This paper presents the results of an experimental investigation of a gyroplane model conducted in a low-speed wind tunnel. The primary objective of the study was to evaluate the aerodynamic characteristics of the complete configuration and selected partial configurations, including cases without horizontal and vertical stabilizers. Measurements were performed for a range of fuselage angles of attack and sideslip angles to determine the influence of landing gear deployment, nacelle geometry, and tail surfaces on aerodynamic performance. The analysis includes the assessment of lift, drag, and side force coefficients, as well as stability and control derivatives. The results indicate that the horizontal stabilizer provides sufficient longitudinal stability, as confirmed by the calculated Tail Volume Coefficient, while the nacelle form drag contributes significantly to the overall fuselage drag. Recommendations for future design improvements include optimization of nacelle shape and landing gear fairings to minimize drag and enhance lift during critical flight phases.