6 Wind and Water Tunnel Equipment
385
addition, there were 2.5-m diameter low-speed wind tunnel (DFD-03) built
in AVIC Aerospace Life-support Industries, LTD.; the 0.6-m diameter transonic supersonic wind tunnel (CG-01) in Xi’an Institute of Modern Control
Technology; and the low-speed wind tunnel with tandem test section NH-2
(3.0 m × 2.5 m, 5.1 m × 4.25 m) in Nanjing University of Aeronautics and
Astronautics.
With the development of aviation and space flight vehicle in China, the
wind tunnel test demands stronger simulating ability (Re, Ma, etc.) and a
wider range of experimental ability (two-dimensional airfoil test, propeller
performance test, etc.). Therefore, the low-speed wind tunnel NF-3 built in
Northwestern Polytechnical University in the 1990s has three test sections
including the 2D (3 m × 1.6 m), 3D (3.5 m × 3.5 m), and propeller (2.2 m
× 2.2 m). The FL-2 transonic supersonic wind tunnel built by CAAA is
with the test section size of 1.2 m × 1.2 m, which can be pressurized to 0.8
mpa. The designed maximum testing Reynolds number is 1.6 × 10 7 . The
FL-26 transonic wind tunnel completed by CARDC in 1999 is with the test
section size of 2.4 m × 2.4 m, which can be pressurized to 0.45 mpa, and
the maximum testing Re is 1.2 × 10 7 .
At the beginning of the twenty-first century, AVIC Aerodynamics Research
Institute built a low-speed supercharged wind tunnel (FL-9) with a section
size of 4.5 m × 3.5 m, a trans- and supersonic wind tunnel with a section
size of 1.6 m × 1.5 m (FL-3), and a sub-hypersonic wind tunnel with
a section size of 1.2 m × 1.2 m (FL-60). FL-9 low-speed supercharged
wind tunnel can be supercharged to 0.4 mpa, the highest testing Reynold
number can be reached to 8.6 × 10 6 , with belly brace, tail brace, half
mode, and other supporting forms, which can meet the requirements of
aircraft development for low-speed and high-Re testing conditions. FL3 trans- and supersonic wind tunnel is a dual-purpose three-sound-speed
wind tunnel with a test section Ma = 0.3−1.35 (2.25), which can be
used for the measurement of force, pressure, an inlet with a large angle
of attack, and other test technologies. The CAAA has built a trans- and
supersonic wind tunnel (FD-12) with a section size of 1.2 m × 1.2 m,
which can be pressurized to 0.8 mpa. The designed maximum testing Re
is 1.6 × 10 7 . The CARDC has built a 2 m × 2 m supersonic wind
tunnel, which is a blow-down, impulse, and inject-type supersonic wind
tunnel with a fully flexible nozzle. The range of the Mach number is
1.5−4.25, and the test Reynolds number range is 7.72 × 10 6 ~74.16 × 10 6
(characteristic length is 1 m). The CARDC and Xi’an Institute of Modern
Control Technology have built vertical wind tunnels with diameters of 5 m
and 4.5 m, respectively, which are capable of studying and testing aircraft at
385
addition, there were 2.5-m diameter low-speed wind tunnel (DFD-03) built
in AVIC Aerospace Life-support Industries, LTD.; the 0.6-m diameter transonic supersonic wind tunnel (CG-01) in Xi’an Institute of Modern Control
Technology; and the low-speed wind tunnel with tandem test section NH-2
(3.0 m × 2.5 m, 5.1 m × 4.25 m) in Nanjing University of Aeronautics and
Astronautics.
With the development of aviation and space flight vehicle in China, the
wind tunnel test demands stronger simulating ability (Re, Ma, etc.) and a
wider range of experimental ability (two-dimensional airfoil test, propeller
performance test, etc.). Therefore, the low-speed wind tunnel NF-3 built in
Northwestern Polytechnical University in the 1990s has three test sections
including the 2D (3 m × 1.6 m), 3D (3.5 m × 3.5 m), and propeller (2.2 m
× 2.2 m). The FL-2 transonic supersonic wind tunnel built by CAAA is
with the test section size of 1.2 m × 1.2 m, which can be pressurized to 0.8
mpa. The designed maximum testing Reynolds number is 1.6 × 10 7 . The
FL-26 transonic wind tunnel completed by CARDC in 1999 is with the test
section size of 2.4 m × 2.4 m, which can be pressurized to 0.45 mpa, and
the maximum testing Re is 1.2 × 10 7 .
At the beginning of the twenty-first century, AVIC Aerodynamics Research
Institute built a low-speed supercharged wind tunnel (FL-9) with a section
size of 4.5 m × 3.5 m, a trans- and supersonic wind tunnel with a section
size of 1.6 m × 1.5 m (FL-3), and a sub-hypersonic wind tunnel with
a section size of 1.2 m × 1.2 m (FL-60). FL-9 low-speed supercharged
wind tunnel can be supercharged to 0.4 mpa, the highest testing Reynold
number can be reached to 8.6 × 10 6 , with belly brace, tail brace, half
mode, and other supporting forms, which can meet the requirements of
aircraft development for low-speed and high-Re testing conditions. FL3 trans- and supersonic wind tunnel is a dual-purpose three-sound-speed
wind tunnel with a test section Ma = 0.3−1.35 (2.25), which can be
used for the measurement of force, pressure, an inlet with a large angle
of attack, and other test technologies. The CAAA has built a trans- and
supersonic wind tunnel (FD-12) with a section size of 1.2 m × 1.2 m,
which can be pressurized to 0.8 mpa. The designed maximum testing Re
is 1.6 × 10 7 . The CARDC has built a 2 m × 2 m supersonic wind
tunnel, which is a blow-down, impulse, and inject-type supersonic wind
tunnel with a fully flexible nozzle. The range of the Mach number is
1.5−4.25, and the test Reynolds number range is 7.72 × 10 6 ~74.16 × 10 6
(characteristic length is 1 m). The CARDC and Xi’an Institute of Modern
Control Technology have built vertical wind tunnels with diameters of 5 m
and 4.5 m, respectively, which are capable of studying and testing aircraft at