Reduction of Stall-Spin Entry Tendencies Through Wing Aerodynamic Design

Format:

Conference/Event

Author/Creator:

Kroeger, R. A., author.

Conference Name:

National Business Aircraft Meeting and Engineering Display (1976-04-06 : Wichita, Kansas, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1976

Summary:

Results of recent wind tunnel tests and analyses are described which are aimed at helping to prevent spin entry after a stall by modifications to the aircraft wing. Simple add-on devices were utilized which modify the shape of the lift curve after stall, making it essentially flat to 30-40° angle of attack. It is hypothesized that this will greatly reduce the danger of spin entry. Further research will be aimed at laying a firmer theoretical and analytical basis for the approach and at incorporating the complete full scale airplane and its dynamics into the problem

Notes:

Vendor supplied data

Publisher Number:

760481

Access Restriction:

Restricted for use by site license