Show simple item record

NASA-TM-X-2917

An investigation of several NACA 1 series axisymmetric inlets at Mach numbers from 0.4 to 1.29

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T16:08:36Z
date available2017-09-04T16:08:36Z
date copyright01/01/1974
date issued1974
identifier otherSENKAEAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/71812
description abstractAn investigation was conducted in the Langley 16-foot transonic tunnel to determine the performance of seven inlets having NACA 1-series contours and one inlet having an elliptical contour over a range of mass-flow ratios and at angle of attack. The inlet diameter ratio varied from 0.81 to 0.89; inlet length ratio varied from 0.75 to 1.25; and internal contraction ratio varied from 1.009 to 1.093. Reynolds number based on inlet maximum diameter varied from 3.4 million at a Mach number of 0.4 to 5.6 million at a Mach number of 1.29.
languageEnglish
titleNASA-TM-X-2917num
titleAn investigation of several NACA 1 series axisymmetric inlets at Mach numbers from 0.4 to 1.29en
typestandard
page143
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1974
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsAIR
subject keywordsCHARACTERISTICS
subject keywordsCONFIGURATIONS
subject keywordsENGINE
subject keywordsFLOW
subject keywordsGEOMETRY
subject keywordsINLETS
subject keywordsMEASUREMENT
subject keywordsPERFORMANCE
subject keywordsPRESSURE
subject keywordsSPEED
subject keywordsTESTS
subject keywordsTRANSONIC
subject keywordsTUNNEL
subject keywordsWIND


Files in this item

Thumbnail
Name:
SENKAEAAAAAAAAAA.pdf
Size:
5.150Mb
Format:
PDF
View/Open

This item appears in the following Collection(s)

Show simple item record