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ITS » Undergraduate Theses » Teknik Mesin Ekstensi - S1
Posted by dee@its.ac.id at 31/01/2012 14:04:30  •  2009 Views


STUDI KARAKTERISTIK ALIRAN CELAH DIANTARA AIRFOIL SIMETRI DENGAN PELAT DATAR STUDI KASUS UNTUK VARIASI LEBAR CELAH HC 0.15 0.2 DAN 0.3

FLOW CHARACTERISTICS OF STUDY GAP BETWEEN AIRFOIL SYMMETRY WITH FLAT PLATE CASE STUDY FOR THE VARIATION GAP WIDTH h C 015 0.2 AND 0.3

Author :
PRASETYO, HUDDY TRI ( 2105109608 )




ABSTRAK

Fluida yang mengalir melewati permukaan dari suatu profil akan terpengaruh oleh suatu gradient tekanan dimana kecepatan aliran lokal sepanjang streamline dekat permukaan profil berubah seiring dengan perubahan tekanan sepanjang permukaan. Perubahan gradient kontur dari profil mempengaruhi gradient tekanan yang terjadi sepanjang kontur profil perubahan pola gradient tekanan mempengaruhi medan aliran disekitar profil sehingga berpengaruh pada karakteristik boundary layer yang terbentuk pada profil. Suatu airfoil simetris dengan letak tebal maksimum dan bilangan Reynold tertentu memiliki karakteristik aliran tertentu bila didekatkan dengan end wall akan terpengaruh boundary layer dari end wall sehingga pada lower side airfoil simetris akan terjadi hambatan hidraulis blockage effect dan aliran akan cenderung memilih lintasan yang melalui upperside airfoil simetris. Penelitian ini dilakukan secara eksperimental dalam sebuah wind tunnel benda uji yang digunakan adalah airfoil simetri dengan posisi ketebalan maksimum 03 C dan dengan variasi lebar celah hC 015 02 03. Karakteristik aliran fluida yang diteliti adalah distribusi koefisien tekanan Cp pada aifoil distribusi koefisien tekanan Cp pada wall dan dilakukan visualisasi menggunakan metode oil flow picture pada subsonic wind tunnel dengan Ret 5x104. Hasil yang didapatkan dari penelitian eksperimental ini adalah perubahan titik separasi pada airfoil simetris akibat pengaruh gradient kontur pada airfoil simetris dan boundary layer dari end wall perubahan titik stagnasi yang menuju ke lower side seiring dengan penyempitan celah pengaruh perubahan celah yang semakin sempit untuk hC 015 pada lower side mengakibatkan terjadinya separasi pada xc 8776 05 akibat adanya distribusi tekanan dari wall.


ABSTRACT

Fluid flowing past the surface of a profile will be affected by a pressure gradient in which the local flow velocity along the streamline near the surface of the profiles change with changes in pressure along the surface. Contour of the profile gradient changes affect the pressure gradient that occurs along the contour of the profile changes in the pattern of pressure gradient affects the flow field around the profile so the effect on the characteristics of the boundary layer that forms on the profile. A symmetrical airfoil with maximum thickness and location of certain Reynolds number has a certain flow characteristics when brought near the end wall will be affected from the end wall boundary layer so that at the lower side will be symmetrical airfoil hydraulic resistance blockage effect and the flow will tend to choose the trajectory through the upperside symmetrical airfoil. The research was carried out experimentally in a wind tunnel test object used is a symmetric airfoil with a position of maximum thickness of 0.3 C and the variation of gap width h C 0.15 0.2 0.3. Characteristics of fluid flow under study is the distribution of pressure coefficient Cp in aifoil the distribution of pressure coefficient Cp on the wall and carried out using the method of oil flow visualization picture at subsonic wind tunnel with Ret 5x104. Results obtained from this experimental study was the change point of separation in symmetrical airfoil contour gradient effect due to the symmetrical airfoil and boundary layer from the end wall stagnation point changes leading to the lower side along with the narrowing of the gap the influence of an increasingly narrow for hC 05 on lower side caused sparation of body on xc8776 05 because effect of pressure distribution from end wall.



KeywordsAirfoil simetris; Variasi lebar celah; End wall
 
Subject:  Kerjang udara;Mesin pesawat terbang
Contributor
  1. Prof. DR. Ing. Herman Sasongko
Date Create: 10/08/2011
Type: Text
Format: pdf
Language: Indonesian
Identifier: ITS-Undergraduate-3100012045441
Collection ID: 3100012045441
Call Number: RSM 629.134 32 Pra s


Source
Undergraduate Thesis of Mechanical Engineering, RSM 629.134 32 Pra s, 2012

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Copyright @2011 by ITS Library. This publication is protected by copyright and per obtained from the ITS Library prior to any prohibited reproduction, storage in a re transmission in any form or by any means, electronic, mechanical, photocopying, reco For information regarding permission(s), write to ITS Library




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  1.  ITS-Undergraduate-17543-Abstract_id.pdf - 414 KB
  2.  ITS-Undergraduate-17543-Abstract_en.pdf - 363 KB
  3.  ITS-Undergraduate-17543-Conclusion-358909.pdf - 350 KB




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