Accession Number : AD0442900


Title :   A GENERAL INVESTIGATION OF HYPERSONIC STABILITY AND CONTROL UNDER TRIMMED FLIGHT CONDITIONS


Descriptive Note : Quarterly technical rept. no. 2.


Corporate Author : FLIGHT SCIENCES LAB INC BUFFALO NY


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/442900.pdf


Report Date : 24 Jun 1964


Pagination or Media Count : 86


Abstract : Analytic equations were determined for the force and moment coefficients and stability derivatives of various shapes in Newtonian flow. These results follow from an application of the general method formerly presented. Equations for all the important derivatives of the cone at zero sideslip and roll were determined as a function of angle of attack. The constants in these simple equations can be determined numerically for any C.G. location and any cone angle. For slender cones, with certain restrictions on the C.G. location, the constants in the stability derivative equations were determined analytically. Similar results were obtained for the delta planform with diamond shape cross-section perpendicular to the longitudinal axis. A preliminary investigation was made of the effects of bluntness on the constants in the stability equations. An initial investigation was undertaken into other hypersonic theories, besides Newtonian, for predicting surface pressures.


Descriptors :   *NOSE CONES , ROLL , DAMPING , MOMENTS , MATHEMATICAL ANALYSIS , PRESSURE , EQUATIONS , HYPERSONIC CHARACTERISTICS , CONICAL BODIES , DELTA WINGS , BLUNT BODIES , FORCE(MECHANICS) , HYPERSONIC FLOW , CONTROL , STABILITY


Subject Categories : Guided Missiles


Distribution Statement : APPROVED FOR PUBLIC RELEASE