Recent experience in improving the accuracy of wall interference corrections in TsAGI T-128 wind tunnel

Glazkov, S. A.; Gorbushin, A. R.; Ivanov, A. I.; Семенов, А. В.

doi:10.1016/s0376-0421(01)00007-0

Cited by 16 publications

(4 citation statements)

References 7 publications

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“…In addition, a short probe to measure static pressure was placed additionally on the Wind-tunnel axis at the model location. The pressure distributions obtained allow the calculated methods (3) intended to determine wall interference and effect of supporting devices to be verified. The system of supporting devices is simulated by distributed singularities the intensity of which depends on geometry of the strut and supporting device.…”

Section: Measurements Of Static Pressure Distributionsmentioning

confidence: 99%

Experimental investigation of the effect of nozzle shape and test section perforation on the stationary and non-stationary characteristics of flow field in the large transonic TsAGI T-128 Wind tunnel

et al. 2005

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The results are presented for a cycle of experimental investigations of flow field characteristics (static pressure distribution, static pressure fluctuations, upwash, boundary-layer parameters) in the perforated test section of the transonic TsAGI T-128 Wind Tunnel. The investigations concern the effect of nozzle shape, wall open-area ratio, Mach and Reynolds numbers on the above-outlined flow characteristics. During the tests, the main Wind-tunnel drive power is measured. Optimal parameters of the nozzle shape and test section perforation are obtained to minimise acoustic perturbations in the test section and their non-uniformity in frequency, static pressure field non-uniformity, nozzle and test section drag and, accordingly, required main Wind-tunnel drive power.

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Section: Measurements Of Static Pressure Distributionsmentioning

confidence: 99%

Experimental investigation of the effect of nozzle shape and test section perforation on the stationary and non-stationary characteristics of flow field in the large transonic TsAGI T-128 Wind tunnel

et al. 2005

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“…Over the past few years, many experimental [7][8][9] and numerical [10][11][12] studies have been devoted to wall interferences of wind tunnel at transonic regime and their consequences. In addition, many research papers have been published about the e ect of porosity based on optimization [13,14].…”

Section: Introductionmentioning

confidence: 99%

Effect of wind tunnel wall porosity on the flow around an oscillating airfoil at transonic speeds

2017

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Abstract. The e ect of porosity in oscillating situations (to the authors' knowledge, for the rst time) on a supercritical airfoil (SC0410) has been experimentally investigated. Tests have been carried out in an open circuit suction-type wind tunnel at a free stream Mach number of M = 0:80. Both static and dynamic (pitching) tests have been carried out on the mentioned airfoil. The oscillation frequency for the unsteady tests has been set to 3 and 6 Hz. The amplitude of frequency is 1 deg. The e ect of porosity has been surveyed on the magnitude of pressure uctuations, phase shift, and lift coe cient loop. The investigations show that increasing porosity in the test section of transonic regime, contrary to the impression, does not necessarily improve results.

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“…It was proved that for a moderate degree of the test section blockage the linear methods can be applied up to M = 0.9. The methodology for tacking into accoumt the effect of boundaries for subsonic velocities of the flow in that form as it is used at present in T 128 are in described in detail in [33]. Originally, for the determination of the influence of flow boundaries, two basic experimental methods were used: (1) tests of geometrically similar models; (2) tests of the same model in the small and large WT, and the tests in the large tunnel were considered as an approximation of infinite flow.…”

Section: Introductionmentioning

confidence: 99%

The use of computational fluid dynamics in TsAGI experimental works

Bosnyakov

Akinfiev

Власенко

et al. 2012

Math Models Comput Simul

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The paper describes methods to calculate the flow around an aircraft model in a wind tun nel. It formulates special boundary conditions to achieve the necessary flow parameters in the control section, as well as to simulate some features of wind tunnel walls, for example, perforation. In order to accelerate the numerical solution convergence, a method for implicit smoothing is suggested allowing the calculation duration to be reduced several times. The cases of practical use of this methodology are given. It is shown that in the conditions of the TsAGI subsonic wind tunnel, it is possible to simulate the effect on the model from the elements of the structure that are missing in this tunnel, for example, the running track. A mathematical model of the European Transonic Windtunnel (ETW) with slotted walls is presented. It is shown that the flow in the reentry affects the main flow in the test section of this tunnel. Data on the effect of the model support in the TsAGI wind tunnel T 128 are given. The pen iche height used in the half model tests has been justified. The conclusion is made that the mathemat ical model of the wind tunnel is an obligatory part in experimental studies.

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Recent experience in improving the accuracy of wall interference corrections in TsAGI T-128 wind tunnel

Cited by 16 publications

References 7 publications

Experimental investigation of the effect of nozzle shape and test section perforation on the stationary and non-stationary characteristics of flow field in the large transonic TsAGI T-128 Wind tunnel

Experimental investigation of the effect of nozzle shape and test section perforation on the stationary and non-stationary characteristics of flow field in the large transonic TsAGI T-128 Wind tunnel

Effect of wind tunnel wall porosity on the flow around an oscillating airfoil at transonic speeds

The use of computational fluid dynamics in TsAGI experimental works

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