Abstract
This paper presents the analysis of effects on the airplane longitudinal stability reserve by the single tractor propeller at high engine power settings. The analysis was done within the terminal flight phases. The airplane has the original and modified horizontal tail shape. The horizontal tail modifications were applied to the second prototype of the “LASTA” airplane during the development of flight testing. The airplane stability problem was initiated by the rise of pilot average mass diverging in practice from the specification of 86 kg (190 lbs), as defined in aviation regulations and installation of measurement equipment. The “LASTA” airplane model is here analyzed for two different horizontal tail shapes by the combination of the calculating aerodynamics and flight testing methods. The paper makes the presentation of the introduction phase of the airplane design and construction process.
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