Light Civil Turboprop Airplane Take-Off Weight Preliminary Design Estimation Method

Abstract

A method for preliminary design estimation of civil light turboprop airplane take-off weight, taking into account the requirements of aviation rules Part 23 “Airworthiness standards for civil light airplane” AP-23 (CS-23, FAR-23), has been developed. The analysis of statistical parameters and characteristics of civil light turboprop airplane has been held. New parameters changing ranges are established. Statistical parameters and characteristics of existing civil light airplanes are specified. A method for light civil turboprop airplane take-off weight preliminary design estimation in three approximations according to the Technical Requirements Specification and recommendations for its implementation is presented. Minimum take-off weight is the accepted as effectiveness criterion. An algorithm for light civil airplane take-off weight calculation in first approximation has been developed. To implement the take-off weight calculation method, software has been developed. It allows studying the influence of the wing geometric parameters (such as aspect ratio (\( \lambda \)), taper ratio (\( \eta \)), airfoil relative thickness (\( \bar{c} \)) and sweep angle (\( \chi \))) on aerodynamic performance, power-to-weight ratio and airplane mass characteristics and parameters. The software was tested in the calculation of modern light airplane, namely: A-Viator, Rysachok, King Air C90 GTx, Cessna 441, as well as An-14 and was used in the development of the preliminary design of the KhAI-90 civil light turboprop airplane.