Wing design with attainable leading-edge thrust considerations

Abstract

This paper presents a brief description of a means of introducing consideration of attainable leading-edge thrust estimated by empirical methods into the design of wings capable of high aerodynamic efficiency at subsonic or supersonic speeds. The relatively mild camber surfaces called for when leading-edge thrust forces are appreciable offer advantages in structural simplicity and in aerodynamic performance at off-design flight conditions. Inclusion of attainable thrust considerations in the linearized theory design process necessitates the use of optimization techniques based on candidate surfaces rather than the more usual candidate wing loading distributions. This causes some computational complexities, but also introduces compensating advantages. One of these is the ability to restrict the extent of candidate surfaces on the wing planform for special problems such as the design of mission adaptive surfaces or selection of flap systems. The validity of the design method is illustrated in comparisons of the results given by the present method for zero thrust cases with results given by other design methods. The new design capabilities offered by the computer program are discussed, and examples of program application to representative problems are given.