• 0
    • ارسال درخواست
    • حذف همه
    • Industrial Standards
    • Defence Standards
  • درباره ما
  • درخواست موردی
  • فهرست استانداردها
    • Industrial Standards
    • Defence Standards
  • راهنما
  • Login
  • لیست خرید شما 0
    • ارسال درخواست
    • حذف همه
View Item 
  •   YSE
  • Defence Standards
  • NASA - National Aeronautics and Space Administration (NASA)
  • View Item
  •   YSE
  • Defence Standards
  • NASA - National Aeronautics and Space Administration (NASA)
  • View Item
  • All Fields
  • Title(or Doc Num)
  • Organization
  • Year
  • Subject
Advanced Search
JavaScript is disabled for your browser. Some features of this site may not work without it.

Archive

NASA-CR-3081

Wind tunnel force and pressure tests of a 21% thick general aviation airfoil with 20% aileron, 25% slotted flap and 10% slot-lip spoile

Organization:
NASA - National Aeronautics and Space Administration (NASA)
Year: 1979

Abstract: Force and surface pressure distributions were measured for the 21% LS(1)-0421 modified airfoil fitted with 20% aileron, 25% slotted flap and 10% slot lip spoiler. All tests were conducted at a Reynolds number of 2.2 x 10 to the 6th power and a Mach number of 0.13. The lift, drag, pitching moments, control surface normal force and hinge moments, and surface pressure distributions are included in the results. Incremental performance of flap and aileron are discussed and compared to the GA(W)-2 airfoil. Spoiler control which shows a slight reversal tendency at high alpha, is examined.
URI: https://yse.yabesh.ir/std/handle/yse/829
Subject: AILERONS
Collections :
  • NASA - National Aeronautics and Space Administration (NASA)
  • Download PDF : (5.419Mb)
  • Show Full MetaData Hide Full MetaData
  • Statistics

    NASA-CR-3081

Show full item record

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T15:03:37Z
date available2017-09-04T15:03:37Z
date copyright01/01/1979
date issued1979
identifier otherKWMKAEAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/829
description abstractForce and surface pressure distributions were measured for the 21% LS(1)-0421 modified airfoil fitted with 20% aileron, 25% slotted flap and 10% slot lip spoiler. All tests were conducted at a Reynolds number of 2.2 x 10 to the 6th power and a Mach number of 0.13. The lift, drag, pitching moments, control surface normal force and hinge moments, and surface pressure distributions are included in the results. Incremental performance of flap and aileron are discussed and compared to the GA(W)-2 airfoil. Spoiler control which shows a slight reversal tendency at high alpha, is examined.
languageEnglish
titleNASA-CR-3081num
titleWind tunnel force and pressure tests of a 21% thick general aviation airfoil with 20% aileron, 25% slotted flap and 10% slot-lip spoileen
typestandard
page116
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1979
contenttypefulltext
subject keywordsAILERONS
subject keywordsAIRFOIL
subject keywordsDISTRIBUTION
subject keywordsDRAG
subject keywordsGAW
subject keywordsLIFT
subject keywordsMOMENTS
subject keywordsPITCHING
subject keywordsPRESSURE
subject keywordsSLOT
subject keywordsSLOTS
subject keywordsSPOILER
subject keywordsSPOILERS
subject keywordsTESTS
subject keywordsTUNNEL
subject keywordsWIND
DSpace software copyright © 2017-2020  DuraSpace
نرم افزار کتابخانه دیجیتال "دی اسپیس" فارسی شده توسط یابش برای کتابخانه های ایرانی | تماس با یابش
yabeshDSpacePersian
 
DSpace software copyright © 2017-2020  DuraSpace
نرم افزار کتابخانه دیجیتال "دی اسپیس" فارسی شده توسط یابش برای کتابخانه های ایرانی | تماس با یابش
yabeshDSpacePersian