In order to describe the nonlinear behavior of oscillation amplitude of the segmental-conical model on a transversive rod setup in a wind tunnel at Mach М = 2, a polynomial function of damping derivatives was used. Polynom of the 4th degree as a function of viscous damping allowed to describe two limit cycles observed in experiments. Coefficients of the polynom were determined and showed sufficient agreement with a direct numerical solution of the proposed dynamic equation.

A brief description of measuring means, a free-oscillation setup with a transverse sting of the model, and test conditions is reported. A procedure for processing experimental data is described. Quasi-steady and damping aerodynamic characteristics of the pitching moment of the model in the range of Mach numbers M = 1.75–6 are obtained. A comparison of research results with calculated data, as well as with the previous experimental data obtained using the base sting is given. It was found that at M = 3–6, regular undamped oscillations of the model are excited.

A cone model is tested on a setup with free oscillations in a supersonic wind tunnel at Mach numbers M= 1.75, 2.0, 2.25, 2.5, 3.0, and 4.0. It is demonstrated that the model is dynamically stable at M= 2.5, 3.0, and 4.0. Self-induced oscillations with soft excitation are observed at M= 1.75 and 2.0; self- induced oscillations with hard excitation are detected at M= 2.25. It is found that the amplitude of these oscillations at M= 1.75 depends on the initial disturbance, Reynolds number, and dimensionless moment of inertia of the model. In the case of soft excitation, the amplitude of oscillations grows slowly at the beginning, and then a jump occurs, which is most clearly expressed at M= 2.0.

Aerodynamic derivatives of the pitching moment of a cone mounted on a transverse sting on a setup with free oscillations are obtained. The measurement tools, model, and test regimes are described. The method used to determine the aerodynamic derivatives is presented. The measured aerodynamic derivatives are compared with the calculated results and with results of experiments performed with a base sting.

A setup with free oscillations containing a transverse sting for holding the test model and possible test regimes are described. The method of testing and data processing is presented. Aerodynamic characteristics of the pitching moment of the model in a wide range of Mach numbers are obtained. Comparisons of quasi-steady data with numerical predictions and of damping derivatives with those obtained previously in tests of the model mounted on the base sting and with calculated results are performed. The model is found to be statically and dynamically stable except for regimes with М = 1.75 and 2.25, where nondecaying oscillations are excited.

Models of promising reentry vehicles, experimental equipment, and test program are described. The method used to determine the total aerodynamic characteristics of these models on the AB-313 mechanical balance in the T-313 supersonic wind tunnel and the method used for simulations are presented. The aerodynamic coefficients of the examined objects in wide ranges of Mach numbers and angles of attack are obtained. The experimental data are compared with the results of simulations.

The experimental equipment, model, test conditions, and methods used for determining the streamwise damping on a setup with free oscillations on rolling bearings are described. Characteristics of aerodynamic damping of the model with two positions of the rotation axis and Mach numbers M∞ = 2, 4, and 6 are measured. Irregular oscillations of the model with a greater displacement of the rotation axis with respect to the longitudinal axis are found to arise at M∞ = 2.

The paper deals with an experimental study of stationary and nonstationary aerodynamic characteristics of a circular cone in the range of Mach numbers 1.75–7. The experimental equipment and the method of determining the aerodynamic characteristics are briefly described. The integral aerodynamic characteristics of the model in tests with force measurements and the aerodynamic derivatives of the pitching moment in dynamic tests on a setup with free oscillations are obtained. The experimental data are compared with numerical predictions.

The model, experimental equipment, and test program are briefly described. A method of determining the aerodynamic characteristics of the model on the facility with free oscillations is presented. Aerodynamic derivatives of the pitching moment of the model are obtained for two positions of the axis of rotation and Mach numbers M ∞ = 2, 4, and 6. At M ∞ = 2, the model with the rear position of the axis of rotation is not balanced at low angles of attack, whereas irregular self-sustained oscillations of the model with the frontal position of the axis of rotation arise.

The European EXPErimental Re-entry Test bed (EXPERT) vehicle is intended for studying various basic phenomena, such as the boundary-layer transition on blunted bodies, real gas effects during shock wave/boundary layer interaction, and effect of surface catalycity. Another task is to develop methods for recalculating the results of windtunnel experiments to flight conditions. The EXPERT program implies large-scale preflight research, in particular, various calculations with the use of advanced numerical methods, experimental studies of the models in various wind tunnels, and comparative analysis of data obtained for possible extrapolation of data to in-flight conditions. The experimental studies are performed in various aerodynamic centers of Europe and Russia under contracts with ESA-ESTEC. In particular, extensive experiments are performed at the Von Karman Institute for Fluid Dynamics (VKI, Belgium) and also at the DLR aerospace center in Germany. At ITAM SB RAS, the experimental studies of the EXPERT model characteristic were performed under ISTC Projects 2109, 3151, and 3550, in the T-313 supersonic wind tunnel and AT-303 hypersonic wind tunnel.

Aerodynamic coefficients of the HB-2 AGARD reference model measured in a new AT-303 hypersonic wind tunnel with adiabatic compression are presented. The experiments are performed in the ranges of Mach numbers M = 9.7 − 15.6 (Re d = 0.14·10 6 − 1.32·10 6 ) and angles of attack α = −4°−12° with the use of an internal six-component strain-gauge balance. The technique used for processing and correcting measured results, which takes into account the dynamic properties of the model and the specific features of the nozzle structure, is described in detail. The aerodynamic coefficients obtained for this model are compared with similar data obtained in wind tunnels of Germany, France, and the USA.

Results of an experimental study of aerodynamic characteristics of models of two hypersonic re-entry vehicles (ARES-H aerospace demonstrator proposed by EADS-ST and EXPERT re-entry capsule proposed by ESA ESTEC) are presented. The experiments were performed in a new wind tunnel AT-303 at ITAM SB RAS in the range of free-stream Mach numbers M = 10–18 at real values of Reynolds numbers. The test results and specific features of wind-tunnel tests in conical nozzles are discussed.