GB2188301A - Aeroplane wing - Google Patents

Abstract

An aeroplane wing which has upper and lower elongate wing elements corresponding to a Busemann biplane and forming an elongate entrance along the leading edge of the wing and a corresponding elongate exit along the trailing edge, together with a passage between the entrance and exit of a cross-section wholly to contain any wave motion set up therein, and end plates located at the extreme ends of the two wing elements to support the wing elements above one another in spaced relationship and laterally to contain any air disturbances caused by passage of the wing elements through the air.

Description

**WARNING** start of DESC field may overlap end of CLMS **.

SPECIFICATION Aeroplane wing

Description Field of the invention This invention relatesto aeroplanewingsand in particularto an improved design of aeroplane wing which should enable air speed in excess of the speed of sound to be achieved without the accompanying supersonic boom.

Background to the invention The flight of an aircraft at supersonic speeds creates a characteristic and unpleasant boom which is experienced by a listening observer. The boom is caused by the breakdown of the airflow over the wing as the aircraft moves at supersonic speeds and it is an object of the present invention to provide a design of wing which underthe correct conditions will elliminatethe so-called sonic boom.

Summary of the invention According to the present invention an aeroplane wing adapted to travel at speeds in excess ofthe speed of sound without creating a sonic boom comprises: upper and lower elongate wing elements defining a so-called Busseman biplane and describing an elongate entrance along the leading edge ofthe wing and a corresponding elongate exit along the trailing edge thereof, the entrance and exit being joined by a passage the cross-section of which reduces to the rear of the entrance and enlarges towards the exit in manner known per se, which passage has the characteristic that any wave motion set up in the passage is wholly contained therewithin, and end plates located at the extreme ends of the two wing elements supporting the elements one above the other in spaced relation, the plates being sufficientlythin as not to cause any significant air disturbance as the wing assembly passes through the air and serving to laterallycontain any air disturbance caused by the formation of waves by the passage of the wing elements through the air.

Byformingtheupperand lowersurfacesofthe wing assembly so that airflow thereover is smooth and no waves are created, the wing assembly will travei through the airwiththe minimum of externally detectable disturbance and therefore with little or no sonic boom at supersonic speeds.

The construction envisaged has little or no aerodynamic lift but this can be provided by for example appropriate modification of the external surface shape of the wing assembly.

It is envisaged that the wing design described can to advantage form the fuselage of an aircraft ie a flying wing assembly, as well as forking a wing assemblyforafuselage.

CLAIMS 1. An aeroplane wing adapted to travel at speeds in excess of the speed of sound without creating a sonic boom comprising upper and lower elongate wing elements defining a so-called Busseman biplane and describing an elongate entrance along the leading edge of the wing and a corresponding elongate exit along the trailing edge thereof, the entrance and exit being joined by a passage the cross-section of which reduces to the rear ofthe entrance and enlargestowardsthe exit in manner known per se, which passage has the characteristic that any wave motion set up in the passage is holly contained therewithin, and end plates located at the extreme ends ofthetwo wing elements supporting the elements one above theother in spaced relation,the plates being sufficiently thin as not to cause any significant air disturbance as the wing assembly passes through the airand serving to laterallycontain anyair disturbance caused by the formation of waves by the passage of the wing elements through the air.

2. An aeroplane wing according to claim 1, wherein aerodynamic lift is provided by contouring the external surface of the wing assembly.

3. An aeroplane wing according to claim 1 or claim 2,which forms the fuselage of an aircraft in a flying wing assembly.

4. An aeroplanewing according to claim 1 or claim 2, in which the said wing forms part of a wing assembly attached to a fuselage.

5. An aeroplane wing substantially as hereinbefore described.

Claims (5)

SPECIFICATION Aeroplane wing Description Field of the invention This invention relatesto aeroplanewingsand in particularto an improved design of aeroplane wing which should enable air speed in excess of the speed of sound to be achieved without the accompanying supersonic boom. Background to the invention The flight of an aircraft at supersonic speeds creates a characteristic and unpleasant boom which is experienced by a listening observer. The boom is caused by the breakdown of the airflow over the wing as the aircraft moves at supersonic speeds and it is an object of the present invention to provide a design of wing which underthe correct conditions will elliminatethe so-called sonic boom. Summary of the invention According to the present invention an aeroplane wing adapted to travel at speeds in excess ofthe speed of sound without creating a sonic boom comprises: upper and lower elongate wing elements defining a so-called Busseman biplane and describing an elongate entrance along the leading edge ofthe wing and a corresponding elongate exit along the trailing edge thereof, the entrance and exit being joined by a passage the cross-section of which reduces to the rear of the entrance and enlarges towards the exit in manner known per se, which passage has the characteristic that any wave motion set up in the passage is wholly contained therewithin, and end plates located at the extreme ends of the two wing elements supporting the elements one above the other in spaced relation, the plates being sufficientlythin as not to cause any significant air disturbance as the wing assembly passes through the air and serving to laterallycontain any air disturbance caused by the formation of waves by the passage of the wing elements through the air. Byformingtheupperand lowersurfacesofthe wing assembly so that airflow thereover is smooth and no waves are created, the wing assembly will travei through the airwiththe minimum of externally detectable disturbance and therefore with little or no sonic boom at supersonic speeds. The construction envisaged has little or no aerodynamic lift but this can be provided by for example appropriate modification of the external surface shape of the wing assembly. It is envisaged that the wing design described can to advantage form the fuselage of an aircraft ie a flying wing assembly, as well as forking a wing assemblyforafuselage. CLAIMS

1. An aeroplane wing adapted to travel at speeds in excess of the speed of sound without creating a sonic boom comprising upper and lower elongate wing elements defining a so-called Busseman biplane and describing an elongate entrance along the leading edge of the wing and a corresponding elongate exit along the trailing edge thereof, the entrance and exit being joined by a passage the cross-section of which reduces to the rear ofthe entrance and enlargestowardsthe exit in manner known per se, which passage has the characteristic that any wave motion set up in the passage is holly contained therewithin, and end plates located at the extreme ends ofthetwo wing elements supporting the elements one above theother in spaced relation,the plates being sufficiently thin as not to cause any significant air disturbance as the wing assembly passes through the airand serving to laterallycontain anyair disturbance caused by the formation of waves by the passage of the wing elements through the air.

2. An aeroplane wing according to claim 1, wherein aerodynamic lift is provided by contouring the external surface of the wing assembly.

3. An aeroplane wing according to claim 1 or claim 2,which forms the fuselage of an aircraft in a flying wing assembly.

4. An aeroplanewing according to claim 1 or claim 2, in which the said wing forms part of a wing assembly attached to a fuselage.

5. An aeroplane wing substantially as hereinbefore described.

**WARNING** end of CLMS field may overlap start of DESC **.