Propeller and Dynamometer Testing of an Additive Manufactured Small
                    Internal Combustion Engine

Gray, Jamee; Srivatsa, Charu Vikram; Mattson, Jonathan; Depcik, Christopher

doi:10.4271/03-16-01-0005

Cited by 2 publications

(1 citation statement)

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“…According to Menon and Cadou [31], small ICEs generally only achieve 50-70% of their rated performance. As a conservative estimate, it was assumed that the engine would perform at 50% of its rated performance: 367.8 W. Recent efforts by Gray et al supplied the air and fuel mass flow rates for this engine as functions of engine speed under propeller-based testing [32]. Using this information and assuming that the maximum power is achieved at an equivalence ratio of 1.1 [33], the average volumetric heating value of gasoline is 114,102 Btu/gal [34], the density of gasoline is 0.73 g/mL [35], and the engine runs at 20% thermal efficiency, a representative power versus engine speed plot was generated, as shown in Figure 9.…”

Section: Engine Power and Speedmentioning

confidence: 99%

Martian Combustion-Powered Fixed-Wing UAVs: An Introductory Investigation and Analysis

et al. 2022

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The Martian topography needs to be investigated in greater detail for human habitations, and this can be accomplished faster using unmanned aerial vehicles (UAVs). In this regard, the RQ-11B Raven appears suitable for remote sensing and topography-mapping applications on Mars, due to its popularity in surveillance and reconnaissance applications on Earth. As a result, this study investigates the flight of this UAV in the Martian atmosphere with the assumptions that it employs an NACA S7012 airfoil and its electric propulsion technology is replaced with a four-stroke oxy-methane fueled Saito FG-11 internal combustion engine (ICE). This ICE is estimated to supply 367.8 W resulting in an engine speed of 6891 revolutions per minute. Based on this speed, the UAV must fly at least 72 m/s (Re = 18,100) at a 5° angle of attack to support flight under calm conditions. To achieve this speed will be difficult; thus, a weather balloon or German V1-style launch system should be employed to launch the UAV successfully. Furthermore, the UAV must operate below 165 m/s (Re = 41,450) to prevent transonic conditions. Finally, the vehicle’s fuel and oxidizer tanks can be refueled using an in situ methane and oxygen production system, enabling its sustainable use on Mars.

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Section: Engine Power and Speedmentioning

confidence: 99%