• Cite/Export
  Cite/Export

  Copy a citation

  APA (6th ed.)

  

  Chicago (Author-Date, 15th ed.)

  

  Harvard (18th ed.)

  

  MLA (7th ed.)

  

  Turabian (6th ed.)

  

  Export a citation

  Export to RefWorks   Export to EndNote / Reference Manager   Export to EasyBib
  Export to EndNote / Reference Manager(non-Latin)   Cancel

  Note: Citations are based on reference standards. However, formatting rules can vary widely between applications and fields of interest or study. The specific requirements or preferences of your reviewing publisher, classroom teacher, institution or organization should be applied.
• Print
• E-mail
  E-mail

  All fields are required.

  The E-mail Address(es) field is required. Please enter recipient e-mail address(es).

  The E-mail Address(es) you entered is(are) not in a valid format. Please re-enter recipient e-mail address(es).

  You may send this item to up to five recipients.

  Enter recipient e-mail address(es): Separate up to five addresses with commas (,)

  The name field is required. Please enter your name.

  Enter your name: The subject field is required. Please enter the subject. Subject:

  The E-mail message field is required. Please enter the message.

  E-mail Message: I thought you might be interested in this item at http://www.worldcat.org/oclc/227859755 Title: Investigation of the Physics of Screech in Supersonic Jets and Turbulent Boundary Layers at High Reynolds Number and Control of Separation Through Oscillatory Blowing. Author: Hassan Nagib; Candace Wark; Ahmed Naguib; Israel Wygnanski; Michael Hites; ILLINOIS INST OF TECH CHICAGO FLUID DYNAMICS RESEARCH CENTER Publisher: Ft. Belvoir Defense Technical Information Center 15 MAR 1996. OCLC:227859755

  
  

  The ReCaptcha terms you entered were incorrect. Please try to match the 2 words shown in the window, or try the audio version.

  Cancel
• Share
• Permalink
  Permalink

  Copy this URL to link to this page:

• Write a review
• Rate this item:
• • 1
  • 2
  • 3
  • 4
  • 5

Investigation of the Physics of Screech in Supersonic Jets and Turbulent Boundary Layers at High Reynolds Number and Control of Separation Through Oscillatory Blowing.

Author:	Hassan Nagib; Candace Wark; Ahmed Naguib; Israel Wygnanski; Michael Hites; All authors
Publisher:	Ft. Belvoir Defense Technical Information Center 15 MAR 1996.
Edition/Format:	eBook : English
Summary:	Using a flapped NACA 0015 airfoil, measurements of static pressure and lift, with and without oscillatory forcing from the leading edge and flap, demonstrated effective separation control and lift enhancement over the range 0.1<M<0.4. Measurements showed that the lift increment was sensitive to the dimensionless forcing frequency. Additionally, a suction pressure coefficient of nearly -5.0 was produced on a previously stalled airfoil at M=0.4, indicating a region of supercritical flow on the airfoil, and suggesting that oscillatory blowing is a viable separation-control technique under compressible flow conditions. Using both the NDF test-section floor boundary layer and a suspended axisymmetric body, a range of momentum thickness Reynolds numbers of 7000<Re<50000 was investigated with a hot-wire anemometer. Streamwise mean and rms velocity and spectra in these boundary layers showed good agreement with established scaling observations. An increasing separation of scales and the appearance of a second low-frequency spectral peak were observed indicating a clear discrimination between inner and outer scales at high Reynolds number. Although some dependence on both axial and momentum thickness Reynolds number was observed, there appeared to be a linear relationship between friction velocity and free-stream velocity over this wide range of Reynolds numbers.  Read more...
Rating:	(not yet rated) 0 with reviews - Be the first.
Subjects	Aerodynamics. Fluid Mechanics. Turbulent boundary layer. View all subjects
More like this	Similar Items