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ITS » Undergraduate Theses » Teknik Mesin
Posted by ida at 15/01/2010 16:21:48  •  2998 Views


STUDI EKSPERIMENTAL ALIRAN MELINTAS AIRFOIL NASA LS-0417 DENGAN PENAMBAHAN ENDPLATE DISERTAI DENGAN VARIASI REYNOLDS NUMBER DAN SUDUT SERANG SERTA VISUALISASI ALIRAN

EXPERIMENTAL STUDY OF FLUID FLOW CHARACTERISTIC THROUGH AIRFOIL NASA LS-0417 WITH ENDPLATES AS ADDITIONAL EQUIPMENT VARY IN REYNOLDS NUMBER AND ANGLE OF ATTACK COMPLETED WITH FLOW VISUALIZATION

Author :
Prasetya, Mahendra Eka 




ABSTRAK

Pemodelan airfoil sangat penting dilakukan terutama dalam menentukan keberhasilan unjuk kerja airfoil tersebut. Salah satu yang terpenting untuk diperhatikan dalam desain airfoil adalah bagaimana membuat airfoil dengan lift L yang tinggi disertai dengan drag D yang rendah sehingga akan didapat perbandingan 911991209118911691179115DL besar. Pada penelitian ini dilakukan pada desain airfoil NASA LS 0417 dengan menambah endplate pada ujung airfoil. Secara garis besar penambahan endplate pada sisi ujung airfoil atau wilayah tipspan bertujuan untuk menghindari terjadinya tip vortex. Timbulnya Tip Vortex diakibatkan oleh adanya aliran dari bawah sayap menuju atas melalui ujung sayap hal ini dapat dicegah dengan adanya penambahan endplate. Sehingga aliran dari bawah sayap terhalangi untuk naik kearah atas sayap yang menyebabkan tidak terjadinya tip vortex dan pengurangan daerah efektif dari aliran atas sayap. Akibatnya induced downwash velocities tidak akan terjadi dan pengurangan effective angle of attack pun tidak terjadi. Hal ini mengakibatkan lift yang dihasilkan dapat lebih optimal jika dibanding dengan kondisi plain airfoil. Hasil analisa unjuk kerja airfoil NASA LS 0417 dengan penambahan endplate menunjukkan adanya peningkatan unjuk kerja airfoil itu sendiri. Hal ini ditunjukkan dengan semakin naiknya coefficient lift. Meskipun juga diikuti oleh semakin meningkatnya coefficient drag tetapi tidak terlalu sigifikan. Sehingga pada hasil perbandingan coefficient lift dan coefficient drag hasilnya didapat lebih baik dari plain airfoil. Sehingga dapat disimpulkan bahwa penambahan endplate berhasil mengurangi adanya tip vortex yang terjadi pada tipspan dari suatu airfoil.


ABSTRACT

Airfoils customization is very important to be done especially for determining airfoils effectivity. One of the most important things to consider is how to make airfoil with high lift force and low drag force so we can achieve high comparison between lift forces and drag forces. In this research concern about the addition of endplate on the tip area of NASA LS 0417 airfoil. The point of endplate addition on the tip area or tip span is avoiding tip vortex. Tip vortex caused by downside flow of airfoil to the upper side through the tip area that is can be avoided by the endplate addition. So the downside flow can not flow to upper side of airfoil through tips area and the correction of effective area for the upper side flow. As the result induced downwash velocities wont happen and neither correction of angle of attack. Then lift force can be produced better than plain airfoil. As result of effectiveness of NASA LS 0417 airfoil with the endplate addition show there is an increase of airfoils effectiveness. This result can be seen with the increasing of lift coefficient. Although drag coefficient is also increasing but that is not very significant. Then we can have the comparison of lift coefficient and drag coefficient is higher than plain airfoil. So we can conclude that endplate addition for NASA LS 0417 airfoil decrease the cause of tip vortex that happen on the tip area of NASA LS 0417 airfoil effectively.



Keywords"airfoil NASA LS 0417tip vortex, endplate, effective angle of attack, induced downwash velocities i"
 
Subject:  Aerofoils
Contributor
  1. Dr. Ir. Sutardi, Meng
Date Create: 15/01/2010
Type: Text
Format: pdf
Language: Indonesian
Identifier: ITS-Undergraduate-3100006025673
Collection ID: 3100006025673
Call Number: RSM 629.134 32 Pra s


Source
Undergraduate Theses of MECHANICAL ENGINEERING Industrial Technology Faculty, RSM 629.134 32 Pra s, 2006

Coverage
ITS Community Only

Rights
Copyright @2006 by ITS Library. This p ublication is protected by copyright and permission should be obtained from the ITS Library prior to any prohibited reproduction, storage in a retrievel system, or transmission in any form or by any means, electronic, mechanical, photocopying, recording, or likewise. For information regarding permission(s), write to ITS Library




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  1.  ITS-Undergraduate-8049-2100100025-kesimpulan.pdf - 114 KB




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