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Parametric Flutter Analysis of the TCA Configuration and Recommendation for FFM Design and ScalingThe current HSR Aeroelasticity plan to design, build, and test a full span, free flying transonic flutter model in the TDT has many technical obstacles that must be overcome for a successful program. One technical obstacle is the determination of a suitable configuration and point in the sky to use in setting the scaling point for the ASE models program. Determining this configuration and point in the sky requires balancing several conflicting requirements, including model buildability, tunnel test safety, and the ability of the model to represent the flutter mechanisms of interest. As will be discussed in detail in subsequent sections, the current TCA design exhibits several flutter mechanisms of interest. It has been decided that the ASE models program will focus on the low frequency symmetric flutter mechanism, and will make no attempt to investigate high frequency flutter mechanisms. There are several reasons for this choice. First, it is believed that the high frequency flutter mechanisms are similar in nature to classical wing bending/torsion flutter, and therefore there is more confidence that this mechanism can be predicted using current techniques. The low frequency mode, on the other hand, is a highly coupled mechanism involving wing, body, tail, and engine motion which may be very difficult to predict. Second, the high frequency flutter modes result in very small weight penalties (several hundred pounds), while suppression of the low frequency mechanism inside the flight envelope causes thousands of pounds to be added to the structure. In order to successfully test the low frequency flutter mode of interest, a suitable starting configuration and point in the sky must be identified. The configuration and point in the sky must result in a wind tunnel model that (1) represents the low-frequency wing/body/engine/empennage flutter mechanisms that are unique to HSCT configurations, (2) flutters at an acceptably low frequency in the tunnel, (3) flutters at an acceptably low dynamic pressure in the tunnel, (4) allows sufficient weight for model buildability without inordinately high cost, and (5) has significant separation between the target flutter mechanism and other, potentially catastrophic, flutter mechanisms.
Document ID
20100033318
Acquisition Source
Langley Research Center
Document Type
Other
Authors
Baker, Myles
(Boeing Co. Seattle, WA, United States)
Lenkey, Peter
(Boeing Co. Seattle, WA, United States)
Date Acquired
August 25, 2013
Publication Date
November 21, 1997
Subject Category
Aircraft Stability And Control
Report/Patent Number
CRAD-9408-TR-3342
NF1676L-11123
NF1676L-13585
Report Number: CRAD-9408-TR-3342
Report Number: NF1676L-11123
Report Number: NF1676L-13585
Funding Number(s)
WBS: WBS 484754.02.07.20.02
CONTRACT_GRANT: ZA0226
WBS: WBS 561581.02.08.07.15.18
CONTRACT_GRANT: NAS1-20220
Distribution Limits
Public
Copyright
Public Use Permitted.
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