Engineering:McDonnell Douglas DC-X-200
The McDonnell Douglas DC-X-200 was a proposed airliner from McDonnell Douglas in the late 70's.
It was to complement McDonnell Douglas DC-10, with a smaller capacity. It was basically a shortened DC-10 (keeping the same fuselage cross-section), with a capacity reduced from 270 to 220 passengers in a 3 class layout, and only two engines under the wings, dropping the DC-10's central engine. They were General Electric CF6s as in the DC-10, but in a slightly uprated version. It addition, the wing was a new design, with higher aspect ratio and supercritical airfoil. It was to compete with Airbus A310 and Boeing 767, developed in the same era and of similar size.
MDD was working with NASA on the aerodynamic design, and wind tunnel testing were conduced.[1] However the project was dropped in the summer of 1978 due to low commercial opportunities.[2]
The NASA report lists the main design features:[1]
- Length : 43.41 m
- Wingspan : 46.84 m
- height : 15.24 m
- Wing area : 220 m2
- MTOW : 132 tonnes
- engines : Two CF6-45 with 200 kN thrust each
References
- ↑ 1.0 1.1 Steckel; Dahlin; Henne (1980-10-01). "Results of design studies and wind tunnel tests of high-aspect-ratio supercritical wings for an energy efficient transport" (in en). NASA TRS.
- ↑ Gillett, Dave (1994-04-01). INDUSTRIAL COLL OF THE ARMED FORCES WASHINGTON DC. ed. "Strategy in the Commercial Aircraft Industry in the United States: A Comparison of Decisionmaking by McDonnell-Douglas and Boeing Aircraft Companies from 1977-1983." (in en). ADA. https://apps.dtic.mil/sti/citations/ADA288289.
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