High lift aerodynamic characteristics of a three lifting surfaces turboprop aircraft

This paper deals with the aerodynamic design and analysis of the high lift capabilities of a three lifting surfaces turboprop aircraft. The aircraft under investigation is part of IRON European Union (EU) funded research project, aimed to provide an innovative regional turboprop aircraft, with advanced performance. This work is focused on evaluating the canard wakes effects on the wing high-lift capabilities. The effects of the canard wake on the wing have been evaluated in terms of downwash and induced angles. A preliminary investigation carried out through a three-dimensional panel method has been useful to evaluate the downwash and upwash produced by the canard on the wing both in the symmetry plane and in the spanwise direction. The estimated induced angles have been useful to improve both the wing root incidence and the spanwise twist distribution. In this way, it has been possible to compensate the loss in wing lift and to mitigate the upwash effects produced by the canard tip vortex. Panel code results have been also compared to a high-fidelity numerical method such as CFD-RANS calculations. The complete aircraft in landing configuration, including the horizontal tail plane, has been analyzed by means of RANS simulations. This analysis highlighted that the canard, when its flap is deployed, introduces a strong downwash angles on the tail plane despite the large horizontal stagger between those surfaces. This latter leads to a reduction of the longitudinal stability at low angles of attack. An investigation about different canard vertical positions and reduction of the canard flap deflection has been performed to carry out the aircraft layout being the best compromise between maximum achievable lift coefficient, longitudinal stability and architectural constraints

Wind tunnel testing of a generic regional turboprop aircraft modular model and development of improved design guidelines

This article presents results of a wide experimental aerodynamic test campaign, regarding the longitudinal and lateral-directional stability, performed in the low-speed wind-tunnel of the University of Naples “Federico II”, on a generic modular model of a modern regional turboprop aircraft. The modular model has been designed to arrange more than 200 possible different configurations with the modification of the aircraft main geometrical characteristics, such as wing-fuselage relative position, vertical tail size, and horizontal tail position. All tests, both longitudinal and lateral-directional, were addressed to the derivation of improved semi-empirical formulations or surrogate models for the estimation of aerodynamic characteristics and derivatives for the regional turboprop aircraft category (similar to the ATR and Bombardier Q-Series) in preliminary design phase. Longitudinal tests were addressed to the measurement of aircraft lift, downwash, and horizontal tailplane contribution to longitudinal stability. Directional tests were instead focused on the correct estimation of vertical tail and fuselage contributions to directional stability for different vertical tail planforms, horizontal tail arrangements, and fuselage after-body shapes. The combined effects of wing and horizontal tail positions on aircraft lateral stability have also been investigated. All the obtained results are likely to be extremely useful for a future application in the preliminary design phase, since the derived charts may give indications for accurate sizing and position of both horizontal and vertical stabilizers