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P. Liu
leading edge and supersonic trailing edge. The pressure distribution and aerodynamic characteristics corresponding to these different flow conditions are
different. The establishment of the theory provides an important basis for
understanding the supersonic flow. At the same time, a wealth of information
has been accumulated based on a large number of wind tunnel tests, which
provides an important support for the development of supersonic aircraft.
The shock wave drag of a supersonic aircraft accounts for the majority of
the total drag. Therefore, the surface of the wing is made into a smooth, thin
and short swept or triangle shape, and the fuselage is made into a sharp tip
slender shape. The characteristics of supersonic flight are the aerodynamic
center moves backward, and the longitudinal static stability increases; the
drag of the aircraft decreases as the Mach number increases. Both of them
cause the disturbance attenuation to slow down, the maneuverability becomes
worse, and the yaw stability becomes worse. Therefore, it is necessary to
increase the vertical tail area or use an automatic device. When the Mach
number is less than 2.5, the strength of the aluminum alloy can maintain the
aerodynamic heating caused by high-speed flight. After the Mach number
reaches 3.0, the aerodynamic heating is intensified and heat-resistant materials are required. To prevent sonic booms and noise hazards, many countries
prohibit supersonic flight over residential areas.
The flight speed of a supersonic aircraft exceeds the speed of sound. On
October 14, 1947, the U.S. Air Force captain Charles Yeager drove the X1 at an altitude of 12,800 meters to a speed of 1,278 km/h, M = 1.1015,
which is the first time humans broke the sound barrier. The representative
of the civilian supersonic aircraft is the medium-range supersonic passenger
aircraft Concorde (as shown in Figs. 7.151 and 7.152) jointly developed by
French Aerospace and British Aircraft Corporation. The aircraft adopts a no
horizontal tail layout. In order to adapt to supersonic flight, the Concorde’s
wing adopts a delta wing, and the leading edge of the wing is S-shaped. The
Concorde has a total of four turbojet engines. The engines were developed
by Rolls-Royce and the SNECMA. The engine has an afterburner that is
typically used on supersonic fighters. The Concorde can fly at speed up to
twice the speed of sound, with a maximum flight speed of Mach 2.04, a
cruising altitude of 18,000 meters, and a cruising speed of 2,150 km per
hour. Serviced in 1976, it is mainly used to carry out transatlantic regular
routes from London Heathrow Airport (British Airways) and Paris Charles de
Gaulle International Airport (Air France) to and from the John F. Kennedy
International Airport in New York. The aircraft can cruise at a speed of 2.02
sound speed at an altitude of 15,000 meters. It takes only about 3 h and
20 min to fly from Paris to New York. It saves more than half of the time
P. Liu
leading edge and supersonic trailing edge. The pressure distribution and aerodynamic characteristics corresponding to these different flow conditions are
different. The establishment of the theory provides an important basis for
understanding the supersonic flow. At the same time, a wealth of information
has been accumulated based on a large number of wind tunnel tests, which
provides an important support for the development of supersonic aircraft.
The shock wave drag of a supersonic aircraft accounts for the majority of
the total drag. Therefore, the surface of the wing is made into a smooth, thin
and short swept or triangle shape, and the fuselage is made into a sharp tip
slender shape. The characteristics of supersonic flight are the aerodynamic
center moves backward, and the longitudinal static stability increases; the
drag of the aircraft decreases as the Mach number increases. Both of them
cause the disturbance attenuation to slow down, the maneuverability becomes
worse, and the yaw stability becomes worse. Therefore, it is necessary to
increase the vertical tail area or use an automatic device. When the Mach
number is less than 2.5, the strength of the aluminum alloy can maintain the
aerodynamic heating caused by high-speed flight. After the Mach number
reaches 3.0, the aerodynamic heating is intensified and heat-resistant materials are required. To prevent sonic booms and noise hazards, many countries
prohibit supersonic flight over residential areas.
The flight speed of a supersonic aircraft exceeds the speed of sound. On
October 14, 1947, the U.S. Air Force captain Charles Yeager drove the X1 at an altitude of 12,800 meters to a speed of 1,278 km/h, M = 1.1015,
which is the first time humans broke the sound barrier. The representative
of the civilian supersonic aircraft is the medium-range supersonic passenger
aircraft Concorde (as shown in Figs. 7.151 and 7.152) jointly developed by
French Aerospace and British Aircraft Corporation. The aircraft adopts a no
horizontal tail layout. In order to adapt to supersonic flight, the Concorde’s
wing adopts a delta wing, and the leading edge of the wing is S-shaped. The
Concorde has a total of four turbojet engines. The engines were developed
by Rolls-Royce and the SNECMA. The engine has an afterburner that is
typically used on supersonic fighters. The Concorde can fly at speed up to
twice the speed of sound, with a maximum flight speed of Mach 2.04, a
cruising altitude of 18,000 meters, and a cruising speed of 2,150 km per
hour. Serviced in 1976, it is mainly used to carry out transatlantic regular
routes from London Heathrow Airport (British Airways) and Paris Charles de
Gaulle International Airport (Air France) to and from the John F. Kennedy
International Airport in New York. The aircraft can cruise at a speed of 2.02
sound speed at an altitude of 15,000 meters. It takes only about 3 h and
20 min to fly from Paris to New York. It saves more than half of the time