Validation of global aeropropulsive characteristics of integrated configurations

Chalot, F.; Rostand, P.; Perrier, Pierre; Gounko, Yurii P.; Kharitonov, A. M.; Latypov, A. F.; Mazhul, Ignatii I.; Yaroslavtsev, M. I.

doi:10.2514/6.1998-1624

Cited by 9 publications

(4 citation statements)

References 5 publications

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“…In [4], the thermal energy is added to the flow in disconnected zones, but the flow structure is formed in accordance with conditions (4) and (5). Chalot et al [5] reported the results of experimental investigations of a hydrogen-driven ramjet model for the free-stream Mach numbers M 6;M 8 , which confirm the validity of the theoretical relations (4) and (5). Figure 3 shows the scheme of the optimal combustor of a hypersonic scramjet [6].…”

Section: Some Examplessupporting

confidence: 58%

On organizing the working process in air-breathing engines

Latypov¹

2017

AIP Conference Proceedings

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Section: Some Examplessupporting

confidence: 58%

On organizing the working process in air-breathing engines

Latypov¹

2017

AIP Conference Proceedings

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“…Отсутствуют достоверные экспериментальные результаты, свидетельствующие о сохранении сверхзвукового течения в канале при подводе энергии с эквивалентным коэффициентом избытка воздуха α 1. В многочисленных экспериментах с моделями ПВРД в аэродинамических трубах при сгорании топлива наблюдается значительная перестройка начального сверхзвукового потока (см., например, [3,4]). После завершения переходного процесса система косых скачков уплотнения замыкается пряc Латыпов А. Ф., 2015…”

Section: Doi: 1015372/pmtf20150506unclassified

Functional Mathematical Model of a Hydrogen-Driven Combustion Chamber for a Scramjet

2015

PMTF

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“…It is assumed that the responses of the strain-gauge balance registered in time are described by ordinary differential equations with constant coefficients, i.e., the system consisting of the model, sting, strain-gauge balance, and fixturing system is a linear dynamic object. This assumption is based on the following circumstances: the acting loads are such that the relation between strains and stresses is described by Hooke's law; the data of the strain-gauge balance weakly depend on the distribution of loads acting on the model if the integral values of loads are fixed (this is validated, e.g., by the results of testing the model of an air-breathing engine and its elements in a blowdown wind tunnel in flows with Mach numbers M = 2, 4, and 6 with simultaneous measurements of forces and moments by mechanical and strain-gauge balances [3,4]); the size of the sensors is small as compared with the characteristic size of the model; the change in temperature of the model and sensors during the experiment is insignificant. In this case, the response of the system to unit loads being measured experimentally, a system of integral equations is derived to recover the acting loads from the responses of the strain-gauge balance measured in time.…”

mentioning

confidence: 99%

Dynamic method of determining aerodynamic characteristics of models from on experimental results obtained in short-duration wind tunnels

Latypov

2006

J Appl Mech Tech Phys

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A technique is developed to recover the loads acting in model testing in short-duration wind tunnels. The model together with the load-measuring device is assumed to be a linear dynamic system. Normal responses of the system to unit loads are determined experimentally. The solution of a system of integral Volterra equations of the first kind is found in the class of piecewise-constant functions. Examples are given on solving a test problem with a known exact solution and a problem of determining the aerodynamic characteristics of the HB-2 reference model on the basis of loads obtained in wind-tunnel measurements.Introduction. The following methods are used for processing the measured results if a strain-gauge balance is applied to measure time-dependent forces and moments acting on the model being tested in short-duration wind tunnels: 1) averaging technique; 2) analytical method; 3) statistical method; 4) simplified statistical method [1]. The averaging technique requires a fairly long time of wind-tunnel operation, so that oscillations caused by initial shock loads could decay, and a large time interval with unchanged flow parameters. Even if these conditions are satisfied, however, there are some uncontrollable systematic errors. Three other methods involve the principle of inertia compensation. For this purpose, accelerations are measured at certain points by accelerometers. The methods are based on the following assumptions: the model is a rigid body; the oscillating system consists of the model and a certain part of the balance to be determined; the products of the velocities of revolution of the system around its axes are rather small and can be neglected, as compared with angular accelerations.In the analytical method, the main difficulty is to establish the portion of the system participating in motion and subsequently determine the mass, center of mass, and matrix of the moments of inertia. The accuracy or reconstructing the acting aerodynamic loads also depends on the coordinates of points where the accelerometers are mounted.The statistical method is based on linearization of relations between the inertia forces and accelerations measured by accelerometers with the use of the following additional assumption: the aerodynamic coefficients are constant over a chosen time interval determining the operation regime of the wind tunnel. The number of equations (6) is smaller than the number of unknowns (42). As the system of equations is valid at an arbitrary time during the run, however, it is solved on a certain interval by the least squares technique.The simplified statistical method implies a linear dependence between the acceleration and the corresponding force, which reduces the number of unknowns. Three accelerometers are used, one in each direction. The measurement axes coincide with the directions of the body-fitted coordinate system. The unknown coefficients of proportionality depend on the geometric and mass characteristics of the model, which have to be determined in each test for the model mounte...

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Validation of global aeropropulsive characteristics of integrated configurations

Cited by 9 publications

References 5 publications

On organizing the working process in air-breathing engines

On organizing the working process in air-breathing engines

Functional Mathematical Model of a Hydrogen-Driven Combustion Chamber for a Scramjet

Dynamic method of determining aerodynamic characteristics of models from on experimental results obtained in short-duration wind tunnels

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