دانلود مقاله EXPERIMENTAL INVESTIGATION OF SIDESLIP EFFECT ON FOUR SLENDER DELTA WINGS تحت word
دانلود مقاله EXPERIMENTAL INVESTIGATION OF SIDESLIP EFFECT ON FOUR SLENDER DELTA WINGS تحت word دارای 11 صفحه می باشد و دارای تنظیمات در microsoft word می باشد و آماده پرینت یا چاپ است
فایل ورد دانلود مقاله EXPERIMENTAL INVESTIGATION OF SIDESLIP EFFECT ON FOUR SLENDER DELTA WINGS تحت word کاملا فرمت بندی و تنظیم شده در استاندارد دانشگاه و مراکز دولتی می باشد.
این پروژه توسط مرکز مرکز پروژه های دانشجویی آماده و تنظیم شده است
توجه : در صورت مشاهده بهم ريختگي احتمالي در متون زير ،دليل ان کپي کردن اين مطالب از داخل فایل ورد مي باشد و در فايل اصلي دانلود مقاله EXPERIMENTAL INVESTIGATION OF SIDESLIP EFFECT ON FOUR SLENDER DELTA WINGS تحت word ،به هيچ وجه بهم ريختگي وجود ندارد
بخشی از متن دانلود مقاله EXPERIMENTAL INVESTIGATION OF SIDESLIP EFFECT ON FOUR SLENDER DELTA WINGS تحت word :
سال انتشار: 1387
محل انتشار: یازدهمین کنفرانس دینامیک شاره ها
تعداد صفحات: 11
نویسنده(ها):
G. Behfarshad – PhD in Aerodynamics, gbehfarshad@yahoo.com Aerospace Research Complex, Malek Ashtar University of Technology
چکیده:
The influence of sideslip on flow over four sharp-edged delta wings of different aspect ratios with high sweep angle was investigated experimentally using surface pressure measurements at x/c=0.75. The tests have been carried out at different incidence angles ranging from 0,5,10,15,20 and 30 deg and at angles of sideslip ranging from zero to -15 deg. Various freestream velocity were used ranging from 10m/s to 30m/s corresponding to Reynolds number 1.7 x 10 5 to 5.2 x 10 5 based on root chord. Reynolds number was not found to have significant influence on spanwise surface pressure distribution profile while an increase in the angle of attack suggested an increase in vortex strength which may lead to vortex breakdown. The pressure distribution over lower aspect ratio wings were found to have asymmetric behaviour even at slight sideslip and this asymmetry increased with increasing sideslip angles and angles of attack.
[ بازدید : 237 ] [ امتیاز : 3 ] [ نظر شما : ]