Accession Number : AD0801752

Title :   A METHOD OF DETERMINING SOME AERODYNAMIC COEFFICIENTS FROM SUPERSONIC FREE FLIGHT TESTS OF A ROLLING MISSILE,

Corporate Author : ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD

Personal Author(s) : Bolz, Ray E. ; Nicolaides, John D.

Report Date : DEC 1949

Pagination or Media Count : 56

Abstract : Based on the assumption that the aerodynamic forces acting at any point on a lifting surface are linearly dependent upon the local angle of attack at that point, the theory of pure rolling motion is applied to the experimentally observed motion of a finned missile in order to determine how well the actual motion is represented by the theory; determine the suitability of the Aerodynamic Range to the proposed free-flight roll technique; and determine certain aerodynamic coefficients associated with the motion. Values for the aerodynamic coefficients are also derived using the linearized supersonic theory and are compared with those obtained from experiment. The results indicate that the actual motion is well represented by the theory to within the small experimental errors and that excellent reproducibility of the aerodynamic coefficients in roll is obtained. Furthermore the results show a fairly good correlation with the linearized theory considering the degree of approximation associated with this theory when applied to aerodynamic surfaces of 16% thickness as employed on the missiles used in the reported tests. (Author)

Descriptors :   (*GUIDED MISSILES, ROLL), GUIDED MISSILE TRAJECTORIES, SUPERSONIC CHARACTERISTICS, FREE FLIGHT TRAJECTORIES, ANGLE OF ATTACK, AERODYNAMIC LOADING, FORCE(MECHANICS), MOTION, ERRORS, EQUATIONS OF MOTION, FINS, PRESSURE, LIFT, DETERMINATION.

Subject Categories : GUIDED MISSILE DYNAM, CONFIG & CNTRL SURFACES

Distribution Statement : APPROVED FOR PUBLIC RELEASE

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