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Development of a computer program for rocket aerodynmic coefficients estimation

A computational method has been developed to realize an efficient and accurate user friendly computational program called RocketCalculator, which integrates carefully assessed methodologies and offer flexibilities of the rocket configurations and velocities up to Mach number 3.0 and angle of attack...

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Main Authors: Dahalan, Md. Nizam, Su, Vin Cent, Ammoo, Mohd. Shar
Format: Article
Language:English
English
Published: Faculty of Mechanical Engineering, UTM 2009
Subjects:
T Technology (General)
TJ Mechanical engineering and machinery
Online Access:http://eprints.utm.my/id/eprint/21023/1/MdNizamDahalan2009_DevelopmentOfAComputerProgram.pdf
http://eprints.utm.my/id/eprint/21023/2/nizam_Rocket-I-2009_28-43.pdf
http://eprints.utm.my/id/eprint/21023/
http://dms.library.utm.my:8080/vital/access/manager/Repository/vital:67933
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spelling my.utm.210232017-10-13T10:20:55Z http://eprints.utm.my/id/eprint/21023/ Development of a computer program for rocket aerodynmic coefficients estimation Dahalan, Md. Nizam Su, Vin Cent Ammoo, Mohd. Shar T Technology (General) TJ Mechanical engineering and machinery A computational method has been developed to realize an efficient and accurate user friendly computational program called RocketCalculator, which integrates carefully assessed methodologies and offer flexibilities of the rocket configurations and velocities up to Mach number 3.0 and angle of attack of 25 degrees. The RocketCalculator is capable of analyzing the configurations of wing-alone, bodyalone, wing-body combination, and wing-body-tail combination of rocket. USAF Datcom Method has been chosen as the analysis method and the programming language is Microsoft Visual Basic. The result would be displayed in form of the corresponding lift (CL ), normal force (CN ) and drag (CD ) coefficients at certain Mach number and angle of attack. Experimented data for several models have been taken out from available sources to validate the program output. Comparisons of the program output and experimental results generally show good agreement with average error of less than 10%. Faculty of Mechanical Engineering, UTM 2009-06 Article PeerReviewed application/pdf en http://eprints.utm.my/id/eprint/21023/1/MdNizamDahalan2009_DevelopmentOfAComputerProgram.pdf text/html en http://eprints.utm.my/id/eprint/21023/2/nizam_Rocket-I-2009_28-43.pdf Dahalan, Md. Nizam and Su, Vin Cent and Ammoo, Mohd. Shar (2009) Development of a computer program for rocket aerodynmic coefficients estimation. Jurnal Mekanikal, 28 . pp. 28-43. ISSN 0127-3396 http://dms.library.utm.my:8080/vital/access/manager/Repository/vital:67933
institution Universiti Teknologi Malaysia
building UTM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Teknologi Malaysia
content_source UTM Institutional Repository
url_provider http://eprints.utm.my/
language English
English
topic T Technology (General)
TJ Mechanical engineering and machinery
spellingShingle T Technology (General)
TJ Mechanical engineering and machinery
Dahalan, Md. Nizam
Su, Vin Cent
Ammoo, Mohd. Shar
Development of a computer program for rocket aerodynmic coefficients estimation
description A computational method has been developed to realize an efficient and accurate user friendly computational program called RocketCalculator, which integrates carefully assessed methodologies and offer flexibilities of the rocket configurations and velocities up to Mach number 3.0 and angle of attack of 25 degrees. The RocketCalculator is capable of analyzing the configurations of wing-alone, bodyalone, wing-body combination, and wing-body-tail combination of rocket. USAF Datcom Method has been chosen as the analysis method and the programming language is Microsoft Visual Basic. The result would be displayed in form of the corresponding lift (CL ), normal force (CN ) and drag (CD ) coefficients at certain Mach number and angle of attack. Experimented data for several models have been taken out from available sources to validate the program output. Comparisons of the program output and experimental results generally show good agreement with average error of less than 10%.
format Article
author Dahalan, Md. Nizam
Su, Vin Cent
Ammoo, Mohd. Shar
author_facet Dahalan, Md. Nizam
Su, Vin Cent
Ammoo, Mohd. Shar
author_sort Dahalan, Md. Nizam
title Development of a computer program for rocket aerodynmic coefficients estimation
title_short Development of a computer program for rocket aerodynmic coefficients estimation
title_full Development of a computer program for rocket aerodynmic coefficients estimation
title_fullStr Development of a computer program for rocket aerodynmic coefficients estimation
title_full_unstemmed Development of a computer program for rocket aerodynmic coefficients estimation
title_sort development of a computer program for rocket aerodynmic coefficients estimation
publisher Faculty of Mechanical Engineering, UTM
publishDate 2009
url http://eprints.utm.my/id/eprint/21023/1/MdNizamDahalan2009_DevelopmentOfAComputerProgram.pdf
http://eprints.utm.my/id/eprint/21023/2/nizam_Rocket-I-2009_28-43.pdf
http://eprints.utm.my/id/eprint/21023/
http://dms.library.utm.my:8080/vital/access/manager/Repository/vital:67933
_version_ 1643647247998517248
score 13.211869

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