1001. Weight Estimates for Quiet/STOL Aircraft


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R W Patterson: 1001. Weight Estimates for Quiet/STOL Aircraft. 1974.



Recognizing that Q/STOL presents many new considerations for the Weight engineer in preparing Advanced Design weight estimates, this paper is offered to highlight some of the unique features and weight estimates derived from several NASA study contracts. For each study, the configuration and estimated weight data are presented and, in each case, the primary weight estimation basis has been derived from weight analyses of various design points. The reader should recognize that Q/STOL weight estimation relationships are mainly dependent upon:
o Design acoustic level
o Engine selection
o High-lift concept
o Design criteria (e.g., field lengths, range, speed, payload, etc.)
o Aircraft geometry
o Design constraints for vehicle cost (e.g., utilization of existing hardware), fuel prices, etc.
This paper, therefore, does not present ‘all-inclusive’ weight estimating relationships; however, it does present weight estimate summaries with their associated configuration and design particulars. Also presented are typical weight estimating relationships which are presently being used for NASA study contract NAS 2-6995. These data presentations are intended to aid the reader in evaluating future Q/STOL weight estimates.
Future Q/STOL applications, of course, are influenced by the recent emphasis on energy conservation; however, low noise levels must remain as a major consideration. Future aircraft development with low noise levels will involve the effects of fuel price levels on aircraft economics and the effects of advanced technology (e.g., active control devices, advanced aerodynamics, and advanced structures). Examples of future applications I or the QJSTOL concepts are visualized as follows:
o Fuel conservative configurations which utilize STOL high-life concepts to obtain relatively higher wing loadings during cruise.
o Configuration derivation of low-wing loading aircraft with short-range, low-passenger capacity, and low fan-pressure-ratio turbo-fan engines (possibly turbo-prop engines) which would fill a future inter-urban air transportation market.
For these future applications, the Weight Engineer in Advanced Design will need the tools and information for assessing the effects of such configuration advances.


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