430
P. Liu
Fig. 6.58 ETW axial compressor tail housing
of 110 K, the total temperature of the test section is 110−313 K,
and the total pressure of the test section is 115−450 kPa. The power
system, located downstream of the second corner section of the wind
tunnel, consists of a 50 MW variable frequency ac motor and an
axial flow compressor outside the tunnel. The compressor diameter is
4.5 m. Compressor speed ranges from 60 to 830 rpm. The maximum
speed is 830 rpm at room temperature. During the operation of the
wind tunnel, the strategy of flow adjustment is adjusting the speed
for coarse, fan front guide plate for fine adjustment. The Ma number
adjustment accuracy of the test section is 1/1000.
(3) 2.4 m × 2.4 m transonic wind tunnel
This wind tunnel is a large sub- and transonic wind tunnel in
Mianyang Aerodynamics Research and Development Center, which
was put into operation in 1999. The section size of the test section is
2.4 m (width) × 2.4 m (height) × 7 m (length), the Mach number
ranges from 0.3 to 1.15, and the maximum Reynolds number is 17 ×
10 6 . It can not only carry out the conventional force and pressure tests
for full model, half model, and components but also special tests such
as buffeting, flutter, dynamic derivative, and TPS can be completed
in this wind tunnel, as shown in Figs. 6.59 and 6.60. Currently, it
is mainly responsible for high-speed wind tunnel testing of the C919
jumbo jet, the ARJ21-700 regional jet, and the MA-700 regional jet.
P. Liu
Fig. 6.58 ETW axial compressor tail housing
of 110 K, the total temperature of the test section is 110−313 K,
and the total pressure of the test section is 115−450 kPa. The power
system, located downstream of the second corner section of the wind
tunnel, consists of a 50 MW variable frequency ac motor and an
axial flow compressor outside the tunnel. The compressor diameter is
4.5 m. Compressor speed ranges from 60 to 830 rpm. The maximum
speed is 830 rpm at room temperature. During the operation of the
wind tunnel, the strategy of flow adjustment is adjusting the speed
for coarse, fan front guide plate for fine adjustment. The Ma number
adjustment accuracy of the test section is 1/1000.
(3) 2.4 m × 2.4 m transonic wind tunnel
This wind tunnel is a large sub- and transonic wind tunnel in
Mianyang Aerodynamics Research and Development Center, which
was put into operation in 1999. The section size of the test section is
2.4 m (width) × 2.4 m (height) × 7 m (length), the Mach number
ranges from 0.3 to 1.15, and the maximum Reynolds number is 17 ×
10 6 . It can not only carry out the conventional force and pressure tests
for full model, half model, and components but also special tests such
as buffeting, flutter, dynamic derivative, and TPS can be completed
in this wind tunnel, as shown in Figs. 6.59 and 6.60. Currently, it
is mainly responsible for high-speed wind tunnel testing of the C919
jumbo jet, the ARJ21-700 regional jet, and the MA-700 regional jet.