One challenge for the design and analysis of hybrid electric aircraft configurations is an increased demand in rejection excess waste heat. A wing surface heat exchanger concept, which explored as part IMOTHEP project, foresees transferring from propulsive electrical components to aircraft. Here, mainly dissipated transported by forced convection. The present study focuses on impact via wing’s ...

A series of wind tunnel experiments was conducted to study the e ect of propeller solidity and thrust axis inclination on the propeller normalforce coe cient. Experiments were conducted in the Langley 14by 22-Foot Subsonic Tunnel with a sting-mounted, counterrotation, scalemodel propeller and nacelle. Con gurations had two rows of blades with combinations of 4 and 8 blades per hub. The solidity...

The advent of electrified propulsion systems for civil aircraft promises not only notable reductions CO 2 and NO x emissions, but also perceived noise. In an attempt to estimate the noise reduction potential fully electric engines, current study compares generated by classical turboprop turbofan engines with spectra calculated engines. calculation is based on published far-field sound pressure ...

Abstract This paper presents an overview and preliminary system architecture evaluation results of the project SIENA developed under European Union Clean Sky 2 Program Thematic Topics. The ambition is to accelerate development novel aircraft propulsion technologies by identification that are scalable across different categories. One main tasks within this process aircraft-level various technolo...

The Descent Advisor (DA) automation tool has undergone a series of field tests at the Denver Air Route Traffic Control Center to study the feasibility of DAbased clearances and procedures. The latest evaluation, conducted in the fall of 1995, expanded the operational nature of DA testing to include a wider variety of test conditions. A total of 197 commercial flights from three airlines partici...

Abstract The integration of distributed electric propulsion and energy storage systems into the wing structure significantly affects mass distribution wing. Compared with conventional aircraft which are designed engines mounted on inner integral fuel tanks, this substantially changes overall loads structure. Assuming a retrofit scenario, paper studies influence transient gust landing impact dyn...

A Monte Carlo model designed for fixed-wing aircraft takeoff performance uncertainty quantification is benchmarked. The uses of an efficient simulator this type range from rapid design variable and constraint sensitivity studies large-scale conceptual level analyses to operational planning real-time anomaly detection. accuracy the assessed against high-resolution flight-test data obtained throu...

This paper studies several problems that may exist in the aerodynamic design of low Mach number general aircraft, and discusses characteristics pressure distribution some related airfoils while part is verified by a multi-point laminar airfoil case. Firstly, issues which such as relatively large zero-lift drag coefficient, high stall performance requirements, variation range Reynolds number, ar...

Abstract The fuel system is one of the most important and complex parts aircraft, being tasked with suppling correct quantity to aircraft engine during all operative conditions, from flight ground operation. It must operate efficiently in any condition guarantee safety reliability. A for kerosene-based fuels (i.e., jet fuels) a combination hydraulic components, namely, tanks, pumps, bypass valv...

As battery and electric machine technologies improve, the electrification of aircraft propulsion systems may have potential to reduce energy consumption emissions transport aircraft. Incorporating electrical components adds a dimension system design space introduces new tradeoffs between weight efficiency. In this article, we apply numerical optimization conceptual regional category airplanes q...