Some Theoretical Considerations of a Stall Proof Airplane

Format:

Conference/Event

Author/Creator:

Chevalier, H. L., author.

Conference Name:

Business Aircraft Meeting and Exposition (1979-04-03 : Wichita, Kansas, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1979

Summary:

For 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 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

Notes:

Vendor supplied data

Publisher Number:

790604

Access Restriction:

Restricted for use by site license