An Experimental Investigation of Low Speed Dynamic Stall and Reattachment of the NACA 23012 Aerofoil Under Constant Pitch Motion PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download An Experimental Investigation of Low Speed Dynamic Stall and Reattachment of the NACA 23012 Aerofoil Under Constant Pitch Motion PDF full book. Access full book title An Experimental Investigation of Low Speed Dynamic Stall and Reattachment of the NACA 23012 Aerofoil Under Constant Pitch Motion by Lup Yun Seto. Download full books in PDF and EPUB format.
Author: Lup Yun Seto
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages :
Get Book Here
Book Description
Author: Lup Yun Seto
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages :
Get Book Here
Book Description
Author: Michael S. Francis
Publisher:
ISBN:
Category :
Languages : en
Pages : 158
Get Book Here
Book Description
The results of an experimental investigation of airfoil dynamic stall involving large amplitude pitching motions are described. The discussion is focused on constant pitch rate motion histories. Measurements of unsteady surface pressure distributions for both NACA 0012 and NACA 64 sub 1 A012(13) profiles have been employed to infer the onset and evolution of an energetic leading edge separation vortex over a wide range of flow and motion conditions. These data have also been integrated to provide estimates of the time histories of the lift, pressure drag and moment coefficients. The effectiveness of the various motions for achieving lift enhancement has been determined through the introduction of a dimensionless impulse parameter which accounts for both the magnitude and duration of the additional lift increment during the post-stall period. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1150
Get Book Here
Book Description
Author: Michael S. Francis
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages :
Get Book Here
Book Description
"The results of an experimental investigation of airfoil dynamic stall involving large amplitude pitching motions are described. The discussion is focused on constant pitch rate motion histories. Measurements of unsteady surface pressure distributions for both NACA 0012 and NACA 64 sub 1 A012(13) profiles have been employed to infer the onset and evolution of an energetic leading edge separation vortex over a wide range of flow and motion conditions. These data have also been integrated to provide estimates of the time histories of the lift, pressure drag and moment coefficients. The effectiveness of the various motions for achieving lift enhancement has been determined through the introduction of a dimensionless impulse parameter which accounts for both the magnitude and duration of the additional lift increment during the post-stall period."--Abstract, report documention p.
Author: K. W. McAlister
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 80
Get Book Here
Book Description
Author: D. C. Daley
Publisher:
ISBN:
Category :
Languages : en
Pages : 82
Get Book Here
Book Description
This thesis discusses an experimental investigation of dynamic stall for an NACA 0015 airfoil rotated at different constant angular rates. It describes a microcomputer-based automatic data acquisition system capable of acquiring 1000 items of data per second. When this information was used to predict stall and compared with film-data stall indications of the same test runs, there was excellent correlation between them. Results of the investigation showed a consistent correlation between the stall angle at dynamic conditions and the nondimensionalized angular rate. Experimental data was obtained for non-dimensional angular rates (defined as one half the chord times the angular rate divided by free stream velocity) in the range of .005 to .06. (Author).
Author: Mark William Gracey
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: Leonard M. Rose
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 28
Get Book Here
Book Description
A faired, double-wedge airfoil section, 4.23 percent thick, was investigated with plain nose and trailing-edge flaps. The nose flap was 0.16 chord of the airfoil and the trailing-edge flap was 0.25 chord of the airfoil. Section lift, drag, and pitching-momnet data are presented for a Reynolds number of 5,800,000 which corresponded to a Mach number of 0.17.
Author: S. J. Schreck
Publisher:
ISBN:
Category :
Languages : en
Pages : 147
Get Book Here
Book Description
Flow over an NACA 0015 airfoil undergoing a constant rate of change of angle of attack was experimentally studied over a range of tunnel speeds and rotation rates. Surface pressure transducers coupled with a microcomputer-based data acquisition system were used to collect surface-pressure data at the rate of 4000 samples per second; data reduction was also microcomputer-based. Data was reduced in two forms: (1) C sub l versus alpha curves through stall were determined for each dynamic experimental configuration. This was accomplished by numerical integration of pressure data at a number of angles through stall, each data point representing the average of five experiments at the same experimental conditions. These curves indicated a slight decrease in C sub l - alpha slope with increasing angle of attack angular rate. (2) Increase in stall angle of attack of the dynamic over the static case was plotted against a nondimensional angular rate parameter (defined as the product of one-half the chord length and angular rotation rate, divided by the freestream velocity). This comparison gave rise to an apparently universal curve of nondimensional angular rotation rate versus increase in stall angle of attack. This curve was in agreement in some sense with previous experiments using stall indicators other than the actual stall.
Author: Katie Kristine Thorne
Publisher:
ISBN:
Category :
Languages : en
Pages : 101
Get Book Here
Book Description
