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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.

Record Type:	Language materials, printed : Monograph/item
Title/Author:	Minimum Induced Power for a Helicopter in High-Speed Forward Flight./
Author:	Hong, JunSoo (Sean).
Published:	Ann Arbor : ProQuest Dissertations & Theses, : 2017,
Description:	92 p.
Notes:	Source: Dissertation Abstracts International, Volume: 79-02(E), Section: B.
Contained By:	Dissertation Abstracts International79-02B(E).
Subject:	Mechanical engineering. -
Online resource:	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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100 1 $a Hong, JunSoo (Sean). $0 (orcid)0000-0002-9156-7779 $3 1148608
245 1 0 $a Minimum Induced Power for a Helicopter in High-Speed Forward Flight.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2017
300 $a 92 p.
500 $a Source: Dissertation Abstracts International, Volume: 79-02(E), Section: B.
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.
590 $a School code: 0252.
650 4 $a Mechanical engineering. $3 557493
650 4 $a Aerospace engineering. $3 686400
650 4 $a Engineering. $3 561152
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710 2 $a Washington University in St. Louis. $b Mechanical Engineering. $3 1148609
773 0 $t Dissertation Abstracts International $g 79-02B(E).
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793 $a English
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=10621943

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