Optimization and integration of naca submerge inlet for unmanned aerial vehicle operating in high subsonic regime. | [Proceedings 5th International Bhurban Conference on Applied Sciences and Technology • 2007]

Author(s):

1. F. Akram: Department of Aerospace Engineering, College of Aeronautical Engineering, National University of S & Technology, Risalpur, Pakistan

2. J. Masud: Department of Aerospace Engineering, College of Aeronautical Engineering, National University of S & Technology, Risalpur, Pakistan

3. A. Rehman: Department of Aerospace Engineering, College of Aeronautical Engineering, National University of S & Technology, Risalpur, Pakistan

4. A. Maqsood: Department of Aerospace Engineering, College of Aeronautical Engineering, National University of S & Technology, Risalpur, Pakistan

Abstract:

Two submerged inlets are designed with the aim to propose an optimal design for Unmanned Aerial Vehicle (UAV) operating in high subsonic regime. First design was based on theoretical one-dimensional isentropic flow characteristics and second design used the semi empirical data taken from different experiments results. The design objectives included mass flow rate of 6.5 kg/sec and acceptable distortion level less than 0.5 for the selected dimensions of UAV engine. Numerical simulations were performed to evaluate the characteristics of both inlets at Mach number 0.8 with various back pressures using commercial software, Fluent 6.2. The computed results indicated that inlet design based on theoretical one-dimensional isentropic flow characteristics performed satisfactory at higher back pressure but shock wave was observed at a desired mass flow rate of 6.5 kg/sec inside the duct at back pressure ranging from 98 kpa to 99 kpa. With the increase in back pressure, the shock wave vanished on the expense of reduction in mass flow rate and lesser pressure recovery. The formation of shock and corresponding low pressure recovery made this design unsuitable for current study. In case of design based `on the semi empirical data, the results predicted a stable behavior of inlet at all back pressures with desired mass flow rate and higher corresponding pressure recovery as compared to former design. This design gave pressure recovery of 93.35 percent and distortion coefficient of 0.06 at mass flow rate of 6.5 kg/sec. The average Mach number at engine face was 0.47 which was suitable for the selected engine operation. Finally, the computed results and numerical visualization study suggested that fluent 6.2 captured the sequence of flow events such as shock wave, region of local flow acceleration, side walls vortices and small regions of flow separation very well.

Page(s): 160-166

DOI: DOI not available

Published: Journal: Proceedings 5th International Bhurban Conference on Applied Sciences and Technology , Volume: 0, Issue: 0, Year: 2007

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