COMPUTATIONAL TECHNIQUE AND DESIGN GUIDE DEFINING DEPARTURE/SPIN RESISTANT FOREBODY CONFIGURATIONS DEVELOPMENT

AIRPLANE FOREBODY DESIGN HAS CONSISTENTLY DEMONSTRATED SIGNIFICANT INFLUENCES ON BOTH STATIC AND ROTATIONAL AERODYNAMICS AND, CONSEQUENTLY, ON HIGH ANGLE-OF-ATTACK FLIGHT CHARACTERISTICS AND SPIN BEHAVIOR. AN EXTENSIVE HIGH ANGLE-OF-ATTACK DATA BASE FOR MILITARY CONFIGURATIONS HAS BEEN GENERATED USING THE ROTARY BALANCE AT THE NASA LANGLEY 20-FOOT SPIN TUNNEL. THIS DATA BASE WILL BE UTILIZED TO CORRELATE STATIC AND ROTATIONAL AERODYNAMIC CHARACTERISTICS WITH FOREBODY DESIGN PARAMETERS. THE RESULTS OF THIS ANALYSIS WILL BE FORMULATED INTO A PRELIMINARY DESIGN GUIDE, WHICH WILL DEMONSTRATE THE RELATIONSHIP OF HIGH ANGLE-OF-ATTACK AERODYNAMIC CHARACTERISTICS WITH FOREBODY DESIGN. THIS TYPE OF INFORMATION IS REQUIRED AS A PRE-REQUISITE FOR THE FORMULATION OF COMPUTATIONAL TECHNIQUES.