THEORETICAL AND EXPERIMENTAL STUDIES ON AIRLOADS RELATED TO HYPERSONIC AEROELASTIC PROBLEMS OF GENERAL SLENDER POINTED CONFIGURATIONS
Abstract
Two approximate techniques for e timating inviscid hypersonic airloads on pointed slender configurations, originally developed for airfoil and bodies of revolution are extended to cover other cross-sectional shapes. The first, an unsteady shock-expansion method, is illustrated by application to two ogives ith earlyelliptic, similar cross sections. A a check, tical analysis, Differential equations, Integral equations.) (*Wings, *Flutter, Mathematical analysis.) Two approximate techniques for e timating inviscid hypersonic airloads on pointed slender configurations, originally developed for airfoil and bodies of revolution are extended to cover other cross-sectional shapes. The first, an unsteady shock-expansion method, is illustrated by application to two ogives ith earlyelliptic, similar cross sections. A a check, steady-flow pressure and total lateral force were measured on two such models, one with a straight and the other with a cambered body axis, in the range of the hypersonic parameter 1.1 less than or equal to K less than or equal to 1.75. Experimental pressures are substantially higher than the predicted ones, although the shapes of the circumferential distributions are in goo agreem nt. The second technique, a variationalRitz procedure valid for lower values of the hypersonic parameter, is applied to a cone and an ogive, both with faired triangular cross sections, following a suitable transformation. Included is a preliminary investigation of the effects of aerodynamic nonlinearity, arising from largeamplitude oscillations, on the flutter characteristics of a typical wing section. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1961
- Accession Number
- AD0267036
Entities
People
- Garabed Zartarian
- Pao Tan Hsu
Organizations
- Massachusetts Institute of Technology