the underlying citation network.	Average