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EBookClubs

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Book An Experimental Investigation of Supersonic Flow in Long Channels

Download or read book An Experimental Investigation of Supersonic Flow in Long Channels written by Malcom Green and published by . This book was released on 1951 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book An Experimental Investigation of Supersonic Flow

Download or read book An Experimental Investigation of Supersonic Flow written by Joseph Francis Madden (Jr.) and published by . This book was released on 1941 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book An Experimental Investigation of Separated Turbulent Supersonic Flow at M

Download or read book An Experimental Investigation of Separated Turbulent Supersonic Flow at M written by Robert Earl Wilson and published by . This book was released on 1966 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book An Experimental Investigation of the Laminar Boundary Layer on a Spinning Ogive Cylinder in Supersonic Flow

Download or read book An Experimental Investigation of the Laminar Boundary Layer on a Spinning Ogive Cylinder in Supersonic Flow written by William C. Ragsdale and published by . This book was released on 1972 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pitot pressure surveys were made of the laminar boundary layer on an ogive-cylinder model at Mach 3.02 and 4.10. Surveys were made at five stations along the model, at angles of attack of zero and four degrees, with and without spin. Tests with spin were performed at Mach 3.02. The pitot pressure data has been used to compute boundary-layer velocity profiles, and results from two data-reduction procedures are presented. Some comparisons are made with theoretical velocity profiles for the zero spin, zero angle-of-attack case. (Author).

Book Experimental Investigation of Supersonic Flow with Detached Shock Waves for Mach Numbers Between 1 8 and 2 9

Download or read book Experimental Investigation of Supersonic Flow with Detached Shock Waves for Mach Numbers Between 1 8 and 2 9 written by W. E. Moeckel and published by . This book was released on 1950 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an experimental investigation of the flow near the nose of plane and axially symmetric bodies in the presence of detached shock waves are compared with predictions of theory. The location of the detached shock wave was determined from schlieren photographs for a variety of nose shapes over a range of free-stream Mach numbers from 1.8 to 2.9. At a Mach number of 1.9, the form of the detached wave and the pressure distribution over the body were investigated for each nose shape. In addition, the relation between shock location and flow spillage was determined for several axially symmetric nose inlets.

Book Experimental Investigation of Combustion Stabilization in Supersonic Flow Using Free Recirculation Zones

Download or read book Experimental Investigation of Combustion Stabilization in Supersonic Flow Using Free Recirculation Zones written by and published by . This book was released on 1997 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Final report summarizes shortly main results of the quarterly reports and presents experimental results on self-ignition and combustion stabilization in supersonic flow using free recirculation zone. Tests are conducted at hypersonic facility TsAGI T-131B. Measurements are performed in a nearly matched supersonic jet at the exit of two-dimensional channel over Mach number range M=2.O-2.8 at stagnation temperature range Tt=1200-1400K. initial thickness of jet was equal 67 mm. Self-ignition and stabilization are obtained at Tt=1400K. Self-ignition was absent at Tt=1200K, 1300K. Thickness of free recirculation zone was about 25-30 mm.

Book An Experimental Study of Slot Injection Into a Supersonic Stream

Download or read book An Experimental Study of Slot Injection Into a Supersonic Stream written by Michael Kenworthy and published by . This book was released on 1973 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of two-dimensional tangential-slot injection into a turbulent boundary layer at a freestream Mach number of 2.4 has been conducted. Nearly adiabatic surface temperatures were maintained during all tests. Static and pitot pressure profiles at four stations downstream of the slot were obtained. Skin friction was measured at the last three stations with a self-nulling balance. Schlieren photographs of the flow field were also obtained. Most of the data were obtained with slot Mach numbers of 0.31 and 0.66 corresponding to slot pressure less than and equal to stream static pressure, respectively. For the latter matched-pressure case, tangential slot injection reduced the surface shear at the three measuring stations by about 60 to 20 percent for increasing downstream distances from the slot of 12 to 28 slot heights. However, for the other case where slot pressure was less than stream static pressure, the effect of injection was to increase the shear by about 90 percent at the last downstream station of 28 slot heights. This increase in shear is attributed to the rapid acceleration of the low speed injectant stream by the high speed main stream and the increasing pressure through the recompression zone which is absent for the matched pressure case.

Book An Experimental Investigation of a Supersonic Vortical Flow

Download or read book An Experimental Investigation of a Supersonic Vortical Flow written by Brian S. Levey and published by . This book was released on 1991 with total page 284 pages. Available in PDF, EPUB and Kindle. Book excerpt: