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Spin-Tunnel Investigation of the Spinning Characteristics of Typical Single-Engine General Aviation Airplane Designs. 1. Low-Wing Model A: Effects of Tail Configurations
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Author and Affiliation:
Burk, S. M., Jr.(NASA Langley Research Center, Hampton, VA, United States);
Bowman, J. S., Jr.(NASA Langley Research Center, Hampton, VA, United States);
White, W. L.(NASA Langley Research Center, Hampton, VA, United States)
Abstract: The effects of tail design on spin and recovery were investigated in a spin tunnel. A 1/11-scale model of a research airplane which represents a typical low-wing, single engine, light general aviation airplane was used. A tail design criterion for satisfactory spin recovery for light airplanes was evaluated. The effects of other geometric design features on the spin and recovery characteristics were also determined. Results indicate that the existing tail design criterion for light airplanes, which uses the tail damping power factor as a parameter, cannot be used to predict spin-recovery characteristics.
Publication Date: Sep 01, 1977
Document ID:
19770026167
(Acquired Nov 18, 1995)
Accession Number: 77N33111
Subject Category: AERODYNAMICS
Report/Patent Number: NASA-TP-1009, L-11227
Document Type: Technical Report
Publisher Information: United States
Contract/Grant/Task Num: RTOP 505-10-11-07
Financial Sponsor: NASA; United States
Organization Source: NASA Langley Research Center; Hampton, VA, United States
Description: 94p; In English; Original contains black and white illustrations
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: AERODYNAMIC CONFIGURATIONS; AIRCRAFT DESIGN; LOW WING AIRCRAFT; SPIN TESTS; TAIL ASSEMBLIES; DYNAMIC STABILITY; LIGHT AIRCRAFT; SCALE MODELS; SPIN DYNAMICS
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