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P. Liu
calculation can replace some experimental items, can significantly improve
the aerodynamic design speed of the aircraft, can provide necessary aerodynamic data more quickly and economically than the experiment, and make
the wind tunnel experiment more faced with the cutting-edge topics and
complex flow mechanism problems in aerodynamics. On the other hand, no
matter the development of science or the development of aircraft, numerical simulation can never replace wind tunnel experiment. This is because
various theories of aerodynamics are formed and developed on the basis
of a large number of experimental studies, and many major breakthroughs
are inseparable from experiments. Numerical calculation can only solve the
flow phenomenon that the flow mechanism has been clearly studied by
experiments, but for the flow problem with complex mechanism and the
verification of numerical calculation results, experiments are the inevitable
way. In addition, the performance of modern aircraft is more and more
advanced, and the aerodynamic problems are very complex. Therefore, the
flow field index and technical level of wind tunnel experiment are required
to be higher and higher, and the experimental items and hours are also
increasing. For example, in the 1950s, the wind tunnel test hours needed
to develop a large aircraft amounted to 10,000 h. The aerodynamic problems
involved were mainly adhesion flow and its reduction in drag. The development means were theoretical analysis and wind tunnel test. In the 1970s,
the number of wind tunnel experiments for the development of supersonic
airliner reached 40,000 h. The aerodynamic problems involved were mainly
shock wave, supersonic flow, and shock resistance reduction. The development means were theoretical analysis, numerical calculation, and wind tunnel
experiments. In the 1980s, the number of wind tunnel experiments for the
development of the space shuttle reached 100,000 h. The main aerodynamic
problems involved were low-speed supersonic flow, high angle of attack flow
around, and thermal barrier problems. The development means were theoretical analysis, numerical calculation, and wind tunnel experiments. This shows
that wind tunnel test is still an important guarantee for the development of
modern aerodynamics and aircraft development.
P. Liu
calculation can replace some experimental items, can significantly improve
the aerodynamic design speed of the aircraft, can provide necessary aerodynamic data more quickly and economically than the experiment, and make
the wind tunnel experiment more faced with the cutting-edge topics and
complex flow mechanism problems in aerodynamics. On the other hand, no
matter the development of science or the development of aircraft, numerical simulation can never replace wind tunnel experiment. This is because
various theories of aerodynamics are formed and developed on the basis
of a large number of experimental studies, and many major breakthroughs
are inseparable from experiments. Numerical calculation can only solve the
flow phenomenon that the flow mechanism has been clearly studied by
experiments, but for the flow problem with complex mechanism and the
verification of numerical calculation results, experiments are the inevitable
way. In addition, the performance of modern aircraft is more and more
advanced, and the aerodynamic problems are very complex. Therefore, the
flow field index and technical level of wind tunnel experiment are required
to be higher and higher, and the experimental items and hours are also
increasing. For example, in the 1950s, the wind tunnel test hours needed
to develop a large aircraft amounted to 10,000 h. The aerodynamic problems
involved were mainly adhesion flow and its reduction in drag. The development means were theoretical analysis and wind tunnel test. In the 1970s,
the number of wind tunnel experiments for the development of supersonic
airliner reached 40,000 h. The aerodynamic problems involved were mainly
shock wave, supersonic flow, and shock resistance reduction. The development means were theoretical analysis, numerical calculation, and wind tunnel
experiments. In the 1980s, the number of wind tunnel experiments for the
development of the space shuttle reached 100,000 h. The main aerodynamic
problems involved were low-speed supersonic flow, high angle of attack flow
around, and thermal barrier problems. The development means were theoretical analysis, numerical calculation, and wind tunnel experiments. This shows
that wind tunnel test is still an important guarantee for the development of
modern aerodynamics and aircraft development.