| 摘要 |
The invention relates essentially to long-haul business aircraft, designed to be used for business trips by heads of state, municipal bodies, large companies, business people and so on, as well as for the urgent delivery of light cargo, with the intent to save substantial amounts of time, in all circumstances, compared with other forms of transport. The essence of the invention consists in a supersonic business aircraft whose aerodynamic design results in a lighter aircraft structure, and the attainment of high performance levels during cruising; the aircraft can also employ the same aerodromes used by subsonic craft. The fuselage is integrated with the wing system, and the middle frame section is substantially round. The engines are disposed in a single engine nacelle, which is integrated with the tail section of the fuselage; the fuselage does not extend beyond the engine nozzle. The vents are located under the wing section, and their forward edges disposed at a distance of 0.6...0.8 of the length of the fuselage commencing from its nose. The lower surface of the nacelle is more or less equidistant from the lower surface of the wing, and the transverse surfaces are disposed parallel to the aircraft's plane of symmetry. Each half-wing comprises three portions; the relative spans of the root and intervening wing portions are fractions of half the wing span, and have values of 0.2...0.35 respectively at the points of fracture. The sweep angles at the forward edge, commencing with the leading edge of the wing, are 70 DEG -82 DEG for the root portion, 55 DEG -65 DEG for the intervening portion, and 35 DEG -55 DEG for the end portion. The sweep of the rear edge of the end and root portions is nearly nil, and the value of the root wing span is 0.8...1.0 of the length of the fuselage. The flying time of the aircraft over a distance of 6000 km does not exceed 4 hours, and operating costs are comparable to those of subsonic craft. The aircraft can take off and land from the same aerodromes as subsonic models. |
