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Flying Wing Aerodynamic Design and A...

Mantz, Philip Lawson,

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Flying Wing Aerodynamic Design and Airbrake Integration /

Record Type:	Electronic resources : Monograph/item
Title/Author:	Flying Wing Aerodynamic Design and Airbrake Integration // Philip Lawson Mantz.
Author:	Mantz, Philip Lawson,
Description:	1 electronic resource (138 pages)
Notes:	Source: Masters Abstracts International, Volume: 86-03.
Contained By:	Masters Abstracts International86-03.
Subject:	Aerospace engineering. -
Online resource:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31558250
ISBN:	9798384456070

Flying Wing Aerodynamic Design and Airbrake Integration /
Mantz, Philip Lawson,

Flying Wing Aerodynamic Design and Airbrake Integration /Philip Lawson Mantz. - 1 electronic resource (138 pages)

Source: Masters Abstracts International, Volume: 86-03.

During the 2022-2023 Academic year, the defense contractor, AeroVironment, tasked the Unmanned Aerial Systems Laboratory at Old Dominion University with designing an autonomous drone platform. A brief summary of the aerodynamic requirements included that the drone should cruise at a target cruise speed of 30m/s, the drone would operate up to an altitude of 1500m and be able to land within a 20m radius of a designated landing spot. The laboratory chose a flying wing model. Additionally, the aircraft would have an airbrake system integrated into the platform. The aerodynamic requirements were configurated through the use of a 'constraint diagram'. The airfoil was selected by conducting a literature search and constructing an airfoil performance matrix. The airframe was designed computationally using the software XFLR5, a Vortex Lattice Method solver for low Reynolds numbers. The airframe was then flight tested and validated using the autopilot logs to confirm the predicted aerodynamic performance. The airbrake system was implemented post flight testing of the airframe and was designed using Stat-Ease 360 software, which is a compiled GUI interface used to generate designed experiments. A response surface was generated using airbrake models created in XFLR5. This response surface was then used to find a list of potential airbrake solutions. The most promising solutions were selected to be wind tunnel tested. After successful wind tunnel testing, another design of experiments was created to flight test the airbrake system. The airbrake system unfortunately was never able to be flight tested due to complications with a launcher system designed outside of the scope of this thesis. Alternatively, the methodology of how to flight test an airbrake system was documented and a trainer aircraft fitted with an airbrake system was flight tested with all data logged and analyzed postflight. After validating the aerodynamic profile and airbrake system, the aerodynamic performance of the aircraft outperformed all predictions. Additionally, while the airbrake system itself was never flight tested, all computational and experimental data points toward encouraging results. If the launcher system is improved, a future flight test using the methodology created could confirm the performance of the airbrake system.

English

ISBN: 9798384456070Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Airbrake models

Flying Wing Aerodynamic Design and Airbrake Integration /
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500 $a Advisors: Landman, Drew Committee members: Britcher, Colin; Alberts, Thomas.
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520 $a During the 2022-2023 Academic year, the defense contractor, AeroVironment, tasked the Unmanned Aerial Systems Laboratory at Old Dominion University with designing an autonomous drone platform. A brief summary of the aerodynamic requirements included that the drone should cruise at a target cruise speed of 30m/s, the drone would operate up to an altitude of 1500m and be able to land within a 20m radius of a designated landing spot. The laboratory chose a flying wing model. Additionally, the aircraft would have an airbrake system integrated into the platform. The aerodynamic requirements were configurated through the use of a 'constraint diagram'. The airfoil was selected by conducting a literature search and constructing an airfoil performance matrix. The airframe was designed computationally using the software XFLR5, a Vortex Lattice Method solver for low Reynolds numbers. The airframe was then flight tested and validated using the autopilot logs to confirm the predicted aerodynamic performance. The airbrake system was implemented post flight testing of the airframe and was designed using Stat-Ease 360 software, which is a compiled GUI interface used to generate designed experiments. A response surface was generated using airbrake models created in XFLR5. This response surface was then used to find a list of potential airbrake solutions. The most promising solutions were selected to be wind tunnel tested. After successful wind tunnel testing, another design of experiments was created to flight test the airbrake system. The airbrake system unfortunately was never able to be flight tested due to complications with a launcher system designed outside of the scope of this thesis. Alternatively, the methodology of how to flight test an airbrake system was documented and a trainer aircraft fitted with an airbrake system was flight tested with all data logged and analyzed postflight. After validating the aerodynamic profile and airbrake system, the aerodynamic performance of the aircraft outperformed all predictions. Additionally, while the airbrake system itself was never flight tested, all computational and experimental data points toward encouraging results. If the launcher system is improved, a future flight test using the methodology created could confirm the performance of the airbrake system.
546 $a English
590 $a School code: 0418
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Aeronomy. $3 2102064
653 $a Airbrake models
653 $a Flight test
653 $a Airfoil performance matrix
690 $a 0538
690 $a 0367
710 2 $a Old Dominion University. $b Mechanical & Aerospace Engineering. $e degree granting institution. $3 3830044
720 1 $a Landman, Drew $e degree supervisor.
773 0 $t Masters Abstracts International $g 86-03.
790 $a 0418
791 $a M.S.
792 $a 2024
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31558250