Hypervelocity ballistic reference models as experimental supersonic test cases

Damljanović, Dijana; Rašuo, Boško; Vuković, Đorđe; Mandić, Slobodan; Isaković, Jovan

doi:10.1016/j.ast.2016.02.035

Cited by 15 publications

(10 citation statements)

References 6 publications

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“…Analysis of the measured aerodynamic coefficients from the point of symmetry was done for two Mach 0.25 runs of the ONERA M4 model in the modelupright and model-inverted positions [24] [25]. A good repeatability of the results of a model testing at φ = 0° and φ = 180° (Figure 24) is established, the deviations being attributed to the uncertainty of the internal balance used, which, because of the mechanical design of the model, had to be an assembled, Task-type one with accuracy somewhat lower than that of monolithic balances.…”

Section: Onera M4 Test Resultsmentioning

confidence: 99%

Contemporary frame of measurement and assessment of wind-tunnel flow quality in a low-speed facility

Ocokoljić¹,

Damljanović²,

Vuković³

et al. 2018

FME Transactions

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The requirements for the accuracy of measurements in a wind tunnel test become more and more severe while the complexity of the test increases. In an environment of reduced time available for wind tunnel test and increasing test costs, it is important that the accurate calibrations and verifications of all components of the measurement chain in a wind tunnel facility are established, maintained and statistically controlled through prolonged periods of time. The paper presents the efforts undertaken to establish and maintain a system of control of the quality of measurements in the T-35 4.4 m × 3.2 m low-speed wind tunnel of the Military Technical Institute in Belgrade. The assurance of the quality of measurement in this facility is based on ensuring the quality of three main constituents: the calibration of the test section of the wind tunnel, the calibration of the instrumentation used, and the periodic tests of the standard wind tunnel models. Sample results from relevant wind tunnel calibration tests are presented and compared with the results from other facilities. The tests confirmed a good overall quality of the facility, and that the achieved quality level has to be maintained, periodically checked and systematically documented.

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Section: Onera M4 Test Resultsmentioning

confidence: 99%

Contemporary frame of measurement and assessment of wind-tunnel flow quality in a low-speed facility

Ocokoljić¹,

Damljanović²,

Vuković³

et al. 2018

FME Transactions

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“…HB-1 standard model is an axisymmetric cone-cylinder body with 25 • nose cone half-angle [40,41]. The more-used HB-2 configuration [40,41,[48][49][50] has a 10 • tail flare, added to reduce the sensitivity of the model to viscous effects (Figure 8a). The junctures of the nose and the flare with the cylinder are smooth radius fairings.…”

Section: The Hb Hypersonic Standard Modelsmentioning

confidence: 99%

“…Aerospace 2021, 8, 275 14 of 21 model was tested on the 48 mm diameter straight sting using the Able Mk XVIII wind tunnel balance (Figure 13a). It was found to be of interest to extend test Mach numbers of the HB-2 model [49] to a transonic part of the wind tunnel operating envelope. The larger of the two available HB-2 models produces the frontal blockage of about 0.9% in the test section of the T-38 wind tunnel, i.e., near the recommended maximum blockage for transonic wind tunnels.…”

Section: Hb Hypersonic Model In a Transonic Flowmentioning

confidence: 99%

Wind Tunnel Testing of ONERA-M, AGARD-B and HB-2 Standard Models at Off-Design Conditions

et al. 2021

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Published results for standard wind tunnel models at non-standard test conditions are quite rare and/or may not be available. It has been found that those results are a useful aid in preparations for a number of wind tunnel tests in the Military Technical Institute (VTI) in Belgrade. Test campaigns of standard models at non-standard conditions are performed to serve as an internal database for future wind tunnel tests in such environments. Those tests, that partially overlap the referenced Mach number and/or angle of attack ranges, are conducted in different VTI’s test facilities; different model sizes and support stings were used. The standard models used in static measurements in VTI, ranging from simple missile shapes and re-entry bodies to complicated airplanes, are briefly described and sample non-standard test results are given. The correlation of the test results among models and facilities has been done with references in the available ranges, and, after confirming a good agreement, it is assumed that the results are also valid in the extended ranges of conditions. These results may be useful for researchers in other wind tunnel facilities and for those who handle CFD tools.

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“…The standard AGARD-B model has been used in the initial calibration of the T-38, wind tunnel of the Military Technical Institute (VTI) in Belgrade, and it has been using for periodical verification of the facility. [17][18][19][20] The AGARD-B model used in VTI was produced by the Boeing Company. Model size (body diameter D ¼ 115.798 mm) was chosen with respect to the tunnel's test section size.…”

Section: Wind Tunnel Modelmentioning

confidence: 99%

“…Fluid dynamics is based on three fundamental physics principles: mass is conserved, Newton’s second law and energy is conserved. Therefore, CFD is based on the fundamental governing equations of fluid dynamics-the continuity, momentum, and energy equations, given by equation (3) 20 , 25 …”

Section: Computational Fluid Dynamics Simulationmentioning

confidence: 99%

Calibration of the CFD code based on testing of a standard AGARD-B model for determination of aerodynamic characteristics

Kostić

Bengin

Rašuo

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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The goal of this work is to build a unique numerical method to obtain the basic aerodynamic characteristics of the aircraft and to enable a wide application of the method in the analysis of some aerodynamic characteristics of the aircraft, without use of empirical methods. The Computational fluid dynamics (CFD) simulation method was being calibrated based on test results of the standard AGARD-B (Advisory Group for Aerospace Research and Development) test model, which were obtained in the T-38 trisonic wind tunnel facility of the Military Technical Institute (VTI) in Belgrade, Serbia.The paper presents the CFD simulation through a description of the conditions of flow, geometry of the computer domain, grid density and mesh strategy, boundary conditions, initial strategy and turbulence model. The CFD simulation was carried out for flow cases with similarity parameters M = 0.6, M = 0.85 and M = 1.6 and Re = from 7.7(x106) to 9.9(x106) . The results of calculations were compared with the appropriate experimental ones and presented in the form of comparative diagrams for the drag, lift and pitching moment coefficients. The results of investigation presented in divergence diagrams show very good agreement between numerical and experimental ones. Simulated flows are illustrated by the distribution of pressure and velocity components on the surface of the tested model and the computational domain. This CFD simulation will be applied to other similar aerodynamic designs for a wide range angles of attack and Mach numbers and can be a strong point for the development of different aerodynamic designs.The ultimate aim of the work is to use the previous calibrated CFD simulation method as the basis for future determination of the aerodynamic characteristics of aircraft in non-stationary flight modes, caused by motion of the aircraft and/or by changing the free-velocity vector.

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Hypervelocity ballistic reference models as experimental supersonic test cases

Cited by 15 publications

References 6 publications

Contemporary frame of measurement and assessment of wind-tunnel flow quality in a low-speed facility

Contemporary frame of measurement and assessment of wind-tunnel flow quality in a low-speed facility

Wind Tunnel Testing of ONERA-M, AGARD-B and HB-2 Standard Models at Off-Design Conditions

Calibration of the CFD code based on testing of a standard AGARD-B model for determination of aerodynamic characteristics

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