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Author : Donald Eckhart Emerson
Publisher :
ISBN 13 :
Total Pages : 246 pages
Book Rating : 4.:/5 (21 download)
Download or read book Investigation of a Thick Laminar Boundary Layer in a Supersonic Nozzle written by Donald Eckhart Emerson and published by . This book was released on 1951 with total page 246 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Edwin Snow Gallacher
Publisher :
ISBN 13 :
Total Pages : 214 pages
Book Rating : 4.E/5 ( download)
Download or read book Theoretical Investigation of a Boundary Layer and Heat Transfer in a Supersonic Nozzle written by Edwin Snow Gallacher and published by . This book was released on 1950 with total page 214 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Klaus Oswatitsch
Publisher :
ISBN 13 :
Total Pages : 68 pages
Book Rating : 4.3/5 (126 download)
Download or read book Theoretical Analysis of Stationary Potential Flows and Boundary Layers at High Speed written by Klaus Oswatitsch and published by . This book was released on 1948 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: The present report consists of two parts. The first part deals with the two-dimensional stationary flow in the presence of local supersonic zones. A numerical method of integration of the equation of gas dynamics is developed. Proceeding from solutions at great distance from the body the flow pattern is calculated step by step. Accordingly the related body form is obtained at the end of the calculation. The second part treats the relationship between the displacement thickness of laminar and turbulent boundary layers and the pressure distribution at high speeds. The stability of the boundary layer is investigated, resulting in basic differences in the behavior of subsonic and supersonic flows. Lastly, the decisive importance of the boundary layer for the pressure distribution, particularly for thin profiles, is demonstrated.
Author : J. P. Kreskovsky
Publisher :
ISBN 13 :
Total Pages : 100 pages
Book Rating : 4.:/5 (31 download)
Download or read book Parametric Study of Relaminarization of Turbulent Boundary Layers on Nozzle Walls written by J. P. Kreskovsky and published by . This book was released on 1974 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Laura L. Pauley
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book A Numerical Investigation of Supersonic Nozzle Boundary Layer Transition written by Laura L. Pauley and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : William D. Harvey
Publisher :
ISBN 13 :
Total Pages : 92 pages
Book Rating : 4.:/5 (31 download)
Download or read book Experimental and Numerical Investigation of Boundary-layer Development and Transition on the Walls of a Mach 5 Nozzle written by William D. Harvey and published by . This book was released on 1975 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Robert L. P. Voisinet
Publisher :
ISBN 13 :
Total Pages : 144 pages
Book Rating : 4.3/5 (91 download)
Download or read book Measurements of a Supersonic Favorable-pressure-gradient Turbulent Boundary Layer with Heat Transfer written by Robert L. P. Voisinet and published by . This book was released on 1973 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a detailed experimental investigation of the compressible turbulent boundary layer in a favorable-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall at momentum thickness Reynolds numbers from 6,700 to 56,000 and at three wall-to-adiabatic-wall temperature ratios. An attempt was made to hold values of Clauser's pressure-gradient parameter constant. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. (Modified author abstract).
Author : John Russell Radbill
Publisher :
ISBN 13 :
Total Pages : 216 pages
Book Rating : 4.:/5 (176 download)
Download or read book Analytical Investigation of the Effects of a Diffusion Field on a Laminar Boundary Layer in Supersonic Flow written by John Russell Radbill and published by . This book was released on 1958 with total page 216 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 580 pages
Book Rating : 4.X/5 (4 download)
Download or read book Compressible Turbulent Boundary Layers written by and published by . This book was released on 1969 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : S. William Gouse
Publisher :
ISBN 13 :
Total Pages : 286 pages
Book Rating : 4.:/5 (323 download)
Download or read book Experimental Investigation of the Effects of a Diffusion Field on a Laminar Boundary Layer in Supersonic Flow written by S. William Gouse and published by . This book was released on 1957 with total page 286 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (227 download)
Download or read book A Free Flight Investigation of the Feasibility of High Reynolds Number Supersonic Laminar Boundary Layers written by and published by . This book was released on 1952 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A modified V-2 was fired 26 October 1950, at White Sands Proving Ground to determine whether, under favorable conditions, laminar flow at high Reynolds Numbers at supersonic speeds was possible. The test area was the surface of a special polished 20 deg included angle conical nose more than eight feet long, which replaced the standard V-2 warhead. The rocket reached M = 3 at 25,000 feet in approximately horizontal flight before it exploded from unknown causes. With the large thermal inertial of the .18-inch thick skin, the skin temperature lagged well behind the boundary layer recovery temperature. Consequently, during most of the supersonic portion of the flight, the heat transfer from the air to the surface was greater than that required to damp small boundary layer oscillations according to Lees' theory. Measurements of the nose skin temperature and of total pressures in the boundary layer were telemetered in order to establish the laminar or turbulent state of the boundary layer. The pressure and temperature data indicate that the cone boundary layer was laminar at an equivalent flat plate Reynolds Number of 5 x 10 to the 7th power which was the largest Reynolds Number obtained on the cone. (Author).
Author : Joseph Sternberg
Publisher :
ISBN 13 :
Total Pages : 48 pages
Book Rating : 4.:/5 (227 download)
Download or read book A Free Flight Investigation of the Feasibility of High Reynolds Number Supersonic Laminar Boundary Layers written by Joseph Sternberg and published by . This book was released on 1952 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: A modified V-2 was fired 26 October 1950, at White Sands Proving Ground to determine whether, under favorable conditions, laminar flow at high Reynolds Numbers at supersonic speeds was possible. The test area was the surface of a special polished 20 deg included angle conical nose more than eight feet long, which replaced the standard V-2 warhead. The rocket reached M = 3 at 25,000 feet in approximately horizontal flight before it exploded from unknown causes. With the large thermal inertial of the .18-inch thick skin, the skin temperature lagged well behind the boundary layer recovery temperature. Consequently, during most of the supersonic portion of the flight, the heat transfer from the air to the surface was greater than that required to damp small boundary layer oscillations according to Lees' theory. Measurements of the nose skin temperature and of total pressures in the boundary layer were telemetered in order to establish the laminar or turbulent state of the boundary layer. The pressure and temperature data indicate that the cone boundary layer was laminar at an equivalent flat plate Reynolds Number of 5 x 10 to the 7th power which was the largest Reynolds Number obtained on the cone. (Author).
Author : Davis H. Crawford
Publisher :
ISBN 13 :
Total Pages : 680 pages
Book Rating : 4.F/5 ( download)
Download or read book Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8 written by Davis H. Crawford and published by . This book was released on 1956 with total page 680 pages. Available in PDF, EPUB and Kindle. Book excerpt: At the stagnation point, the theory of Sibulkin, using the diameter and conditions behind the normal shock, was in good agreement with the experiment when the velocity graident at the stagnation opint appropriate to the free-stream Mach number was used.
Author : Paul Joseph Shall (Jr)
Publisher :
ISBN 13 :
Total Pages : 78 pages
Book Rating : 4.:/5 (227 download)
Download or read book A Boundary Layer Study on Hypersonic Nozzles written by Paul Joseph Shall (Jr) and published by . This book was released on 1968 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was made to determine the structure and integrated properties of turbulent boundary layers in hypersonic nozzles, at Mach numbers between 10 and 12. It is concluded that the 1/7-power velocity profile does not agree with the experimental data in this Mach number range. However, a velocity profile based on the Crocco energy relations agrees well with the data as does the corresponding temperature profile, except at the point of maximum temperature. The semi-empirical relationships for boundary layer thickness and displacement thickness, proposed by Burke are strongly supported by the experimental data of this study. (Author).
Author : Walter Samuel Bradfield
Publisher :
ISBN 13 :
Total Pages : 344 pages
Book Rating : 4.:/5 (319 download)
Download or read book An Experimental Investigation of the Turbulent Boundary Layer in Supersonic Flow Around Unyawed Cones with Small Heat Transfer and Correlations with Two Dimensional Data written by Walter Samuel Bradfield and published by . This book was released on 1957 with total page 344 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : David F. Gates
Publisher :
ISBN 13 :
Total Pages : 124 pages
Book Rating : 4.3/5 (91 download)
Download or read book Measurements of Upstream History Effects in Compressible Turbulent Boundary Layers written by David F. Gates and published by . This book was released on 1973 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report describes an experimental study of compressible turbulent boundary layers for which the upstream history was systematically varied. A series of experiments was conducted using both a supersonic half nozzle and a conventional flat plate for which the nozzle throat and flat plate leading edge can be temperature controlled. The supersonic nozzle provided a favorable upstream pressure gradient together with a controlled thermal history at the throat. The flat plate provided upstream temperature control with no pressure history. Velocity and temperature profile and heat-transfer measurements were made in a downstream region of zero-pressure-gradient and constant wall temperature. (Modified author abstract).
Author : S. R. Pate
Publisher :
ISBN 13 :
Total Pages : 46 pages
Book Rating : 4.3/5 (91 download)
Download or read book Investigation of Drag Reduction by Boundary-layer Suction on a Flat Plate and a 36-deg Swept Wing at Supersonic Speeds written by S. R. Pate and published by . This book was released on 1962 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in a 40-in. supersonic tunnel to determine the effectiveness of boundary-layer suction for laminar flow control on a two-dimensional, biconvex, 36-degree swept wing and on a flat plate with and without shock impingement. Test Mach numbers were 2.5, 3, 3.5, and 4 with a Reynolds-number/in. range from 0.17 to 0.66 x 10 to the sixth power. With suction, full chord laminar flow was maintained on the flat plate at free stream Mach number of 2.5 and 3 at length Reynolds numbers of 22 and 26.5 x 10 to the sixth power, respectively, which resulted in a total drag reduction of 77 and 74%. With suction and shock impingement across the plate resulting from a 1-degree shock generator angle, full chord laminar flow was maintained at free stream Mach number of 2.5, 3, and 3.5 at length Reynolds numbers of 19.7, 18.9, and 21.7 x 10 to the sixth power, respectively. On the 36-degree swept wing, full chord laminar flow was maintained with suction up to a length Reynolds number of 11.3 x 10 to the sixth power at free stream Mach number of 3. (Author).
