This paper describes the possibility of using a small autonomous helicopter to perform tasks using a remote sensing system. This article further shows the most effective way to properly set up autopilot and to process its validation during flight tests. The most important components of the remote sensing system are described and the possibilities of using this system to monitor gas transmission and distribution networks are presented.

This paper presents a numerical analysis of the stability of the flow parameters along the intake duct of an aircraft jet turbine engine. This problem has been investigated by many research teams and was included in the literature analysis. The unstable operation of a turbojet intake system can be the consequence of many adverse factors, including an intake vortex. The investigated intake system, due to its low location to the plane of the airport, is highly susceptible to the formation of an intake vortex. The phenomenon of an intake vortex can, in the worst-case scenario, result in the surging of the turbojet, and even engine stalling. This paper presents a developed model of the forward section of an aircraft, complete with its intake duct, and the method of its discretization. The intake-system model and numerical analysis were performed in Ansys Fluent. The flow parameters adopted for numerical simulations, under specific boundary conditions, corresponded to the operating conditions of the engine cooperating with the investigated intake system. The numerical calculations were performed assuming an air-pressure rise in the end section of the engine-intake system, reflecting the reduction in the pitch angle of the inlet stator blades of the fan. As a result, the pressure distributions in a significant cross section in the intake system were obtained. The results were analyzed with the quantitative distribution of the pressure fields by applying a dimensionless potential-pressure ratio. The pressure ratio enabled a comparative analysis of the nonuniformity of the total-pressure distribution in selected cross sections of the intake system. The results were revealing in terms of growing unstable flows in the flow duct. A major conclusion drawn from the results, by testing the dimensionless potential-pressure ratio, was that, within certain limits, it was possible to improve the flow uniformity by increasing the throttling pressure.

In the design process of blade arrangements in axial flow machines, it is extremely important to have the aerodynamic characteristics of the airfoils in a rectilinear blade cascade arrangement. However, the source of these characteristics is often difficult to access. This paper presents a methodology for the numerical determination of the characteristics of the lift coefficient, drag coefficient and flow turning angle of the airflow as a function of the angle of attack, by using the example of a blade cascade formed by NACA 65-010 airfoils for the flow intake angle β1=30° and the cascade solidity σ=1. A numerical analysis of the impact of the numerical mesh parameters and the applied turbulence model on the obtained values of the lift coefficient, drag coefficient and flow turning angle of the airfoil in a rectilinear blade cascade has been performed. The numerical values obtained have been compared to experimental results. In this respect, satisfactory agreement has been obtained between experimental and numerical results, confirming the feasibility of numerical determination of the aerodynamic characteristics of airfoils in a rectilinear blade cascade. Copyright © 2023 The Authors - Published by Praise Worthy Prize under the CC BY-NC-ND license.

The design of an aircraft’s internal structure, and therefore the appropriate choice of material type, is a direct function of the performed tasks and the magnitude and type of the acting loads. The design of a durable aircraft structure with appropriate stiffness and lightness requires knowledge of the loads that will be applied to the structure. Therefore, this paper presents the results of an aerodynamic experimental test and numerical analysis of a newly designed jet-propelled aerial target. The experimental tests were carried out in a low-speed wind tunnel for a wide range of angles of attack and sideslips. Moreover, they were performed for various configurations of the airplane model. In addition, the results of the experimental test were supplemented with the results of the numerical analysis performed using computational fluid dynamics methods. During numerical analysis, specialized software based on solving partial differential equations using the Finite Volumes Method was used. This article presents the methodology of the conducted research. The results of the aerodynamic analysis are presented in the form of diagrams showing the aerodynamic force and moment components as a function of the angle of attack and sideslip. In addition, qualitative results of the flow around the plane have been presented. The results obtained prove that the adopted methods are sufficient to solve these types of problem. The aerial system was positively verified during the qualification tests of the system at the Polish Air Force training range and finally received the type certificate.

This paper presents the numerical evaluation of ground (proximity) effects on the basic aerodynamic characteristics of a specifically designed airplane model. The ground effects were investigated in relation to the angle of attack and flight altitude. The results were referenced to the characteristics of an object in motion unaffected by ground effects.