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.


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    Aeroelastic Analysis of a Trimmed Generic Hypersonic Vehicle

    Nydick, I. / Friedmann, P. P. | British Library Online Contents | 1997


    Aeroelastic Analysis of a Trimmed Generic Hypersonic Vehicle

    Nydick, I. / Friedmann, P. / AIAA et al. | British Library Conference Proceedings | 1996


    Multidisciplinary Aeroelastic Analysis of a Generic Hypersonic Vehicle

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