Lees, Lester
(1946)
*A Discussion of the Application of the Prandtl-Glauert Method to Subsonic Compressible Flow over a Slender Body of Revolution.*
National Advisory Committee for Aeronautics
, Washington, D. C..
http://resolver.caltech.edu/CaltechAUTHORS:LEEnacatn1127

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## Abstract

The Prandtl-Glauert method for subsonic potential flow of a compressible fluid has generally been believed to lead to an increase in the pressures over a slender body of revolution by a factor 1/([sqrt](1-M[sub]1^2)) (where M[sub]1 is Mach number in undisturbed flow) as compared with the pressures in incompressible flow. Recent German work on this problem has indicated, however, that the factor 1/([sqrt](1-M[sub]1^2)) is not applicable in this case. In the present discussion a more careful application of the Prandtl-Glauert method to three-dimensional flow gives the following results: The Prandtl-Glauert method does not lead to a universal velocity or pressure correction formula that is independent of the shape of the body. The factor 1/([sqrt](1-M[sub]1^2)) is applicable only to the case of two-dimensional flow. The increase with Mach number of the pressures over a slender body of revolution is much less rapid than for a two-dimensional airfoil. An approximate formula from which the increase can be estimated is derived theoretically. The increase with Mach number of the maximum axial interference velocity on a slender body of revolution in a closed wind tunnel is given approximately by the factor 1/((1-M[sub]1^2)^-3/2), rather than by the factor 1/([sqrt](1-M[sub]1^2)) previously obtained by Goldstein and Young and by Tsien and Lees.

Item Type: | Report or Paper (Technical Report) |
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Record Number: | CaltechAUTHORS:LEEnacatn1127 |

Persistent URL: | http://resolver.caltech.edu/CaltechAUTHORS:LEEnacatn1127 |

Alternative URL: | http://naca.larc.nasa.gov/reports/1946/naca-tn-1127/naca-tn-1127.pdf |

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ID Code: | 458 |

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Deposited On: | 21 Jun 2005 |

Last Modified: | 26 Dec 2012 08:40 |

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