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

Damljanović, Dijana; Vuković, Đorđe; Ocokoljić, Goran; Ilić, Biljana; Rašuo, Boško

doi:10.3390/aerospace8100275

Cited by 11 publications

(7 citation statements)

References 36 publications

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“…Since no experimental work has been undertaken supporting the present research work, we have validated the work using the published paper by Milicev [28] and Damljanović et al [29]. The off-design performance of the model in the wind tunnel has been studied based on the work of Damljanović et al [30].…”

Section: Geometry and Gridmentioning

confidence: 85%

Passive flow modification over the supersonic and the hypersonic air-intake system using bleed

Sinha,

Singh,

Prakash

et al. 2023

FME Transactions

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The air intake should be operated at design conditions to achieve a high total pressure recovery and optimum mass capture ratio. The current research focuses on the numerical simulation of the supersonic and hypersonic air inlet and its starting and unstarting characteristics. 2D RANS equation for supersonic and hypersonic intake has been solved using the k-oSST turbulence model. The in-house code and the algorithm based on the RANS equation have also been validated in due process and used for subsequent simulations. The sudden drop in mass capture ratio indicates the unstart condition of the intake. The presence of a bleed section has a commendable effect on the performance parameter of the air intake. A separation bubble was observed at the intake's entrance during the off-design conditions, resulting in performance losses. Four different bleed sections ranging in size from 1.6mm to 8.6mm were used, and simulations with bleed were run for different Mach numbers ranging from 3 to 8. The optimum bleed size of 3mm has been found quite effective in modifying Total pressure recovery within the optimum mass flow rate over the wide range of Mach numbers.

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Section: Geometry and Gridmentioning

confidence: 85%

Passive flow modification over the supersonic and the hypersonic air-intake system using bleed

Sinha,

Singh,

Prakash

et al. 2023

FME Transactions

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show abstract

“…The wind tunnels at the Military Technical Institute (VTI) in Belgrade, Serbia, are being checked periodically, ensuring the measurement accuracy of calibration and other models [19][20][21]. Many results have been reported from these checks.…”

Section: The Wind Tunnel Facility and The Geometry Of The Tested Modelsmentioning

confidence: 99%

“…Damljanovic et al [20] obtained results for the same model in the transonic domain and compared them with the results from six relevant whirlwind tunnels for the same flow conditions. The same authors also analyzed the results for standard models obtained at non-standard conditions [21]. The regular testing of the standard calibration models ensures both the verification of the airfield parameters in the test sections and valid conditions of the wind tunnels instrumentation.…”

Section: The Wind Tunnel Facility and The Geometry Of The Tested Modelsmentioning

confidence: 99%

An experimental study of the influence of spike in supersonic and transonic flows past a hemispheric body

Milićev¹

2022

FME Transactions

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A strong shock wave during a supersonic flight of a blunt-nosed projectile increases the drag and aerodynamic heating considerably. A spike can be mounted on the nose of the projectile to reduce these effects. Apart from its very existence and its length, the spike's shape may also affect the aerodynamic characteristics of a blunt body. This paper presents the results of an experiment that analyzed the influence of the spike's shape on the aerodynamic forces and moments coefficients, and the location of the center of pressure, at supersonic and transonic flows past a model of a projectile with a hemispheric forebody. The experiment was carried out in a trisonic wind tunnel, for Mach numbers M=1.89 and M=1.03 and different angles of attack (0○ -10○ ). Visualization of the experiments was performed by the schlieren method in the case of supersonic flow. It enables qualitative analysis of the airflow around the tested model without and with four different spikes. The conclusions are by the obtained values of the aerodynamic coefficients. The experiments show that a spike and its shape affect only the performance of the tested projectile during its supersonic flight. Besides, a spike does not affect or even slightly impairs the aerodynamic performance of the projectile during its transonic flight. The obtained results are applicable in broader contexts, e.g. for the design of an aircraft for supersonic flights.

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“…Moreover, there were also experiments focused on the aerodynamic interactions between a scaled model and the walls of the test section, providing procedures to correct wind tunnel data with respect to free flight conditions [24,25]. The wind tunnel is, nowadays, also used to present test cases to the community to validate numerical methods [26,27].…”

Section: Introductionmentioning

confidence: 99%

Longitudinal Wind Tunnel Tests of the PROSIB 19-Pax Airplane

Ciliberti,

Buonagura,

Nicolosi

2023

Applied Sciences

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This research paper delves into the longitudinal wind tunnel tests conducted on the 19-passengers aircraft model of the Italian PROSIB project. The concept is an innovative small air transport airplane with distributed propellers and hybrid-electric powerplant. The primary objective was to assess its stability and control characteristics in power-off conditions. In addition to the usual investigation of the aircraft components, the study introduced a belly-mounted pod, which served as a battery storage unit, and explored two distinct tail configurations: a body-mounted (low) tail and a T-tail (high). The results obtained from these tests generally confirmed the anticipated characteristics of the aircraft design. The experiments provided data on aerodynamic forces and moments, giving useful indications on the effects of a belly-mounted battery storage unit and tail layout on the aircraft stability and control characteristics. This information could be used by aircraft designers to size an airplane of the same class.

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

Cited by 11 publications

References 36 publications

Passive flow modification over the supersonic and the hypersonic air-intake system using bleed

Passive flow modification over the supersonic and the hypersonic air-intake system using bleed

An experimental study of the influence of spike in supersonic and transonic flows past a hemispheric body

Longitudinal Wind Tunnel Tests of the PROSIB 19-Pax Airplane

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