Design of Inward-Turning External Compression Supersonic Inlet for Supersonic Transport Aircraft

Muhammad Adnan Utomo, Romie Oktavianus Bura

Abstract


Inward-turning external compression intake is one of the hybrid intakes that employs both external and internal compression intakes principle. This intake is commonly developed for hypersonic flight due to its efficiency and utilizing fewer shockwaves that generate heat. Since this intake employ less shockwaves, this design can be applied for low supersonic (Mach 1.4 - 2.5) intakes to reduce noise generated from the shockwaves while maintaining the efficiency. Other than developing the design method, a tool is written in MATLAB language to generate the intake shape automatically based on the desired design requirement. To investigate the intake design tool code and the performance of the generated intake shape, some CFD simulation were performed. The intake design tool code can be validated by comparing the shockwave location and the air properties in every intake's stations. The performance parameters that being observed are the intake efficiency, flow distortion level at the engine face, and the noise level generated by the shockwaves. The design tool written in MATLAB is working as intended. Two dimensional axisymmetric CFD simulations validation has been done and the design meets the minimum requirement. As for the 3D inlet geometry, with a little modification on diffuser and equipping vent to release the buildup pressure, the inlet has been successfully met the military standard on inlet performance (MIL-E-5007D). This design method also has feature to fit every possible throat cross sectional shapes and has been proven to work as designed.

Keywords— Inward-turning, Supersonic, Engine Intakes, Low- noise, Design Method


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References


Ascher, Uri M., and Lzinda R. Petzold. Computer Methods for Ordinary Differential Equations and Differential-Algebraic Equations. Philadelphia: SIAM, 1998.

Otto, Samuel E., Charles J. Trefny, and John W. Slater. Inward-Turning Streamline-Traced Inlet Design Method for Low-Boom, Low-Drag Applications. Cleveland: NASA Glenn Research Center, 2015.

Slater, John W. Methodology for the Design of Streamline-Traced External-Compression Supersonic Inlets. American Institute of Aeronautics and Astronautics, 2014.

Mlder, S. and Szpiro, E.J. Busemann Inlet for Hypersonic Speeds. AIAA Journal of Spacecraft and Rockets, Vol. 3, No.8, pp. 1303-1304, 1966.

Mlder, S. Internal, Axisymmetric, Conical Flow. AIAA Journal, Vol. 5, No. 7, Jul. 1967, pp. 1252-1255.

Zhao, Zhi, Wenyang Song. Effect of Truncation on the Performance of Busemann Inlet. Canada: CCSE Modern Applied Science Journal, 2009.

O’Brien, Timothy F. and Jesse R. Colville. Analytical Computation of Leading Edge Truncation Effects on InviscidBusemann Inlet Performance. Reno: AIAA Aerospace Sciences Meeting and Exhibit, 2007.

Xiao, Yabin, LianjieYue, Peng Gong, and Xinyu Chang. Investigation on a Truncated Streamline-Traced Hypersonic Busemann Inlet. Dayton: AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2008.

Ramasubramanian, Vijay, and Mark Lewis. Performance of Various Truncation Strategies Employed on Hypersonic Busemann Inlets. AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, 2009.

You, Yancheng, Chengxiang Zhu, JunliangGuo. Dual Waverider Concept for the Integration of Hypersonic Inward-Turning Inlet and Airframe Forebody. AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, 2009.

Courant, Richard, Friedrichs, K.O. Supersonic Flow and Shock Waves. New York: Springer-Verlag, 1976.

Hutomo, Muhammad Adnan. DesainKonseptual Mixed-Compression Intake padaKecepatan High Supersonic. InstitutTeknologi Bandung, 2015.

Mattingly, Jack D. Aircraft Engine Design. Virginia: American Institute of Aeronautics and Astronautics, 2002.

Guide for the Verification and Validation of Computational Fluid Dynamics Simulations. Renton: American Institute of Aeronautics and Astronautics, 1998.

Slater, John W. Design and Analysis Tool for External-Compression Supersonic Inlets. Cleveland: American Institute of Aeronautics and Astronautics, 2012.

Bloch, Gregory S. An Assessment of Inlet Total-Pressure Distortion Requirements for the Compressor Research Facility. Ohio: Aero Propulsion and Power Directorate, 1992.

Farmer, Clinton J. Inlet Distortion, Vorticity, and Stall in an Axial-flow Compressor. Springfield: Naval Postgraduate School Thesis, 1972.




DOI: http://dx.doi.org/10.23960/ins.v2i2.90

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