Theoretically, several calculation methods have been proposed to calculate the force generated by a propeller in yaw within the scope of the blade element theory. There have also been several measurements of the force generated by a propeller in yaw and the wake. In recent years, several analyses have been performed using CFD. In this report, we propose a calculation method based on the vortex method, which has a much lower calculation cost than CFD but can calculate the phase lag that cannot be captured by the blade element theory. The results of this calculation method were in good agreement with the results of past CFD calculations and experimental results. We also calculate the contribution of a pusher propeller to directional stability as the area of the vertical tail that provides the same stability.

This paper validates a design support framework that integrates OpenVSP with an in-house panel method solver, UNLSI, to develop efficient transportation systems using unmanned aerial vehicles (UAVs). This framework utilizes OpenVSP for geometry definition and UNLSI for the analysis of aerodynamic characteristics. To verify the methodology of this approach, the analytical results were compared with those from an existing solver, and with data from wind tunnel experiments. The results demonstrated that the predictions from UNLSI were in good agreement with the wind tunnel test data. Furthermore, flight tests were conducted on the designed aircraft. The aircraft's performance was compared with the analytical results, based on the measured power consumption and assumed performance of the propulsion system.

The Super Low Altitude Test Satellite: TSUBAME (SLATS) was launched on December 23, 2017, operated in the Very Low Earth Orbit (VLEO), and completed its operation in October 2019. A bumper of SLATS which was covered with multi-layer insulation (MLI), was attached to the proceeding direction of this satellite. A temperature sensor was attached to the thermal control film, which was the outermost layer of the MLI. In this paper, free molecular heating by the upper atmosphere is reported with the temperature sensor data of SLATS at an altitude of less than 220km. The temperature on the bumper was affected by the sunlight, the earth's albedo, and the earth's infrared rays. The effect was evaluated using thermal analysis, and the temperature rise due to free molecular heating was extracted. As a result, they obtained a relationship between temperature rise, atmospheric density and free molecular heating at altitudes below 220km, where there are almost no actual measurements.

Advancements in technology have enabled the development of more integrated flight deck display formats, which are expected to enhance aircraft design and operational safety. The authors proposed a novel integrated display format for next-generation regional jets in previous research, aiming to improve situational awareness, reduce pilot workload during flight tasks. However, the research did not address display reversion necessary instruments to the remaining operational displays in the event of random display unit failures. Display reversion mechanisms must be carefully designed for the limited display areas available on regional jets, which are smaller than those of larger transport aircraft. Without appropriate reversion, it may become impossible to secure the MFW capacity strongly required for future aircraft, adversely affecting operations during display malfunctions. Conversely, an overemphasis on maintaining MFW availability could compromise other critical aspects of flight deck operation. To address this challenge, this study employs a measure framework to establish robust display reversion requirements and proposes its adequate design for the novel integrated display format in next generation aircraft. The proposed design prioritizes simplicity, minimizes role-switching between Pilot Flying (PF) and Pilot Monitoring (PM), and ensures the availability of MFWs for each pilot. The evaluation demonstrates that the proposed display format not only outperforms conventional designs by enhancing safety in current operations but also supports the transition to future single-pilot operations, even under display failure conditions. The proposed requirements and its evaluation process can be utilized for the other display format in the next generation civil aircraft as a framework.

The aerodynamic properties of rectangular AR = 1 wings with different cambered circular-arc airfoils were measured through wind tunnel tests at Re = 10000. The aerodynamic forces (lift and drag) and the pitching moment acting on the wing were measured for a wide range of angles of attack α (-90deg ≤ α ≤ 90deg). The AR = 1 wings, which exhibited a substantial maximum lift coefficient (C_{L max}) even for a thin flat plate, demonstrated a greater C_{L max} for cambered wings. Concurrently, a substantial maximum resultant force coefficient, C_{R max}, was determined to occur at approximately α = 40deg. The development of small unmanned aircraft capable of flying at very low Reynolds numbers has recently been undertaken for the purpose of Mars exploration. The objective of this study is to supply the aerodynamic data for AR = 1 wings that will be useful for low Reynolds number aircraft.