Topic
United States Air Force Stability and Control Digital DATCOM
About: United States Air Force Stability and Control Digital DATCOM is a research topic. Over the lifetime, 243 publications have been published within this topic receiving 1861 citations.
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01 Feb 1998
TL;DR: The fundamental purpose of Missile Datcom is to provide an aerodynamic design tool which has the predictive accuracy suitable for preliminary design, and the capability for the user to easily substitute methods to fit specific applications.
Abstract: : THIS REPORT IS A USER'S MANUAL FOR THE 1997 FORTRAN 90 REVISION OF THE MISSILE DATCOM COMPUTER PROGRAM. THIS SUPERSEDES WL-TR-93-3043. In missile preliminary design it is necessary to quickly and economically estimate the aerodynamics of a wide variety of missile configuration designs. Since the ultimate shape and aerodynamic performance are so dependent upon the subsystems utilized, such as payload size, propulsion system selection and launch mechanism, the designer must be capable of predicting a wide variety of configurations accurately. The fundamental purpose of Missile Datcom is to provide an aerodynamic design tool which has the predictive accuracy suitable for preliminary design, and the capability for the user to easily substitute methods to fit specific applications.
137 citations
TL;DR: A new optimizer is proposed and tested for a typical aerodynamic shape optimization of missile control surfaces with computational fluid dynamics (CFD), which significantly decreases the required CFD calls by over 62.5%.
103 citations
TL;DR: The generation of a tabular aerodynamic model for design related flight dynamics studies, based on simulation generated data, is considered, and Kriging is used to interpolate the samples computed using simulation.
Abstract: The generation of a tabular aerodynamic model for design related flight dynamics studies, based on simulation generated data, is considered. The framework described accommodates two design scenarios. The first emphasizes the representation of the aerodynamic nonlinearities, and is based on sampling. The second scenario assumes incremental change from an initial geometry, for which a hi-fidelity model from the first scenario is available. In this case data fusion is used to update the model. In both cases, Kriging is used to interpolate the samples computed using simulation. A commercial jet test case, using DATCOM as a source of data, is computed to illustrate the sampling and fusion. Future application using Computational Fluid Dynamics as the source of data is considered.
82 citations
01 Apr 1991
TL;DR: In this article, the authors present an aerodynamic design tool for preliminary design of a wide variety of missile configuration designs, such as the one described in this paper. But, the accuracy of the predicted aerodynamic performance is dependent upon the subsystems used.
Abstract: : In missile preliminary design it is necessary to quickly and economically estimate the aerodynamics of a wide variety of missile configuration designs Since the ultimate shape and aerodynamic performance are so dependent upon the subsystems used, such as payload size, propulsion system selection and launch mechanism, the designer must be capable of predicting a wide variety of configurations accurately The fundamental purpose of Missile Datcom is to provide an aerodynamic design tool which has the predictive accuracy suitable for preliminary design, and the capability for the user to easily substitute methods to fit specific applications
80 citations
TL;DR: The U.S. Air Force Missile DATCOM (97 version) and the Naval Surface Warfare Center Dahlgren Division Aeroprediction 98 (AP98) are two widely used aerodynamic prediction codes as discussed by the authors.
Abstract: The U.S. Air Force Missile DATCOM (97 version) and the Naval Surface Warfare Center Dahlgren Division Aeroprediction 98 (AP98) are two widely used aerodynamic prediction codes. These codes predict aerodynamic forces, moments, and stability derivatives as a function of angle of attack and Mach number for a wide range of axisymmetric and nonaxisymmetric missile configurations. This study evaluates the accuracy of each code compared to experimental wind-tunnel data for a variety of missile configurations and flight conditions. The missile configurations in this study include axisymmetric body alone, body wing tail, and body tail. The aerodynamic forces under investigation were normal force, pitching moment, axial force, and center-of-pressure location. For the configurations detailed in this paper, these case studies show normal force prediction for both codes to have minimal error. Both AP98 and Missile DATCOM were effective in predicting pitching-moment coefficients, though at times limiting factors were necessary. Finally, both AP98 and DATCOM predict reasonable axial-force coefficients for most cases, though AP98 proved more accurate for the body-wing-tail and body-tail configurations evaluated in this study.
63 citations