Actions for Implementation of uniform perturbation method for potential flow past axisymmetric and two-dimensional bodies

Email RIS file
Bookmark
Report an Issue

Implementation of uniform perturbation method for potential flow past axisymmetric and two-dimensional bodies

Author
Wong, T. C.
Published
Aug 1, 1984.
Physical Description
1 electronic document
Additional Creators
Tiwari, S. N.
Online Version

Availability

I Want It
I Want It

Finding items...

Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
The aerodynamic characteristics of potential flow past an axisymmetric slender body and a thin airfoil are calculated using a uniform perturbation analysis method. The method is based on the superposition of potentials of point singularities distributed inside the body. The strength distribution satisfies a linear integral equation by enforcing the flow tangency condition on the surface of the body. The complete uniform asymptotic expansion of its solution is obtained with respect to the slenderness ratio by modifying and adapting an existing technique. Results calculated by the perturbation analysis method are compared with the existing surface singularity panel method and some available analytical solutions for a number of cases under identical conditions. From these comparisons, it is found that the perturbation analysis method can provide quite accurate results for bodies with small slenderness ratio. The present method is much simpler and requires less memory and computation time than existing surface singularity panel methods of comparable accuracy.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19840021782.
Accession ID: 84N29851.
NASA-CR-173829.
NAS 1.26:173829.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15707272