초록 ▼

An aircraft (10), in particular a trainer aircraft with improved aerodynamic performance, having a configuration able to keep a directional stability and a very good aerodynamic behaviour even at very high angles of attack, where, traditional configurations prove themselves inefficient. In particula

An aircraft (10), in particular a trainer aircraft with improved aerodynamic performance, having a configuration able to keep a directional stability and a very good aerodynamic behaviour even at very high angles of attack, where, traditional configurations prove themselves inefficient. In particular, this configuration foresees a forebody (52) with variable section, optimised for high angle of attack flights, a LEX vortex control device (72) at least one diverterless air intake (46), and a wing profile (18, 20) optimised in order to reduce the buffet effects typical of low aspect ratio wings with thin profile and variable camber. The aircraft (10) presents, finally, staggered tails (44 and 38), to optimise the aerodynamic performance.

대표청구항 ▼

The invention claimed is: 1. Configuration of an aircraft (10) with improved aerodynamic performance, so as to maintain direction stability at mid/high angles of attack, said aircraft (10) having a fuselage (12) fitted with wings (18, 20) and leading edge extensions each leading edge extension ("LE

The invention claimed is: 1. Configuration of an aircraft (10) with improved aerodynamic performance, so as to maintain direction stability at mid/high angles of attack, said aircraft (10) having a fuselage (12) fitted with wings (18, 20) and leading edge extensions each leading edge extension ("LEX") having an area at least one air intake (46) and a fuselage forebody (52) with a tapering section, said aircraft (10) including a LEX vortex control device (72) shaped such as to make symmetrical the bursting of the vortex generated by a said LEX at mid/high angles of attack, wherein the ratio of the LEX area over the corresponding LEX vortex control device height is equal to 2.35m with a tolerance range varying from about 200% to about 50% of said ratio, said LEX vortex control device cooperating with staggered tails comprising a single vertical fin (38) and at least one horizontal stabilizer (44), obtained by coupling the vertical fin (38) to the wing (18, 20), wherein the leading edges (36) of the vertical fin (38) overlap the tailing edges (70) of each wing (18, 20), in order to maintain lateral-directional stability. 2. Configuration of an aircraft (10) as defined in claim 1, wherein the fuselage forebody (52) has a low aspect ratio. 3. Configuration of an aircraft (10) as defined in claim 1, wherein the staggered tails (44 and 38) are coupled by the vertical fin with trapezoidal platform to the wing (18, 20) and whose leading edges (36) overlap trailing edges (70) of each wing (18, 20). 4. Configuration of an aircraft (10) as defined in claim 3, wherein the horizontal stabilizer (44) comprises a trapezoidal platform and the capability of symmetrical and asymmetrical deflection, said horizontal tail having a hinge axis (86), along a lateral axis (88) of the aircraft (10), in order to optimize hinge and inertial moments. 5. Configuration of an aircraft (10) as defined in claim 3, wherein the air intake (46) has no diverter on the upper lip of the air intake. 6. Configuration of an aircraft (10) as defined in 1, wherein the air intake (46) has an inner lip average leading edge radius (76A) equal to 7 mm, while the lower lip average leading edge radius (78) is equal to 17.5 mm and that of the average outer lip (80) is equal to 14 mm, so that the capture area of the air intake (46) is about 0.322 m2, the throat area is about 0.257 m2 and the engine face area is about 0.273 m2. 7. Configuration of an aircraft (10) as defined in claim 1, wherein each wing (18, 20) of the aircraft (10) has a trapezoidal platform and at least one saw tooth area (S) in at least one part of the wing span, said wing (18, 20) also having a leading edge (68) and radius (R) with a triangular profile. 8. Configuration of an aircraft (10) as defined in claim 1, wherein each wing (18, 20) of the aircraft (10) shows a variable camber profile, both on the leading edge (66) and on the trailing edge (70), in order to optimize camber profile for improved compressibility effects. 9. Configuration of an aircraft as defined in claim 1, wherein the LEX control device is substantially vertically oriented. 10. Configuration of an aircraft as defined in claim 1 wherein a LEX control device is located at about the tip of each LEX, where said LEX meets an adjacent wing. 11. Configuration of an aircraft as defined in claim 1 wherein a LEX control device is substantially vertically oriented at about the tip of said LEX, where said LEX meets an adjacent wing. 12. Configuration of an aircraft as defined in claim 1 wherein the ratio of the LEX area over the corresponding LEX vortex control device height is equal to about 2.35m.