Preliminary design of a low speed, long endurance remote piloted vehicles (RPV) for civil applications

1999 ◽  
Vol 2 (3) ◽  
pp. 167-182 ◽  
Author(s):  
Rodrigo Martı́nez-Val ◽  
Carlos Hernández
Keyword(s):  
Preliminary Design ◽  
Low Speed ◽  
Long Endurance

Optimized Preliminary Design of a Multistage Low-Speed Axial FLow Compressor

2021 ◽  
Author(s):  
AbdelRahman Ahmed Kamal ◽  
Alyaa Abdelnaby Thabet ◽  
Mohamed M. A. Elnabawy
Keyword(s):  
Axial Flow ◽  
Preliminary Design ◽  
Low Speed ◽  
Axial Flow Compressor ◽  
Flow Compressor

scholarly journals Experiment-Based Preliminary Design Guidelines for Consideration of Profile Vortex Shedding From Low-Speed Axial Fan Blades

2021 ◽  
Vol 143 (6) ◽  
Author(s):  
Gábor Daku ◽  
János Vad
Keyword(s):  
Vortex Shedding ◽  
Design Guidelines ◽  
Preliminary Design ◽  
Axial Fan ◽  
Noise Emission ◽  
Blade Vibration ◽  
Low Speed ◽  
Blunt Trailing Edge ◽  
Axial Fans ◽  
Semi Empirical

Abstract This paper presents hot-wire measurements in a wind tunnel, close downstream of basic models of blade sections being representative for low-speed, low-Reynolds number axial fans, in order to explore the signatures of vortex shedding (VS) from the blade profiles. Using the Rankine-type vortex approach, an analytical model was developed on the velocity fluctuation represented by the vortex streets, as an aid in evaluating the experimental data. The signatures of profile VS were distinguished from blunt trailing-edge VS based on Strouhal numbers obtained from the measurements in a case-specific manner. Utilizing the experimental results, the semi-empirical model available in the literature for predicting the frequency of profile VS was extended to low-speed axial fan applications. On this basis, quantitative guidelines were developed for the consideration of profile VS in preliminary design of axial fans in the moderation of VS-induced blade vibration and noise emission.

A model for solar powered aircraft preliminary design

2008 ◽  
Vol 112 (1128) ◽  
pp. 57-78 ◽  
Author(s):  
E. Rizzo ◽  
A. Frediani
Keyword(s):  
Mathematical Model ◽  
Great Emphasis ◽  
Preliminary Design ◽  
Research Activities ◽  
Solar Powered ◽  
Flying Wings ◽  
Long Endurance ◽  
Near Future ◽  
Aircraft Configurations ◽  
Aerodynamic Configuration

Abstract Solar powered aircraft are becoming more and more interesting for future long endurance missions at high altitudes, because they could provide Earth monitoring, telecommunications, etc. without any atmospheric pollution and, hopefully in the near future, with competitive costs compared with satellites. The research activities carried out till now have been mainly focused on flying wings or conventional aircraft configurations, with a great emphasis on the technological aspects. The present paper aims to define a mathematical model for solar powered aircraft preliminary design, valid independently of the aerodynamic configuration. A preliminary analysis is carried out in order to simulate Helios and the results are compared with those available from the flights of this aircraft. The proposed mathematical model is used also to compare four different aircraft configurations, namely: a flying wing, a conventional aircraft, a twin boom aircraft and a biplane aircraft. The results obtained are discussed in the paper and an optimum aircraft is analysed.

scholarly journals Experiment-Based Preliminary Design Guidelines for Consideration of Profile Vortex Shedding From Low-Speed Axial Fan Blades

2020 ◽  
Author(s):  
Gábor Daku ◽  
János Vad
Keyword(s):  
Vortex Shedding ◽  
Design Guidelines ◽  
Preliminary Design ◽  
Axial Fan ◽  
Noise Emission ◽  
Blade Vibration ◽  
Low Speed ◽  
Blunt Trailing Edge ◽  
Axial Fans ◽  
Semi Empirical

Abstract The paper presents hot wire measurements in a wind tunnel, close downstream of basic models of blade sections being representative for low-speed, low-Reynolds-number axial fans, in order to explore the signatures of vortex shedding (VS) from the blade profiles. Using the Rankine-type vortex approach, an analytical model was developed on the velocity fluctuation represented by the vortex streets, as an aid in evaluating the experimental data. The signatures of profile VS were distinguished from blunt-trailing-edge VS based on Strouhal numbers obtained from the measurements in a case-specific manner. Utilizing the experimental results, the semi-empirical model available in the literature for predicting the frequency of profile VS was extended to low-speed axial fan applications. On this basis, quantitative guidelines were developed for consideration of profile VS in preliminary design of axial fans in moderation of VS-induced blade vibration and noise emission.

scholarly journals Feasibility Study of Solar Powered Unmanned Aerial Vehicle

2022 ◽  
pp. 8-13
Author(s):  
Shiva Prasad U ◽  
Kiran Ravi Kumar ◽  
Vinaya Acharekar ◽  
Rishika Radhakrishnan
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Conceptual Design ◽  
Design Methodology ◽  
Preliminary Design ◽  
Vast Number ◽  
Aerial Vehicles ◽  
Aerial Vehicle ◽  
Solar Powered ◽  
Long Endurance ◽  
Surveillance Applications

High Altitude Long Endurance Unmanned Aerial Vehicles (HALE UAVs) could provide an improved service and/or flexibility at a reduced cost over existing systems for a vast number of civil patrol and surveillance applications. This document looks into the Feasibility and Conceptual Design of Solar Powered UAV for HALE applications. It mentions the advancements in technology of the components required to build an efficient solar powered UAV. It also provides a preliminary design methodology that can be adopted for the conceptual design of Solar Powered UAV. It also emphasizes the Aerodynamic difficulties that are faced in HALE configurations.

scholarly journals An efficient low-speed airfoil design optimization process using multi-fidelity analysis for UAV flying wing

2016 ◽  
Vol 19 (3) ◽  
pp. 43-52
Author(s):  
Bao Anh Dinh ◽  
Hieu Khanh Ngo ◽  
Van Nhu Nguyen
Keyword(s):  
Design Optimization ◽  
Wind Tunnel Test ◽  
Aircraft Design ◽  
Aerodynamic Characteristics ◽  
Optimization Process ◽  
Design Stage ◽  
Low Speed ◽  
Design Requirements ◽  
Long Endurance ◽  
The Given

This paper proposes an efficient low-speed airfoil selection and design optimization process using multi-fidelity analysis for a long endurance Unmanned Aerial Vehicle (UAV) flying wing. The developed process includes the low speed airfoil database construction, airfoil selection and design optimization steps based on the given design requirements. The multi-fidelity analysis solvers including the panel method and computational fluid dynamics (CFD) are presented to analyze the low speed airfoil aerodynamic characteristics accurately and perform inverse airfoil design optimization effectively without any noticeable turnaround time in the early aircraft design stage. The unconventional flying wing UAV design shows poor reaction in longitudinal stability. However, It has low parasite drag, long endurance, and better performance. The multi-fidelity analysis solvers are validated for the E387 and CAL2463m airfoil compared to the wind tunnel test data. Then, 29 low speed airfoils for flying wing UAV are constructed by using the multi-fidelity solvers. The weighting score method is used to select the appropriate airfoil for the given design requirements. The selected airfoil is used as a baseline for the inverse airfoil design optimization step to refine and obtain the optimal airfoil configuration. The implementation of proposed method is applied for the real flying-wing UAV airfoil design case to demonstrate the effectiveness and feasibility of the proposed method.

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