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Analysis of Drag Coefficient in the Dynamic Modeling of a Hobby Lander.

Record Type:	Language materials, manuscript : Monograph/item
Title/Author:	Analysis of Drag Coefficient in the Dynamic Modeling of a Hobby Lander./
Author:	Montgomery, Leanne.
Description:	1 online resource (133 pages)
Notes:	Source: Masters Abstracts International, Volume: 85-03.
Contained By:	Masters Abstracts International85-03.
Subject:	Mechanical engineering. -
Online resource:	click for full text (PQDT)
ISBN:	9798380165730

Analysis of Drag Coefficient in the Dynamic Modeling of a Hobby Lander.
Montgomery, Leanne.

Analysis of Drag Coefficient in the Dynamic Modeling of a Hobby Lander. - 1 online resource (133 pages)

Source: Masters Abstracts International, Volume: 85-03.

Thesis (M.S.)--Southern Illinois University at Edwardsville, 2023.

Includes bibliographical references

Since the advent of hobby rocketry, enthusiasts have sought to effectively model vehicle behavior through flight, descent, and landing. Simple landers, while less common than rockets, allow hobbyists to examine new aspects of the physics and aerodynamics of flight. One of the key components in modeling a freefall landing is the coefficient of drag (Cd). This project aims to clarify the effects of Reynolds number and angle of attack on the drag coefficient for a lander using a three-pronged approach. First, wind tunnel experiments are conducted to measure the drag coefficient in an incompressible regime up to Reynolds numbers of 90,400 at angles up to 15°. Next, computational fluid dynamics (CFD) simulations are used to validate the wind tunnel results within the same range of Reynolds numbers and angles of attack. Finally, data is collected from lander descents in the field. Numerical results demonstrate that Cd increases with Reynolds number according to a power curve. Cd for a 5° angle of attack is 17% greater than for the lander in axial flow, and Cd for a 15° angle of attack is 74% greater. While modeling lander freefall with constant Cd will underestimate drag vs. modeling with variable-Cd, the differences in time of flight are no more than 3% for the cases considered, and less than 0.5% for the range of operation for this model lander.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2024

Mode of access: World Wide Web

ISBN: 9798380165730Subjects--Topical Terms:

557493
Mechanical engineering.
Subjects--Index Terms:

RocketsIndex Terms--Genre/Form:

554714
Electronic books.

Analysis of Drag Coefficient in the Dynamic Modeling of a Hobby Lander.
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500 $a Advisor: Yan, Terry.
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504 $a Includes bibliographical references
520 $a Since the advent of hobby rocketry, enthusiasts have sought to effectively model vehicle behavior through flight, descent, and landing. Simple landers, while less common than rockets, allow hobbyists to examine new aspects of the physics and aerodynamics of flight. One of the key components in modeling a freefall landing is the coefficient of drag (Cd). This project aims to clarify the effects of Reynolds number and angle of attack on the drag coefficient for a lander using a three-pronged approach. First, wind tunnel experiments are conducted to measure the drag coefficient in an incompressible regime up to Reynolds numbers of 90,400 at angles up to 15°. Next, computational fluid dynamics (CFD) simulations are used to validate the wind tunnel results within the same range of Reynolds numbers and angles of attack. Finally, data is collected from lander descents in the field. Numerical results demonstrate that Cd increases with Reynolds number according to a power curve. Cd for a 5° angle of attack is 17% greater than for the lander in axial flow, and Cd for a 15° angle of attack is 74% greater. While modeling lander freefall with constant Cd will underestimate drag vs. modeling with variable-Cd, the differences in time of flight are no more than 3% for the cases considered, and less than 0.5% for the range of operation for this model lander.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2024
538 $a Mode of access: World Wide Web
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