Accession Number : ADA111768

Title :   Theoretical and Experimental Supersonic Lateral-Directional Stability Characteristics,

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CENTER

Personal Author(s) : Lamb,Milton ; Sawyer,Wallace C ; Thomas,James L

PDF Url : ADA111768

Report Date : 14 May 1981

Pagination or Media Count : 8

Abstract : A program has been initiated at NASA Langley Research Center to assess several methods for estimation of lateral-directional stability. As a basis for comparison, experimental data are presented for a simple wing-body vertical tail configuration. The methods for estimating the characteristics include a second-order shock expansion and panel method (MISLIFT), a slender body and 'first-order' panel method (APAS), and a 'higher-order' panel method for linearized supersonic flow (PAN AIR). The results show that PAN AIR provides accurate estimates of these characteristics at moderate angles of attack for complete configurations with either single or twin vertical tails. APAS will provide estimates for complete configurations at zero angle of attack. However, MISLIFT will only provide estimates for the simplest body-vertical tail configurations at zero angle of attack. (Author)

Descriptors :   *Aerodynamic characteristics, Supersonic flow, Estimates, Mathematical prediction, Computer aided design, Panels, Roll, Pitch(Motion), Aerodynamic stability, Shock, Wing body configurations, Tail assemblies, Aerodynamic loading, Aircraft, Guided missiles

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE