Development of new or upgrading of existing airplanes requires
many different analyses, e.g., thermal, aerodynamical, structural,
and safety. Similar studies were performed during re-design of two small
aircrafts, which were equipped with new turboprop engines. In this paper
thermo-fluid analyses of interactions of new propulsion systems with
selected elements of airplane skin were carried out. Commercial software
based numerical models were developed. Analyses of heat and fluid flow
in the engine bay and nacelle of a single-engine airplane with a power unit
in the front part of the fuselage were performed in the first stage. Subsequently,
numerical simulations of thermal interactions between the hot
exhaust gases, which leave the exhaust system close to the front landing
gear, and the bottom part of the fuselage were investigated. Similar studies
were carried out for the twin-engine airplane with power units mounted on
the wings. In this case thermal interactions between the hot exhaust gases,
which were flowing out below the wings, and the wing covers and flaps
were studied. Simulations were carried out for different airplane configurations
and operating conditions. The aim of these studies was to check if
for the assumed airplane skin materials and the initially proposed airplane
geometries, the cover destruction due to high temperature is likely. The
results of the simulations were used to recommend some modifications of
constructions of the considered airplanes.
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