Show simple item record

NACA-TR-1359

Thin airfoil theory based on approximate solution of the transonic flow equation

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T17:23:37Z
date available2017-09-04T17:23:37Z
date copyright01/01/1958
date issued1958
identifier otherZZONEEAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std/handle/yse/146830
description abstractA method is presented for the approximate solution of the nonlinear equations of transonic flow theory. Solutions are found for two-dimensional flows at a Mach number of 1 and for purely subsonic and purely supersonic flows. Results are obtained in closed analytic form for a large and significant class of nonlifting airfoils. At a Mach number of 1 general expressions are given for the pressure distribution on an airfoil of specified geometry and for the shape of an airfoil having a prescribed pressure distribution. Extensive comparisons are made with available data, particularly for a Mach number of 1, and with existing solutions.
languageEnglish
titleNACA-TR-1359num
titleThin airfoil theory based on approximate solution of the transonic flow equationen
typestandard
page37
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1958
contenttypefulltext
subject keywordsAPPROXIMATION
subject keywordsCOMPUTATIONAL FLUID DYNAMICS
subject keywordsEQUATIONS OF MOTION
subject keywordsFLOW THEORY
subject keywordsFREE FLOW
subject keywordsINTEGRAL EQUATIONS
subject keywordsMACH NUMBER
subject keywordsMULTIPHASE FLOW
subject keywordsNONLINEAR EQUATIONS
subject keywordsPRESSURE DISTRIBUTION
subject keywordsPRESSURE DRAG
subject keywordsSUBSONIC FLOW
subject keywordsSUPERSONIC FLOW
subject keywordsTHIN WINGS
subject keywordsTRANSONIC FLOW
subject keywordsTWO DIMENSIONAL FLOW
subject keywordsWING PROFILES


Files in this item

Thumbnail
Name:
ZZONEEAAAAAAAAAA.pdf
Size:
1.683Mb
Format:
PDF
View/Open

This item appears in the following Collection(s)

Show simple item record