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Minimum Induced Power for a Helicopt...

Washington University in St. Louis.

Minimum Induced Power for a Helicopter in High-Speed Forward Flight.

紀錄類型:	書目-語言資料,印刷品 : Monograph/item
正題名/作者:	Minimum Induced Power for a Helicopter in High-Speed Forward Flight./
作者:	Hong, JunSoo (Sean).
出版者:	Ann Arbor : ProQuest Dissertations & Theses, : 2017,
面頁冊數:	92 p.
附註:	Source: Dissertation Abstracts International, Volume: 79-02(E), Section: B.
Contained By:	Dissertation Abstracts International79-02B(E).
標題:	Mechanical engineering. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=10621943
ISBN:	9780355229202

Minimum Induced Power for a Helicopter in High-Speed Forward Flight.
Hong, JunSoo (Sean).

Minimum Induced Power for a Helicopter in High-Speed Forward Flight. - Ann Arbor : ProQuest Dissertations & Theses, 2017 - 92 p.

Source: Dissertation Abstracts International, Volume: 79-02(E), Section: B.

Thesis (Ph.D.)--Washington University in St. Louis, 2017.

A dynamic inflow model is used to calculate minimum induced power for a helicopter in high-speed forward flight with infinite and finite number of blades. Comparisons between analytical and numerical results are shown and they show good agreement. Different flow conditions (such as with and without reverse flow or inflow feedback) are used to show how each condition affects optimum induced power. Several results confirm the findings of earlier investigations such as a singularity in rotor power in reverse flow and induced power reduction with increase in blade number. Some of the new findings are that greater inflow feedback (due to greater solidity) reduces the induced power for an infinite-bladed rotor. For a rotor with a finite number of blades, the addition of inflow feedback can either increase or decrease optimum power depending on the flight conditions. Results obtained using higher harmonic blade pitch control show that induced power can be thereby reduced for all conditions.

ISBN: 9780355229202Subjects--Topical Terms:

557493
Mechanical engineering.

Minimum Induced Power for a Helicopter in High-Speed Forward Flight.
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300 $a 92 p.
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500 $a Adviser: David A. Peters.
502 $a Thesis (Ph.D.)--Washington University in St. Louis, 2017.
520 $a A dynamic inflow model is used to calculate minimum induced power for a helicopter in high-speed forward flight with infinite and finite number of blades. Comparisons between analytical and numerical results are shown and they show good agreement. Different flow conditions (such as with and without reverse flow or inflow feedback) are used to show how each condition affects optimum induced power. Several results confirm the findings of earlier investigations such as a singularity in rotor power in reverse flow and induced power reduction with increase in blade number. Some of the new findings are that greater inflow feedback (due to greater solidity) reduces the induced power for an infinite-bladed rotor. For a rotor with a finite number of blades, the addition of inflow feedback can either increase or decrease optimum power depending on the flight conditions. Results obtained using higher harmonic blade pitch control show that induced power can be thereby reduced for all conditions.
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