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Supersonic Experiments on Dynamic Cross-Derivatives Due to Pitching and Yawing of Aircraft-Like Vehicles

Author
Orlik-Ruckemann, K. J.
Published
Aug 1, 1973.
Physical Description
1 electronic document
Additional Creators
Hanff, E. S. and Laberge, J. G.
Online Version

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
A wind tunnel apparatus has been developed and constructed for the determination of moment cross-derivatives due to pitching and yawing on models at moderate angles of attack and sideslip. The apparatus can also be used to determine the direct moment derivatives in pitch and yaw. Experimental results were obtained at Mach 2 on a cone-wing-fin configuration at angles of attack and sideslip up to 15. Although at small values of these angles the cross-derivatives were always negligibly small, measureable effects were sometimes observed, at all angles of attack included in this investigation (i.e. up to 15 deg), when the angle of sideslip was 10 deg or 15 deg.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19730022212.
Accession ID: 73N30944.
LTR-UA-24.
NASA-CR-114663.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15747867