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A parametric investigation was made to determine which aerodynamic design modifications can be made to improve significantly the performance of light airplanes. The study was made around a typical low wing and a typical high wing airplane. Performance parameters selected for comparison with the baseline configuration are: speed for best range, maximum level speed, specific range, maximum rate of climb, and speed for maximum rate of climb. It is shown that significant improvements in these performance parameters are possible by aerodynamic refinements. It is also shown that by application of modern high lift technology significant improvements in take-off and landing performance can be obtained. A similar analysis was employed to improve stability and handling characteristics such as spiral stability, dutch roll stability, and gust response.

This paper presents results of a systematic experimental investigation of parameters which affect sound transmission through general aviation structures. Parameters studied include angle of sound incidence, panel curvature, panel stresses, and edge conditions for bare panels; pane thickness, spacing, inclination of window panes, and depressurization for dual pane windows; densities of hard foam and sound absorption materials, air gaps, and trim panel thickness for multilayered panels. Based on the study, some promising methods for reducing interior noise in general aviation airplanes are discussed.

Significant progress has been made in several areas of research relating to general aviation technology at the University of Kansas. This paper describes the design and operation of the major systems of a fixed-base visual and instrument flight simulator, now operating as a valuable research tool in configuration analysis, handling qualities research, control system and cockpit design studies, and other areas. Also included is a report on the status of a NASA sponsored project on improvements in light aircraft design, with attention focused on the wing design, high lift systems, spoiler lateral controls, and a direct lift system. Results of theoretical and wind tunnel studies in these areas are being incorporated in a Cessna 177 Cardinal for an extensive flight test program next year. A brief discussion is also given of two projects recently initiated which will investigate the use of separate auxiliary control surfaces for stability augmentation and for gust alleviation.

The paper compares the size, weight and performance characteristics of hydraulic, pneumatic and electro-mechanical actuators for general aviation flight controls. Mathematical models for each type are presented. Actuator designs for specific control tasks in realistic light airplane applications are compared with each other. It is shown that electro-mechanical actuators utilizing the recently developed samarium-cobalt technology have significant advantages in terms of size and weight requirements while yielding very fast response.

The paper presents the results of a large number of systematic tests to determine noise reduction characteristics of general aviation materials. Effects of material type (metallic and composite), thickness, panel stiffening, vibration damping materials, sound absorption materials and pressurization on noise reduction are included. Several promising methods for reducing cabin interior noise in light airplanes are discussed based on the results.