NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
The impact of materials technology and operational constraints on the economics of cruise speed selectionSix material concepts at Mach 2.0 and three material concepts at Mach 2.55 were proposed. The resulting evaluations, based on projected development, production, and operating costs, indicate that aircraft designs with advanced composites as the primary material ingredient have the lowest fare premiums at both Mach 2.0 and 2.55. Designs having advanced metallics as the primary material ingredient are not economical. Advanced titanium, employing advanced manufacturing methods such as SFF/DB, requires a fare premium of about 30 percent at both Mach 2.0 and 2.55. Advanced aluminum, usable only at the lower Mach number, requires a fare premium of 20 percent. Cruise speeds in the Mach 2.0-2.3 regime are preferred because of the better economics and because of the availability of two material concepts to reduce program risk - advanced composites and advanced aluminums. This cruise speed regime also avoids the increase in risk associated with the more complex inlets and airframe systems and higher temperature composite matrices required at the higher Mach numbers typified by Mach 2.55.
Document ID
19810009498
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Clauss, J. S., Jr.
(Lockheed-California Co. Burbank, CA, United States)
Bruckman, F. A.
(Lockheed-California Co. Burbank, CA, United States)
Horning, D. L.
(Lockheed-California Co. Burbank, CA, United States)
Johnston, R. H.
(Lockheed-California Co. Burbank, CA, United States)
Werner, J. V.
(Lockheed-California Co. Burbank, CA, United States)
Date Acquired
August 11, 2013
Publication Date
March 1, 1981
Publication Information
Publication: NASA. Langley Research Center Supersonic Cruise Res., 1979, Pt. 2
Subject Category
Air Transportation And Safety
Accession Number
81N18021
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Available Downloads

There are no available downloads for this record.
No Preview Available