CoefficientofLift MomentCoefficient CoefficientofPressure DDrag IIntegral Reynold'sNumber uFreeStreamVelocity AngleofAttack Density C D C f C L C M C p R e αρ INTRODUCTION ThisexperimentanalyzestheNACA0015airfoilinalowspeedwindtunnel atvaryinganglesofattack.TheNACA0015isasymmetricalairfoilwitha15% ...
LIFT, DRAG AND MOMENT OF A NACA 0015 (升力、阻力和NACA 0015的时刻).pdf,LIFT, DRAG AND MOMENT OF A NACA 0015 AIRFOIL by Steven D. Miller DEPARTMENT OF AEROSPACE ENGINEERING THE OHIO STATE UNIVERSITY 28 MAY 2 8 i ABSTRACT A NACA 15 symmetrical airfoil wi
Fluctuations in the lift and drag coefficients on the non-actuated airfoil are found to be governed by the vortex shedding frequency. Provided that the momentum coefficient is sufficiently high, the lift and drag coefficients tend to fluctuate at the synthetic jet frequency. The mean lift ...
The main objective is to reduce the take off distance of the aircraft by minimizing the drag force. The project includes CFD analysis of vortex effect on the 3D model of airfoil NACA 0015. Dimple shape may be semi-sphere of 15 mm in different configuration i.e. inward and outward and 1...
For example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord. The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. The 15 indicates that the airfoil has a 15% thic...
The k-o SST model overpredict thedragcoefficient when AOA vairies between 30 and 150 degree.5 failed to capture the lift at AOA between 150 and 180 degrees.5 Stall is difficult to quantify experimentally Post stall data >> Extrapolation ...
The k-o SST model overpredict the drag coefficient when AOA vairies between 30 and 150 degree.5 failed to capture the lift at AOA between 150 and 180 degrees. 5 Stall is difficult to quantify experimentally Post stall data >> Extrapolation Extraplolation methods: Viterna and Corrigan 4...
The base drag coefficient measured on this model varied from a value of -0,0015 in the subsonic range to a maximum of about 0.0020 at a Mach number of 1.28, Drag coefficients for the equivalent-body models varied from about 0.125 (based on body maximum area) in the subsonic range to ...
The study focuses on the symmetric NACA0012 and NACA0015 airfoils and aims to improve their lift-to-drag ratio using CFJ flow control. They examine a range of CFJ parameters, such as jet angle and momentum coefficient, to determine the optimal CFJ configuration for improving the airfoil ...
It is found that plasma actuation can effectively suppress flow separation on the airfoil at free-stream speeds in the range from 20 m/s up to 65 m/s. When the speed is 25m/s, the stall angle will be delayed by 3掳, lift coefficient will increase and drag coefficient will decrease by...