Bleviss, Zegmund O. (1951) Interference effects in supersonic flow. Dissertation (Ph.D.), California Institute of Technology. http://resolver.caltech.edu/CaltechETD:etd-03182009-105100
A study is made of interference problems with emphasis on low-aspect-ratio supersonic missile configurations. The configurations are composed of slender pointed bodies with circular cross section, plane or cruciform delta wings, and tails which are not specified. For fin-fin interference (no body) general multi-fin delta wings are studied for the roll problems.
Three types of interferences are studied. They are (1) fin-fin interference, (2) fin-fin and wing-body interferences combined, and (3) wing-body-tail interference. Where possible, three aerodynamic problems are studied under each of these interferences. They are (1) lift and incidence, (2) roll due to aileron deflection, and (3) damping in roll.
A survey of the theoretical work on supersonic interference problems is included.
Linearized theory is used throughout for all problems treated by the writer. Work by other writers which fits naturally into the scheme of the present work is summarized briefly. For most of the problems it is not possible to obtain exact linearized solutions without excessive labor. Where possible, approximations to or estimates of the exact solutions are obtained. It is hoped that these results will be useful for engineering estimates of the interference effects.
Theoretical results for the roll problems--exact, approximate, and estimated--are presented for fin-fin interference for cruciform and more general multi-fin delta wings with subsonic and supersonic leading edges.
For fin-fin and wing-body interferences combined, theoretical results which bracket the exact solutions are obtained for the roll problems.
For wing-body-tail interference, the vorticity distributions, rolled-up vortex strengths, and initial vortex positions at the trailing edges are estimated for lift, incidence, aileron deflection, and damping in roll problems. Both plane and cruciform delta wing body configurations are studied.
A qualitative discussion of some of the nonlinear, viscous, and gap effects is included.
Recommendations for future research are made.
|Item Type:||Thesis (Dissertation (Ph.D.))|
|Degree Grantor:||California Institute of Technology|
|Division:||Engineering and Applied Science|
|Thesis Availability:||Public (worldwide access)|
|Defense Date:||1 January 1951|
|Default Usage Policy:||No commercial reproduction, distribution, display or performance rights in this work are provided.|
|Deposited By:||Imported from ETD-db|
|Deposited On:||18 Mar 2009|
|Last Modified:||26 Dec 2012 02:34|
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