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An Evaluation Technique for an F/A-18 Aircraft Loads Model Using F/A-18 Systems Research Aircraft Flight DataA limited evaluation of the F/A-18 baseline loads model was performed on the Systems Research Aircraft at NASA Dryden Flight Research Center (Edwards, California). Boeing developed the F/A-18 loads model using a linear aeroelastic analysis in conjunction with a flight simulator to determine loads at discrete locations on the aircraft. This experiment was designed so that analysis of doublets could be used to establish aircraft aerodynamic and loads response at 20 flight conditions. Instrumentation on the right outboard leading edge flap, left aileron, and left stabilator measured the hinge moment so that comparisons could be made between in-flight-measured hinge moments and loads model-predicted values at these locations. Comparisons showed that the difference between the loads model-predicted and in-flight-measured hinge moments was up to 130 percent of the flight limit load. A stepwise regression technique was used to determine new loads derivatives. These derivatives were placed in the loads model, which reduced the error to within 10 percent of the flight limit load. This paper discusses the flight test methodology, a process for determining loads coefficients, and the direct comparisons of predicted and measured hinge moments and loads coefficients.
Document ID
20000079998
Acquisition Source
Armstrong Flight Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Olney, Candida D. (NASA Dryden Flight Research Center Edwards, CA United States)
Hillebrandt, Heather (NASA Dryden Flight Research Center Edwards, CA United States)
Reichenbach, Eric Y. (Boeing Co. Saint Louis, MO United States)
Date Acquired
September 7, 2013
Publication Date
July 1, 2000
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NAS 1.15:209028
H-2423
NASA/TM-2000-209028
Meeting Information
Meeting: 31st SFTE Annual Symposium 2000
Location: Torino
Country: Italy
Start Date: September 18, 2000
End Date: September 22, 2000
Funding Number(s)
PROJECT: RTOP 529-61-14
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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