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NASA-TN-D-6909

Dynamic stability derivatives at angles of attack from -5 degrees to 90 degrees for a variable-sweep fighter configuration with twin vertical tails

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T18:47:01Z
date available2017-09-04T18:47:01Z
date copyright01/01/1972
date issued1972
identifier otherAMYKAEAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std;query=authoCA58ear3081D206861598F1EFDEC014A/handle/yse/228217
description abstractAn investigation was conducted in the Langley full-scale tunnel to determine the dynamic stability derivatives in pitch, roll, and yaw over an angle-of-attack range of -5 deg to 90 deg for a variable-sweep fighter configuration with twin vertical tails. The study consisted of forced-oscillation tests of a 1/10-scale model of the airplane at a Reynolds number of 0.4 million based on the reference wing mean aerodynamic chord. Tests were conducted for wing sweep angles of 22 deg, 35 deg, 50 deg, and 68 deg, and the effects of the vertical and horizontal tails, wing leading-edge slats, nose-mounted canards, and frequency of the oscillation were also evaluated.
languageEnglish
titleNASA-TN-D-6909num
titleDynamic stability derivatives at angles of attack from -5 degrees to 90 degrees for a variable-sweep fighter configuration with twin vertical tailsen
typestandard
page54
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1972
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsAIRCRAFT
subject keywordsCHARACTERISTICS
subject keywordsCONFIGURATIONS
subject keywordsDERIVATIVES
subject keywordsFIGHTER
subject keywordsSTABILITY
subject keywordsSWEEP
subject keywordsTESTS
subject keywordsTUNNEL
subject keywordsVARIABLE
subject keywordsWIND
subject keywordsWINGS


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