| タイトル | The airplane: A simulated commercial air transportation study |
| 本文（外部サイト） | http://hdl.handle.net/2060/19940020364 |
| 著者（英） | Dauteuil, Mark; Hunniford, Michael; Tognarelli, Michael; Lawler, Kathleen; Geniesse, Pete; Quirk, Elena |
| 著者所属（英） | Notre Dame Univ. |
| 発行日 | 1993-04-01 |
| 言語 | eng |
| 内容記述 | The 'Airplane' is a moderate-range, 70 passenger aircraft. It is designed to serve demands for flights up to 10,000 feet and it cruises at 32 ft/s. The major drivers for the design of the Airplane are economic competitiveness, takeoff performance, and weight minimization. The Airplane is propelled by a single Astro 15 electric motor and a Zinger 12-8 propeller. The wing section is a Spica airfoil which, because of its flat bottom, provides simplicity in manufacturing and thus helps to cut costs. The wing is constructed of a single load bearing mainspar and shape-holding ribs coated with Monokote skin, lending to a light weight structural makeup. The fuselage houses the motor, flight deck and passenger compartments as well as the fuel and control actuating systems. The wing will be attached to the top of the fuselage as will the fuel and control actuator systems for easy disassembly and maintenance. The aircraft is maneuvered about its pitch axis by means of an aft elevator on the flat plate horizontal tail. The twin vertical tail surfaces are also flat plates and each features a rudder for both directional and roll control. Along with wing dihedral, the rudders will be used to roll the aircraft. The Airplane is less costly to operate at its own maximum range and capacity as well as at its maximum range and the HB-40's maximum capacity than the HB-40. |
| NASA分類 | AIRCRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 94N24837
NASA-CR-195525
NAS 1.26:195525 |
| 権利 | No Copyright |
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