Unsteady Aerodynamic Simulations of a Finned Projectile at a Supersonic Speed With Jet Interaction

Sahu, Jubaraj; Fresconi, Frank; Heavey, Karen R.

doi:10.21236/ada606268

Cited by 5 publications

(5 citation statements)

References 20 publications

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“…Developing a reduced order model for three dimensional jet interactions would reduce the computational cost while capturing the important features in the flow. Sahu et al 10 and VanderWyst et al 11 both used computational fluid dynamics (CFD) solutions to create a reduced model of the slender high speed vehicle surface loads due to aerodynamics and jet interaction. Sahu et al 10 went on to use this reduced model in a coupled rigid-body dynamics (RBD) simulation and compared the results to a coupled CFD/RBD solution.…”

Section: Nomenclaturementioning

confidence: 99%

“…Sahu et al 10 and VanderWyst et al 11 both used computational fluid dynamics (CFD) solutions to create a reduced model of the slender high speed vehicle surface loads due to aerodynamics and jet interaction. Sahu et al 10 went on to use this reduced model in a coupled rigid-body dynamics (RBD) simulation and compared the results to a coupled CFD/RBD solution. The two solutions in terms of vehicle loading and attitude are very similar when the vehicle is stabilized by a high initial roll rate.…”

Section: Nomenclaturementioning

confidence: 99%

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High Speed Vehicle Fluid-Structure-Jet Interaction Analysis and Modeling

Kitson

Cesnik

2017

58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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This paper presents high-fidelity solutions of the fluid-structure-jet interaction problem for slender high-speed vehicles along with two jet interaction modeling methods, one semiempirical and one CFD-based, to approximate the high-fidelity solution. The high-fidelity solutions of a representative high-speed vehicle with jet interaction and structural deformation show that the resultant loads are affected by the deformation. The semi-empirical jet interaction model is developed using previous work in the literature and approximates the main features of the jet interaction solution when compared to numerical and experimental results. The CFD-based jet interaction model is developed by using data-fusion of a previously developed aerodynamic loads surrogate, the semi-empirical jet interaction model, and CFD solutions of the jet interaction. This data-fusion model approximates the surface pressure of a representative high-speed vehicle with varying flow, structure, and jet parameters and can be used within a flight simulation framework. Overall, the work demonstrates a need to model the fluid-structure-jet interaction of high-speed vehicles and modeling methods that may be used to approximate the full solution.

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Section: Nomenclaturementioning

confidence: 99%

Section: Nomenclaturementioning

confidence: 99%

High Speed Vehicle Fluid-Structure-Jet Interaction Analysis and Modeling

Kitson

Cesnik

2017

58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…The feasibility of hypersonic flight is highly dependent on the controller's design. Due to extreme flow conditions, it is a challenge to develop a design for a large flight envelope and strong interactions between propulsion and structural systems [17,18]. However, the control-oriented model, truth model, wing-cone model, curve-fitted model, and re-entry motion are few techniques with which to take up this challenge [17].…”

Section: Introductionmentioning

confidence: 99%

Estimation of Stability Parameters for Wide Body Aircraft Using Computational Techniques

et al. 2021

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In this paper, we present the procedure of estimating the aerodynamic coefficients for a commercial aviation aircraft from geometric parameters at low-cruise-flight conditions using US DATCOM (United States Data Compendium) and XFLR software. The purpose of this research was to compare the stability parameters from both pieces of software to determine the efficacy of software solution for a wide-body aircraft at the stated flight conditions. During the initial phase of this project, the geometric parameters were acquired from established literature. In the next phase, stability and control coefficients of the aircraft were estimated using both pieces of software in parallel. Results obtained from both pieces of software were compared for any differences and the both pieces of software were validated with analytical correlations as presented in literature. The plots of various parameters with variations of the angle of attack or control surface deflection have also been obtained and presented. The differences between the software solutions and the analytical results can be associated with approximations of techniques used in software (the vortex lattice method is the background theory used in both DATCOM and XFLR). Additionally, from the results, it can be concluded that XFLR is more reliable than DATCOM for longitudinal, directional, and lateral stability/control coefficients. Analyses of a Boeing 747-200 (a wide-body commercial airliner) in DATCOM and XFLR for complete stability/control analysis including all modes in the longitudinal and lateral directions have been presented. DATCOM already has a sample analysis of a previous version of the Boeing 737; however, the Boeing 747-200 is much larger than the former, and complete analysis was, therefore, felt necessary to study its aerodynamics characteristics. Furthermore, in this research, it was concluded that XFLR is more reliable for various categories of aircraft alike in terms of general stability and control coefficients, and hence many aircraft can be dependably modeled and analyzed in this software.

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“…shocks, separation). Computational fluid dynamics (CFD) has become a feasible alternative [1,2] to linear methods for the capability to model flow nonlinearities. This comes at the price of high computing times, and CFD-based aeroelastic analysis is generally restricted to few flight conditions and mass configurations [3,4].…”

Section: Introductionmentioning

confidence: 99%

Efficient aeroelastic reduced order model with global structural modifications

Chen

Zhou

et al. 2018

Aerospace Science and Technology

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Time domain aeroelastic analysis has high computing costs when using computational fluid dynamics. These costs become prohibitive when the structural model undergoes large changes from the baseline design, as within an aircraft design process. To overcome this realistic challenge, we have developed, implemented, and demonstrated an efficient method that is robust in the presence of global modifications of the structure. The method consists of: a) a reduced order model of the linearized Navier-Stokes equations generated around an aeroelastic equilibrium that depends, in turn, on the structural model; b) an approximate structural dynamic reanalysis method valid for global modifications of the structure; and c) a mechanism to exchange information between fluid and structural solvers without need for calculating at each iteration of the structural design an eigenvalue problem of the modified structure. The resulting aeroelastic reduced order model is demonstrated for the AGARD 445.6 wing, and material properties are varied up to 100% from their original values. It is found that: a) predictions of the time domain aeroelastic response and of the flutter speed are accurate for all modifications of the structure; and b) the computational efficiency of the proposed aeroelastic reduced order model is linearly proportional to the number of structural configurations considered. The method, therefore, is ideally suited for optimization and uncertainty studies.

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Unsteady Aerodynamic Simulations of a Finned Projectile at a Supersonic Speed With Jet Interaction

Cited by 5 publications

References 20 publications

High Speed Vehicle Fluid-Structure-Jet Interaction Analysis and Modeling

High Speed Vehicle Fluid-Structure-Jet Interaction Analysis and Modeling

Estimation of Stability Parameters for Wide Body Aircraft Using Computational Techniques

Efficient aeroelastic reduced order model with global structural modifications

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