The aerothermoelastic characteristics of a tactical missile operating at near zero angle of attack in the low hypersonic speed range have been studies. An integrated digital computer program has been developed for the aeroelastic response of sharp-edge aerodynamically heated, cantilevered lifting surfaces representative of tactical missile fins. The nonuniform flow generated by a spherically blunted missile nose is accounted for. Based upon the application of the computer program to selected cases, recommendations are made regarding the analysis procedures. Appropriate prestress conditions are obtained from the quasi-static solution. An analytic theory is developed which can predict the nonuniform flow effects of nose bluntness in the complete hypersonic speed range up to Mach 3.
Hypersonic Aeroelastic Analysis
1975
218 pages
Report
Keine Angabe
Englisch
Missile Trajectories & Reentry Dynamics , Fluid Mechanics , Guided missiles , Hypersonic characteristics , Aerothermoelasticity , Lifting surfaces , Angle of attack , Low angles , Computer programming , Mathematical prediction , Digital computers , Equations of motion , Numerical integration , Structural analysis , Inviscid flow , Two dimensional flow , Sharp bodies , Leading edges , Nonuniform flow , Aerodynamic characteristics , Viscous flow , Recommendations
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