The effect of compressor inlet sensitivity to the turboprop engine performance for an increased high lift capacity aircraft will be investigated. In contrast to existing systems, engines of a high‐lift aircraft require greater core engine performance demand during take‐off, which is due to the sum of the increased thrust requirements with the additional mass flow of particle separators, as well as the additional power extraction for the active high-lift supply. This performance sensitivity for both uninstalled and installed engines is to be quantified by numerical methods using unsteady RANS simulations, in order to determine the main geometry as a parametric design. In the case of over‐wing engine integration, the effect of the wing flow is analysed in detail with respect to the inlet angle of attack in order to evaluate the sensitivity of the inlet position relative to the propeller axis. The objective parameters for the sensitivity analysis are defined as total losses and distortion coefficients, in this case on the core engine compressor face (Aerodynamic Interface Plane ‐ AIP).
Based on the sensitivity analysis results, an inlet model with variable suction will be realised and,integrated into the existing propeller driven model at the Institute. Using this engine model, high‐quality local and unsteady experimental data will be achieved. The first measurement objective will be the unsteady influence of the axial inlet position and the propeller geometry on the interaction between the propeller and intake, while the second focus is on the assessment of the unsteady flow parameters and distortion factors on the core engine compressor face (AIP) as a function of the inlet flow.