碩士 / 國立成功大學 / 航空太空工程學系 / 84 / The objective of this work is to calibrate the transonic pilot
tunnel located in ASTRC. The calibration process
basically follows that of the large transonic tunnel built
by Fluidyne. Various operational parameters were studied
which include settling chamber stagnation pressure, wall
porosity, Mach flap angle, choke flap angle and the test section
wall divergence angle. How do these parameters affect
the flow quality were assessed by measuring the
centerline Mach number distributions as the control
mechanism associated with each parameter was activated. Aside
from these tunnel control parameters, the deviation of plenum
chamber Mach number to the centerline Mach number was
considered important also. All the Mach numbers obtained
were calculated using the measured static pressure and the
settling chamber stagnation pressure via an isentropic
relationship. The calibration results show that the wall effects
are significant for high-speed flow and the test
section flow speed can be accelerated when either Mach
flap or test section wall angle was enlarged. The twice
deviation in centerline Mach number was found to be around
0.004∼0.006 for low speed flow(M=0.3∼0.7) and 0.006∼ 0.011
for high speed flow(M=0.7∼1.1), respectively. Generally
speaking, a larger Mach number test section flow will
cause a larger deviation in the centerline Mach number
distribution.
| Identifer | oai:union.ndltd.org:TW/084NCKU0295036 |
| Date | January 1996 |
| Creators | Chyan, Yeu-Liang, 錢禹良 |
| Contributors | Lu Pong-Jeu, 陸鵬舉 |
| Source Sets | National Digital Library of Theses and Dissertations in Taiwan |
| Language | zh-TW |
| Detected Language | English |
| Type | 學位論文 ; thesis |
| Format | 90 |
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