Some theoretical considerations of a stall proof airplaneFor the stall proof airplane there should be a stabilizing pitching moment below the stall angle of attack of sufficient amount to prevent the attainment of the stall angle of attack which cannot be over-ridden by control deflections. This paper presents (1) a development of the moment equations to show the theoretical considerations of a stall proof airplane and (2) the nonlinear moment characteristics that must be obtained to satisfy the stall proof requirements. In addition, it is shown that an aerodynamic spoiler located on the under surface of the horizontal tail can be designed to meet these requirements of a stall proof airplane. Wind tunnel results are shown to validate assumptions and predictions.
Document ID
19790052723
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chevalier, H. L. (Texas A&M University College Station, Tex., United States)
Date Acquired
August 9, 2013
Publication Date
April 1, 1979
Subject Category
Aircraft Stability And Control
Report/Patent Number
SAE PAPER 790604
Meeting Information
Meeting: Society of Automotive Engineers, Business Aircraft Meeting and Exposition