EXPERIMENTAL INVESTIGATION OF SIDESLIP EFFECT ON FOUR SLENDER DELTA WINGS

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.

کلیدواژه ها:

Single Delta Wings ، Sideslip ، Vortex Breakdown ،