Application of the NASA Kernel-Function Procedures to Generally Deforming Wings

Item

Title
Application of the NASA Kernel-Function Procedures to Generally Deforming Wings
Date
1962
Index Abstract
Coming Soon
Photo Quality
Not Needed
Report Number
ASD TDR 62-409
Creator
None Given
Corporate Author
Aerojet-General Corporation
Laboratory
Flight Dynamics Laboratory
Extent
44
Identifier
AD0289882
Access Rights
OTS
Distribution Classification
1
Contract
AF 33(616)-7420
DoD Project
1370
DoD Task
137003
DTIC Record Exists
No
Distribution Change Authority Correspondence
None
Abstract
A method is described for obtaining generalized aerodynamic forces by utilizing the NASA KernelFunction Procedures. An evaluation of the generalized aerodynamic forces and the consequent flutter conditions is made for the particular case of a uniform, cantilevered, 70 degree delta wing. The supersonic Kernel-Function Procedure was found to be inadequate for treating the elastic modes on this low-aspect-ratio wing; the subsonic procedure, however, appears to work satisfactorily. The theoretical flutter predictions are compared with the experimental results of NASA Report TM X-53 (AD-222 902). The Kernel-Function predictions for quasi-steady flow (k approaches O) appear to be superior to those for the complete unsteady case k = omega sub fc sub r/2V sub f. Based on this limited comparison, it appears that for this low-aspect-ratio wing the large transient effects predicted by linearized theory in the transonic regime may not actually exist.
Report Availability
Full text available
Date Issued
1962-10
Provenance
Lockheed Martin Missiles & Fire Control
Type
report
Format
1 online resource
Media
ASDTDR62-409.pdf

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