An investigation was conducted in the Langley 1/8-scale V/STOL model tunnel on a semispan delta wing with a leading-edge sweep of 74 deg, to determine the effectiveness of various locations of upper surface and reflection plane blowing on leading-edge vortex bursting. Constant area nozzles were located on the wing upper surface along a ray swept 79 deg, which was beneath the leading-edge vortex core. The bursting and reformation of the leading-edge vortex was viewed by injecting helium into the vortex core, and employing a schlieren system
The dye injection and hydrogen bubble visualization techniques are used to investigate the dual-vort...
It is found that the entrainment effect of a thin jet emerging from the leading edge of a delta win...
The aerodynamic effects of spanwise blowing on the trailing edge flap of an advanced fighter aircraf...
Flow visualization studies were conducted in a small pilot wind tunnel to determine qualitative effe...
A wind tunnel test was conducted to determine the effects of over-the-wing blowing as a means of aug...
Wind-tunnel data were obtained at a free-stream Mach number of 0.26 for a range of model angle of at...
Flow visualization studies were conducted to qualitatively determine the effects of active generatio...
Eleven semi-span wing models were tested in the 1/8-scale model of the Langley V/STOL tunnel to qual...
SEE A90-458458th AIAA Applied Aerodynamics Conference; Aug. 20-22, 1990; Portland, OR; United States...
Water tunnel studies were performed to define the changes that occur in vortex flow fields above the...
It has been demonstrated that leading edge vortices (LEVs) formed by airflow past an elevated delta ...
Exploratory wind tunnel tests are reported on a 74 deg. delta wing model. The potential of a vortex ...
The effects of spanwise blowing on two configurations representative of current fighter airplanes we...
An experimental wind tunnel test of a 65 deg delta wing model with interchangeable leading edges was...
An experimental study, based on a swept wing, was undertaken in the water tunnel and the wind tunnel...
The dye injection and hydrogen bubble visualization techniques are used to investigate the dual-vort...
It is found that the entrainment effect of a thin jet emerging from the leading edge of a delta win...
The aerodynamic effects of spanwise blowing on the trailing edge flap of an advanced fighter aircraf...
Flow visualization studies were conducted in a small pilot wind tunnel to determine qualitative effe...
A wind tunnel test was conducted to determine the effects of over-the-wing blowing as a means of aug...
Wind-tunnel data were obtained at a free-stream Mach number of 0.26 for a range of model angle of at...
Flow visualization studies were conducted to qualitatively determine the effects of active generatio...
Eleven semi-span wing models were tested in the 1/8-scale model of the Langley V/STOL tunnel to qual...
SEE A90-458458th AIAA Applied Aerodynamics Conference; Aug. 20-22, 1990; Portland, OR; United States...
Water tunnel studies were performed to define the changes that occur in vortex flow fields above the...
It has been demonstrated that leading edge vortices (LEVs) formed by airflow past an elevated delta ...
Exploratory wind tunnel tests are reported on a 74 deg. delta wing model. The potential of a vortex ...
The effects of spanwise blowing on two configurations representative of current fighter airplanes we...
An experimental wind tunnel test of a 65 deg delta wing model with interchangeable leading edges was...
An experimental study, based on a swept wing, was undertaken in the water tunnel and the wind tunnel...
The dye injection and hydrogen bubble visualization techniques are used to investigate the dual-vort...
It is found that the entrainment effect of a thin jet emerging from the leading edge of a delta win...
The aerodynamic effects of spanwise blowing on the trailing edge flap of an advanced fighter aircraf...
Add to ORKG