Supersonic flow past two oscillating airfoils
By: Georgios Alexandris
Publisher: Naval Postgraduate School; Available from National Technical Information Service
Published: 1998
Place of publication: Monterey, Calif; Springfield, Va
Language: eng
Number of pages: 73
Description: Supersonic flow past two oscillating airfoils is analyzed using an elementary analytical theory valid for low      frequencies of oscillation. The airfoils may have arbitrary stagger angle. This approach generalizes Sauer'      solution for a single airfoil oscillating at small frequencies in an unbounded supersonic flow. It is shown that      this generalization can provide an elementary theory for supersonic flow past two slowly oscillating airfoils.      This aerodynamic tool will facilitate the evaluation of pressure distributions and consequently the calculation of      moment coefficient. Torsional fluller boundaries are computed. The results for the pitch-damping coefficient      are the same when compared with previous analysis. For arbitrary frequencies a linearized method of      characteristics was outlined. The elementary theory that has been developed in the thesis can be used for      flutter evaluation of aircraft carrying external stores. The result of the thesis is the derivation of the      pitch-damping coefficient, which is necessary to predict the flutter conditions.
Notes: "June 1998."

Thesis advisor(s): Max F. Platzer, James H. Luscombe, S. Weber.

Thesis (M.S. in Applied Physics) Naval Postgraduate School, June 1998.

Includes bibliographical references (p. 71-72).

"Approved for public release, distribution unlimited"--Cover.

Also available online.

Mode of access: World Wide Web

System requirements: Adobe Acrobat reader.

Hellenic Air Force author.

dk/dk cc:9116 9/3/98.