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Low-Order Modeling of Propeller-Wing Interaction Using a Modified Weissinger Method.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Low-Order Modeling of Propeller-Wing Interaction Using a Modified Weissinger Method./
作者:	D'Angelo, Brendan Kyle.
面頁冊數:	1 online resource (96 pages)
附註:	Source: Masters Abstracts International, Volume: 83-05.
Contained By:	Masters Abstracts International83-05.
標題:	Aircraft. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=28814847click for full text (PQDT)
ISBN:	9798494455284

Low-Order Modeling of Propeller-Wing Interaction Using a Modified Weissinger Method.
D'Angelo, Brendan Kyle.

Low-Order Modeling of Propeller-Wing Interaction Using a Modified Weissinger Method. - 1 online resource (96 pages)

Source: Masters Abstracts International, Volume: 83-05.

Thesis (M.Sc.)--North Carolina State University, 2021.

Includes bibliographical references

This thesis aims to present a low-order method for the prediction of propeller interaction effects on a wing regarding the total lift and lift distributions. A wing model based on the Weissinger method is modified to predict the effect of a propeller upstream of the wing. Two different propeller models are used to determine the propeller induced velocities within the slipstream. The first model is a vortex ring method, which predicts the propeller axial induced velocity. The second model is a blade performance theory, which utilizes the induced velocity calculated by the vortex ring method and predicts the propeller tangential velocity along with a more detailed axial induced velocity. However, with limited propeller geometry, the vortex ring axial induced velocity is used over the blade performance theory results because it remains more consistent for a variety of propeller types and configurations. Utilizing these methods minimizes the number of inputs required for the model to predict the interaction effects as well as keeping the computational cost very low compared to more detailed solvers. The low computational cost allows for rapid testing of various propeller-wing configurations to narrow down design choices. Overall, the lift distributions show good agreement with numerical and experimental data for a variety of different cases. Only major discrepancies occurred near and beyond stall, where the inviscid nature of the model is unable to make accurate predictions. General trends in overall wing lift are also captured by the model even in difficult cases such as low aspect ratios and low Reynolds numbers.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2023

Mode of access: World Wide Web

ISBN: 9798494455284Subjects--Topical Terms:

832698
Aircraft.
Index Terms--Genre/Form:

542853
Electronic books.

Low-Order Modeling of Propeller-Wing Interaction Using a Modified Weissinger Method.
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100 1 $a D'Angelo, Brendan Kyle. $3 3694413
245 1 0 $a Low-Order Modeling of Propeller-Wing Interaction Using a Modified Weissinger Method.
264 0 $c 2021
300 $a 1 online resource (96 pages)
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500 $a Source: Masters Abstracts International, Volume: 83-05.
500 $a Advisor: Granlund, Kenneth; Bryant, Matthew.
502 $a Thesis (M.Sc.)--North Carolina State University, 2021.
504 $a Includes bibliographical references
520 $a This thesis aims to present a low-order method for the prediction of propeller interaction effects on a wing regarding the total lift and lift distributions. A wing model based on the Weissinger method is modified to predict the effect of a propeller upstream of the wing. Two different propeller models are used to determine the propeller induced velocities within the slipstream. The first model is a vortex ring method, which predicts the propeller axial induced velocity. The second model is a blade performance theory, which utilizes the induced velocity calculated by the vortex ring method and predicts the propeller tangential velocity along with a more detailed axial induced velocity. However, with limited propeller geometry, the vortex ring axial induced velocity is used over the blade performance theory results because it remains more consistent for a variety of propeller types and configurations. Utilizing these methods minimizes the number of inputs required for the model to predict the interaction effects as well as keeping the computational cost very low compared to more detailed solvers. The low computational cost allows for rapid testing of various propeller-wing configurations to narrow down design choices. Overall, the lift distributions show good agreement with numerical and experimental data for a variety of different cases. Only major discrepancies occurred near and beyond stall, where the inviscid nature of the model is unable to make accurate predictions. General trends in overall wing lift are also captured by the model even in difficult cases such as low aspect ratios and low Reynolds numbers.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2023
538 $a Mode of access: World Wide Web
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650 4 $a Design. $3 518875
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650 4 $a Designers. $3 589292
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Engineering. $3 586835
650 4 $a Mathematics. $3 515831
655 7 $a Electronic books. $2 lcsh $3 542853
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710 2 $a North Carolina State University. $3 1018772
773 0 $t Masters Abstracts International $g 83-05.
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=28814847 $z click for full text (PQDT)