scholarly journals Pengembangan Aplikasi Manajemen Informasi Magang Terowongan Angin Kecepatan Rendah Indonesia

2020 ◽  
Vol 4 (3) ◽  
pp. 297
Author(s):  
Ivransa Zuhdi Pane
Keyword(s):  
Wind Tunnel ◽  
Information Management ◽  
Task Allocation ◽  
Positive Impact ◽  
Wind Tunnel Test ◽  
Service Business ◽  
Engineering Activity ◽  
Management Application ◽  
And Performance ◽  
Low Speed Wind Tunnel

<em>An </em><em>internship information management application at Indonesian Low Speed Wind Tunnel facility is useful for supporting managerial tasks related to internship activities, ranging from registration, task allocation, task implementation supervision to evaluation of the work results of the apprentices. This application is expected to not only support productivity and performance, but also provide input for management in making decisions related to the employment of apprentices in order to realize a synergy that has a positive impact on the smooth process of the wind tunnel test service business as a whole. To realize it, a software engineering activity by adopting prototyping methodology is carried out to build the application to be then operated in a desktop platform and be used as needed</em>

STOVL Hot Gas Ingestion Control Technology

1989 ◽  
Author(s):  
K. C. Amuedo ◽  
B. R. Williams ◽  
J. D. Flood ◽  
A. L. Johns
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Scale Model ◽  
Nasa Lewis Research ◽  
Control Technology ◽  
Test Program ◽  
Hot Gas ◽  
Vertical Landing ◽  
Low Speed Wind Tunnel ◽  
Face Temperature

A comprehensive wind tunnel test program was conducted to evaluate control of Hot Gas Ingestion (HGI) on a 9.2% scale model of the McDonnell Aircraft Company model 279-3C advanced Short Takeoff and Vertical Landing (STOVL) configuration. The test was conducted in the NASA-Lewis Research Center 9 foot by 15 foot Low Speed Wind Tunnel during the summer of 1987. Initial tests defined baseline HGI levels as determined by engine face temperature rise and temperature distortion. Subsequent testing was conducted to parametrically evaluate HGI control using: Lift Improvement Devices (LIDs), forward nozzle splay angle, combination of LIDs and forward nozzle splay angle, and main inlet blocking. The results from this test program demonstrate that HGI can be effectively controlled and that HGI is not a barrier to STOVL aircraft development.

Composite Wing Flutter Speed and Frequency due to Variable Control Surface Deflection in Low Speed Wind Tunnel

2013 ◽  
Vol 390 ◽  
pp. 3-7
Author(s):  
Muhammad Iyas Mahzan ◽  
Sallehuddin Muhamad ◽  
Sa’ardin Abdul Aziz ◽  
Mohamed Sukri Mat Ali
Keyword(s):  
Wind Tunnel ◽  
Dynamic Instability ◽  
Wind Tunnel Test ◽  
Control Surface ◽  
Wing Flutter ◽  
Flutter Speed ◽  
Surface Deflection ◽  
Relationship Of ◽  
Low Speed Wind Tunnel ◽  
The Relationship

Flutter is a dynamic instability problem represents the interaction among structural, aerodynamic, elastic and inertial forces and occurred when the energy is continuously transformed by the surrounding fluids to a flying structure in the form of kinetic energy. The study was conducted to investigate the relationship of the control surface deflection angle to the flutter speed and the flutter frequency. A wind tunnel test was performed using a flat plate wing made of composite material. It was found that by deflecting the control surface up to 45°, the flutter speed reduced almost linearly from 35.6 m/s to 22.7 m/s. The flutter frequency greatly reduced from 48 Hz without the control surface deflected to 34 Hz with the control surface deflected at 15°. After 15° deflection up to 45°, the flutter frequency reduced almost linearly.

LOW SPEED WIND TUNNEL TEST OF THE JET TRAINER MODEL AT HIGH ANGLES OF ATTACK

2016 ◽  
Vol 23 (4) ◽  
pp. 471-478
Author(s):  
Kamil Smędra ◽  
Rafał Świerkot ◽  
Krzysztof Kubryński
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Low Speed ◽  
Low Speed Wind Tunnel ◽  
High Angles Of Attack

scholarly journals Pengembangan Aplikasi Pengendalian Mutu Uji Terowongan Angin Kecepatan Rendah Indonesia

2020 ◽  
Vol 4 (2) ◽  
pp. 277
Author(s):  
Ivransa Zuhdi Pane
Keyword(s):  
Information Technology ◽  
Quality Control ◽  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Control Unit ◽  
Control Mechanisms ◽  
Good Test ◽  
Other Information ◽  
Executive Decision Making ◽  
And Performance

Quality control in the wind tunnel test service in the Indonesian Low Speed Tunnel plays an important role to produce good test results, but it is still being done in a manual and traditional way. As a result, there are still problems in the implementasion and evaluation of quality control of a wind tunnel test. The quality control which is managed by utilizing information technology can not only solve such problems, but also encourage productivity and performance of quality control unit personnel in carrying out their duties. The development of quality control applications as a form of utilizing information technology through software engineering stages, starting from requirements analysis, design, construction and software testing, is expected to be able to realize contemporary quality control mechanisms and integrated with other information management activities which in turn support the management in executive decision making

scholarly journals Application of the HPCMP CREATETM-AV Kestrel to an Integrated Propeller Prediction

Aerospace ◽  
2020 ◽  
Vol 7 (12) ◽  
pp. 177
Author(s):  
Pooneh Aref ◽  
Mehdi Ghoreyshi ◽  
Adam Jirasek ◽  
Jürgen Seidel
Keyword(s):  
Experimental Data ◽  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Test Case ◽  
Simulation Tools ◽  
Electric Aircraft ◽  
Computational Resources ◽  
Adaptive Cartesian Grid ◽  
Low Speed Wind Tunnel ◽  
Wing Tip

This article presents the results of a computational investigation of an integrated propeller test case using the HPCMP CREATETM-AV Kestrel simulation tools. There is a renewed interest in propeller-driven aircraft for unmanned aerial vehicles, electric aircraft, and flying taxies. Computational resources can significantly accelerate the generation of aerodynamic models for these vehicles and reduce the development cost if the prediction tools can accurately predict the aircraft/propeller aerodynamic interactions. Unfortunately, limited propeller experimental data are available to validate computational methods. An American Institute of Aeronautics and Astronautics (AIAA) workshop was therefore established to address this problem. The objective of this workshop was to generate an open access-powered wind tunnel test database for computational validation of propeller effects on the wing aerodynamics, specifically for wing-tip-mounted propellers. The propeller selected for the workshop has four blades and a diameter of 16.2 in. The wing has a root and tip chord of 11.6 and 8.6 in, respectively. Two different simulation approaches were used: one using a single grid including wind tunnel walls and the second using a subset grid overset to an adaptive Cartesian grid that fills the space between the near-body grid and wind tunnel walls. The predictions of both approaches have been compared with available experimental data from the Lockheed Martin low-speed wind tunnel to investigate the grid resolution required for accurate prediction of flowfield data. The results show a good agreement for all tested conditions. The measured and predicted data show that wing aerodynamic performance is improved by the spinning tip-mounted propeller.

scholarly journals High lift device design and low speed wind-tunnel test.

1986 ◽  
Vol 34 (394) ◽  
pp. 592-599
Author(s):  
Masanobu OGAKI ◽  
Takeshi WATANABE ◽  
Kanichi AMANO
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Device Design ◽  
High Lift ◽  
Low Speed ◽  
Low Speed Wind Tunnel
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