Investigation of the Unsteady Aerodynamic Characteristics of an Unmanned Aerial Vehicle with Variable-Sweep Morphing

2014 ◽  
Author(s):  
Han Han ◽  
Jun Hu ◽  
Yong Yu
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Aerodynamic Characteristics ◽  
Unsteady Aerodynamic ◽  
Aerial Vehicle

scholarly journals Aerodynamic Characteristics of Tube-Launched Tandem Wing Unmanned Aerial Vehicle

2018 ◽  
Vol 1005 ◽  
pp. 012015
Author(s):  
Nurhayyan H. Rosid ◽  
E. Irsyad Lukman ◽  
M. Ahmad Fadlillah ◽  
M. Agoes Moelyadi
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Aerodynamic Characteristics ◽  
Aerial Vehicle

AERODYNAMIC OF UITM'S BLENDED-WING-BODY UNMANNED AERIAL VEHICLE BASELINE-II EQUIPPED WITH ONE CENTRAL VERTICAL RUDDER

2015 ◽  
Vol 75 (8) ◽  
Author(s):  
Wirachman Wisnoe ◽  
Rizal E.M. Nasir ◽  
Ramzyzan Ramly ◽  
Wahyu Kuntjoro ◽  
Firdaus Muhammad
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Cfd Simulation ◽  
Aerodynamic Characteristics ◽  
Control Surface ◽  
Wind Tunnel Experiments ◽  
Aerodynamic Parameter ◽  
Aerial Vehicle ◽  
Computational Fluid Dynamics Cfd ◽  
Blended Wing Body ◽  
Lift And Drag

In this paper, a study of aerodynamic characteristics of UiTM's Blended-Wing-Body Unmanned Aerial Vehicle (BWB-UAV) Baseline-II in terms of side force, drag force and yawing moment coefficients are presented through Computational Fluid Dynamics (CFD) simulation. A vertical rudder is added to the aircraft at the rear centre part of the fuselage as yawing control surface. The study consists of varying the side slip angles for various rudder deflection angles and to plot the results for each aerodynamic parameter. The comparison with other yawing control surface for the same aircraft obtained previously are also presented. For validation purpose, the lift and drag coefficients are compared with the results obtained from wind tunnel experiments. 

CALCULATION OF THE AERODYNAMIC CHARACTERISTICS OF A UAV TAKING INTO ACCOUNT THE INSTALLED ELEMENTS OF ANTI-ICE SYSTEM IN A VIRTUAL ENVIRONMENT XFLR5

2019 ◽  
Vol 12 (2) ◽  
pp. 66-71
Author(s):  
А. Мельников ◽  
A. Mel'nikov
Keyword(s):  
Virtual Environment ◽  
Unmanned Aerial Vehicle ◽  
Aerodynamic Characteristics ◽  
Wing Profile ◽  
Aerial Vehicle ◽  
Aerodynamic Quality

Based on the geometric dimensions of the CLARK-Y wing profile used in the design of various aircraft models, the calculations of its main aerodynamic characteristics were carried out. Taking into account the developed method of protecting the wing of an unmanned aerial vehicle (UAV) from icing, changes were made to the profile structure taking into account the installation features of the anti-icing system (AIS) elements. Both profiles are digitally entered into the XFLR5 program, where the aerodynamic quality of the wing was calculated before installing the AIS elements and with the elements installed. Wing polarities were obtained, on the basis of which conclusions were drawn about the possibility of using the developed AIS.

scholarly journals DESIGN, PERFORMANCE ANALYSIS OF WING, AND MANUFACTURING OF FIXED WING HAND LAUNCH UNMANNED AERIAL VEHICLE

2021 ◽  
Vol 5 (9) ◽  
Author(s):  
Krishn Das Patel ◽  
Bala Syam Kumar Karuparthi
Keyword(s):  
Composite Materials ◽  
Mach Number ◽  
Carbon Fiber ◽  
Unmanned Aerial Vehicle ◽  
Subsonic Flow ◽  
Aerodynamic Characteristics ◽  
Aerodynamic Design ◽  
Ansys Fluent ◽  
Detailed Design ◽  
Aerial Vehicle

This paper concentrates on the design, analysis, and development of fixed-wing hand launch unmanned aerial vehicle (UAV). This flight can able to carry the payloads of 0.8. The design process involves the conceptual, preliminary, and detailed design. This paper involves the investigation of the aerodynamic characteristics over the wing to enhance the aerodynamic design of the UAV. This analysis includes estimating the best gliding ratio to increase the flight mission and attain the maximum altitude. This simulation will be performed for subsonic flow with Mach number 0.04202(14.3m/s). The manufacturing of the UAV is done using composite materials like glass fiber of both (1mm and 2 mm) thickness, carbon fiber of 2mm, and carbon rod is used for connecting the empennage to the fuselage. The detailed design has been done in CATIA V5 and the analysis of the wing has been done using XFLR, ANSYS (fluent).

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