tailieunhanh - Aircraft Design Projects Episode 8

Tham khảo tài liệu 'aircraft design projects episode 8', kỹ thuật - công nghệ, cơ khí - chế tạo máy phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | Project study a dual-mode road air vehicle 191 Table Component weight mass estimates Component Weight lb Mass kg Structure Wing 215 Horizontal tail 30 Vertical tail 50 Fuselage 350 Main gear rear wheels 85 Nose gear front wheels 85 Subtotal 815 Propulsion Engine 400 Transmission 305 Propeller 50 Fuel system 45 Subtotal 800 Systems Controls 20 Electrical 190 Avionics 100 Anti-icing system 80 Subtotal 390 Cabin furnishings 115 Variable weights masses Fuel 480 Front passengers 320 Rear passengers 320 Luggage 60 Subtotal 1180 Total 3300 1500 characteristics a wing aspect ratio of a calculated Oswald efficiency factor of an aircraft parasitic drag coefficient CD0 a propeller efficiency np of 88 percent giving a constant thrust of 1012lb 4500N a specific fuel consumption of lb hp-hr kg kW-hr and a maximum gross weight mass of 3308 lb 1500 kg . The power plot Figure shows a cruise speed at 80 percent power at 9843 ft 3000 m altitude of kt 81 m s and a maximum speed at this altitude of 179 kt 92m s . Using take-off at stall speed from a hard surface gave a take-off ground roll of 689ft 210m and a 50ft obstacle clearance take-off distance of 920ft 280 m . With touchdown at stall speed which can be achieved with less than 10 flap deflection and braking at 80 percent of touchdown speed the landing ground roll was calculated at 755 ft 230 m . This gave a total distance of 1148 ft 350 m after clearing a 50 ft obstacle at an approach sink rate of 787 ft min 4m s . With 30 flap deflection this distance is reduced to 1066 ft 325 m . 192 Aircraft Design Projects Fig. Aircraft center of gravity excursion diagram Fig. Performance envelope at 3000 meters The aircraft maximum rate of climb at sea level was found to be 1460 ft min 445 m min and 755 ft min 230m min at the cruise altitude of 9842