Marble, Frank E. (1993) Response of a Thin Airfoil Encountering a Strong Density Discontinuity. Journal of Fluids Engineering, 115 (4). pp. 580-589. ISSN 0098-2202 http://resolver.caltech.edu/CaltechAUTHORS:20101122-104523778
- Published Version
See Usage Policy.
Use this Persistent URL to link to this item: http://resolver.caltech.edu/CaltechAUTHORS:20101122-104523778
Airfoil theory for unsteady motion has been developed extensively, assuming the undisturbed medium to be of uniform density, a restriction accurate for motion in the atmosphere [1,2,3,4,5,6]. In some instances, notably for airfoils comprising fan, compressor and turbine blade rows, the undisturbed medium may carry density variations or "spots," resulting from non-uniformities in temperature or composition, of a size comparable to the blade chord. This condition exists for turbine blades [7,8] immediately downstream of the main burner of a gas turbine engine where the density fluctuations of the order of 50% may occur. Disturbances of a somewhat smaller magnitude arise from the ingestion of hot boundary layers into fans  and exhaust into hovercraft. Because these regions of non-uniform density convect with the moving medium, the airfoil experiences a time varying load and moment which we propose to calculate.
|Additional Information:||©1993 The American Society of Mechanical Engineers. Received June 29, 193; revised September 23, 1993.|
|Group:||Guggenheim Jet Propulsion Center|
|Other Numbering System:|
|Official Citation:||Response of a Thin Airfoil Encountering a Strong Density Discontinuity F. E. Marble pp. 580-589|
|Usage Policy:||No commercial reproduction, distribution, display or performance rights in this work are provided.|
|Deposited By:||Ruth Sustaita|
|Deposited On:||30 Nov 2010 21:46|
|Last Modified:||26 Dec 2012 12:40|
Repository Staff Only: item control page