Publications

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Journal Article
El-Gendi, M., M. K. IBRAHIM, K. Mori, and Y. Nakamura, "Comparison Between Hot and Cold Flow Conditions of a Turbine Cascade", Transaction of Japan Society for Aeronautical and Space Sciences, vol. 53, issue 181, pp. 171-179, 2010. PDF
Ochi, A., M. K. IBRAHIM, and Y. Nakamura, "Computational Fluid Dynamics Validation Study of Wake-Capturing Capability for Flat-Plate Wake", Journal of Aircraft, vol. 47, issue 2, pp. 441-449, 2010. PDF
El-Ghandour, M., M. K. IBRAHIM, K. Mori, and Y. Nakamura, "Control of Leakage Flow by Triple Squealer Configuration in Axial Flow Turbine", The Transaction of The Japan Society for Aeronautical and Space Sciences, vol. 53, issue 179, pp. 1-7, 2010. PDF
IBRAHIM, M. K., and Y. Nakamura, "Correlation Between Linear Stability Theory and Transition of Compressible Jet Shear Layer", Transaction of The Japan Society for Aeronautical and Space Sciences, vol. 45, issue 147, pp. 35-44, 2002. PDF
IBRAHIM, M. K., A. Abohelwa, and G. B. Salem, "Design, Fabrication and Testing of a Supersonic Wind Tunnel for Educational Purposes", International journal of mechanical engineering education, Manchester University, UK,, vol. 37, issue 4, pp. 286-303, 2009. PDF
IBRAHIM, M. K., and Y. Nakamura, "Effects of Rotating Tabs on Flow and Acoustic Fields of Supersonic Jet", AIAA Journal, vol. 39, issue 4, pp. 745-748, 2002. PDF
El-Ghandour, M., M. K. IBRAHIM, K. DOI, and Y. Nakamura, "Effects of Tip Cavity Depth, Width, and Location on the Leakage Flow in an Axial Turbine Cascade", Journal of Fluid Science and Technology, vol. 5, issue 2, pp. 558-573, 2010. PDF
El-Gendi, M., M. K. IBRAHIM, K. Mori, and Y. Nakamura, "Energy Separation in a High Subsonic Turbine Cascade", Transaction of The Japan Society for Aeronautical and Space Sciences, vol. 152, issue 47, pp. 206-212, 2010. PDF
IBRAHIM, M. K., "Experimental and Theoretical Investigation on Edge Tones in High Speed Jets", Journal of Fluid Science and Technology, vol. 8, issue 1, pp. 1-19, 2013. PDF
IBRAHIM, M. K., N. Miya, K. Mori, and Y. Nakamura, "Experimental Investigation of Noise and Flow Characteristics of Supersonic Underexpanded Jet Interaction with a Coannular Tube", The Transaction of The Japan Society for Aeronautical and Space Sciences, 2014.
IBRAHIM, M. K., T. Sawai, K. Obase, K. Mori, and Y. Nakamura, "Experimental Investigation of Screech-Tone Characteristics of Jet Interaction with a Flat Plate", AIAA Journal, vol. 47, issue 9, pp. 2031-2038, 2009. PDF
IBRAHIM, M. K., "Image Processing-Based Technique for Computation of Axial Sound Source Distribution in a Chocked Screech Jet", International Review of Aerospace Engineering (IREASE), vol. 6, issue 1, pp. 76-82, 2013. PDF
IBRAHIM, M. K., R. Kunimura, and Y. Nakamura, "Mixing Enhancement of Compressible Jets by Using Unsteady Micro-Jets as Actuator", AIAA Journal, vol. 40, issue 4, pp. 681-688, 2002. PDF
El-Gendi, M., M. K. IBRAHIM, K. Mori, and Y. Nakamura, "Novel Flow Control Method of Vortex Shedding for a Turbine", The Transaction of The Japan Society for Aeronautical and Space Sciences, vol. 53, issue 180, pp. 122-129, 2010. PDF
IBRAHIM, M. K., and S. M. El-Haggar, "Parametric Study of Solar Hydrogen Production From Saline Water Electrolysis", International Journal of Environment and Pollution, vol. 8, issue 1-2, pp. 164-173, 1997. PDF
IBRAHIM, M. K., T. Nakamura, K. Kitamura, K. Mori, and Y. Nakamura, "The Role of Vortices in Side Jet/Blunt Body Interaction at Hypersonic Speed", Transaction of The Japan Society for Aeronautical and Space Sciences, Space Technology Japan (Online), vol. 7, pp. 1-10, 2009. PDF
Mori, K., Y. MURAHASHI, Y. KOGA, Y. Nakamura, M. K. IBRAHIM, T. TAKAHASHI, and K. MURAKAMI, "A simple technique for the precise measurement of transmission loss of planar sound waves", AIAA Journal , vol. 48, issue 10, pp. 2377-2385., 2010. PDF
IBRAHIM, M. K., S. Matsumoto, K. Mori, and Y. Nakamura, "Visualization of Pressure Field over Rotating Blades using Pressure Sensitive Foil Technique", " , The Transaction of The Japan Society for Aeronautical and Space Sciences, vol. 53, issue 182, pp. 243-249, 2011. AbstractPDF

This paper describes a new pressure measurement technique for measuring the pressure over rotating blades of an industrial axial flow fan. The new technique is called the pressure sensitive foil (PS-Foil) technique. In this technique, a very thin aluminum foil is coated with pressure sensitive paint using anodization. The resulting PS-Foil can be stuck on any blade using a very thin layer of silicon. The PS-Foil technique shows a very fast time response like conventional porous anodized aluminum and can be applied to any rotor blade without fabricating the blade from aluminum. The total thickness of the aluminum foil and silicon layer is as small as 200 μm. An intensity based method and prior calibration procedures are used to obtain the calibrated PSP image. The unsteady experimental setup presented here shows that the PS-Foil time response is on the order 30 μs which is close to the conventional porous anodized aluminum method. Two applications are considered here to assess the applicability of this technique. Subsonic jet-plate impingement, and rotating blade of industrial fan. The pressure distribution over the impingement plate at different plate angles, and over the rotating blade at various speeds could be obtained with sufficient spatial resolution.

Report
TAKAHASHI, T., H. KANEDA, K. MURAKAMI, A. HASHIMOTO, T. AOYAMA, Y. KOGA, N. Miya, M. K. IBRAHIM, K. Mori, and Y. Nakamura, Study on Steady-State Sound Transmission and Propagation Analysis Using the Two-Dimensional Wave Based Method, , ISSN 1349-1113, JAXA-RR-09-008, Japan Aerospace Exploration Agency, pp. 1-18, 03, 2010. PDF
TAKAHASHI, T., H. KANEDA, K. MURAKAMI, A. HASHIMOTO, T. AOYAMA, M. K. IBRAHIM, Y. MURAHASHI, K. Mori, and Y. Nakamura, Verification of the Numerical Prediction Method by Fundamental Sound Transmission Experiments for Fairing Materials: Aluminum Plates, , ISSN 1349-1113, JAXA-RR-09-009, Japan Aerospace Exploration Agency, pp. 1-47, 03, 2010. AbstractPDF

The mechanical vibration is applied to a spacecraft via the interface to a launch vehicle at lift-off. The spacecraft is also exposed to acoustic pressure with wide frequency range. Lightweight and large area structures, such as solar paddles, antennas, and components with relatively high natural frequencies, are sensitive to acoustic load. Although the acoustic tests are usually conducted for components and system of the spacecraft, acoustic tests and analysis of the spacecraft mounted in a fairing have not been sufficiently done. It is expected that numerical analysis can be applied to the prediction of acoustic environment inside of fairings. Japan Aerospace Exploration Agency (JAXA) has been developing a vibroacoustic prediction tool by the wave based method (WBM), which is one of the deterministic approaches and is proposed for numerical prediction up to the mid-frequency range. The existing deterministic approaches can not accurately solve vibroacoustic problems in this range. In this paper, numerical prediction results of sound transmission by the 3D WBM and FEM are compared with those by an experiment, and verification of the 3D WBM is examined.

Thesis
IBRAHIM, M. K., On Mixing Enhancement and Noise Emission of High Speed Jet Flows, , Nagoya, Japan, Nagoya University, 2002. PDF
IBRAHIM, M. K., On The Solution of Two-Dimensional Transonic Flows, , Giza, Cairo University, 1996. PDF
Tourism