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Aerodynamic Effects of a 24-Foot, Multisegmented Telescoping Nose Boom on an F-15B Airplane

Author
Smith, Mark S.
Published
August 20, 2007.
Physical Description
1 electronic document
Additional Creators
Frederick, Michael A. and Cumming, Stephen B.
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
An experimental multisegmented telescoping nose boom has been installed on an F-15B airplane to be tested in a flight environment. The experimental nose boom is representative of one that could be used to tailor the sonic boom signature of an airplane such as a supersonic business jet. The nose boom consists of multiple sections and could be extended during flight to a length of 24 ft. The preliminary analyses indicated that the addition of the experimental nose boom could adversely affect vehicle flight characteristics and air data systems. Before the boom was added, a series of flights was flown to update the aerodynamic model and characterize the air data systems of the baseline airplane. The baseline results have been used in conjunction with estimates of the nose boom s influence to prepare for a series of research flights conducted with the nose boom installed. Data from these flights indicate that the presence of the experimental boom reduced the static pitch and yaw stability of the airplane. The boom also adversely affected the static-position error of the airplane but did not significantly affect angle-of-attack or angle-of-sideslip measurements. The research flight series has been successfully completed.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 20070028417.
AIAA Paper-2007-6638.
AIAA Atmospheric Flight Mechanics Conference; 20 Aug. 2007; Hilton Head, SC; United States.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 16001610