A Boundary Layer Study on Hypersonic Nozzles 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 A Boundary Layer Study on Hypersonic Nozzles PDF full book. Access full book title A Boundary Layer Study on Hypersonic Nozzles by Paul Joseph Shall (Jr). Download full books in PDF and EPUB format.
Author: Paul Joseph Shall (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 78
Get Book Here
Book Description
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: Paul Joseph Shall (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 78
Get Book Here
Book Description
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: Dennis M. Bushnell
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 44
Get Book Here
Book Description
Turbulent boundary layer measurements on axisymmetric hypersonic nozzle walls.
Author: Joan Patricia Gosink
Publisher:
ISBN:
Category : Nozzles
Languages : en
Pages : 148
Get Book Here
Book Description
Author: John B. Anders
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 36
Get Book Here
Book Description
A hypersonic-wind-tunnel nozzle concept which incorporates a hot-core flow surrounded by an annular flow of cold air offers a promising technique for maximizing the model size while minimizing the power required to heat the test core. This capability becomes especially important when providing the true-temperature duplication needed for hypersonic propulsion testing. Several two-dimensional wind-tunnel nozzle configurations that are designed according to this concept are analyzed by using recently developed analytical techniques for prediction of the boundary-layer growth and the mixing between the hot and cold coaxial supersonic airflows. The analyses indicate that introduction of the cold annular flow near the throat results in an unacceptable test core for the nozzle size and stagnation conditions considered because of both mixing and condensation effects. Use of a half-nozzle with a ramp on the flat portion does not appear promising because of the thick boundary layer associated with the extra length. However, the analyses indicate that if the cold annular flow is introduced at the exit of a full two-dimensional nozzle, an acceptable test core will be produced. Predictions of the mixing between the hot and cold supersonic streams for this configuration show that mixing effects from the cold flow do not appreciably penetrate into the hot core for the large downstream distances of interest.
Author: Ralph C. Tolle
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 274
Get Book Here
Book Description
Author: Max Kinslow
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 40
Get Book Here
Book Description
The potential value of controlled boundary-layer removal from the wall of a nozzle for low-density hypersonic flow was investigated in a brief experimental program. A particular objective was the achievement of sufficient control over boundary-layer thickness to enable a contoured nozzle to be operated under off-design conditions without excessive deterioration of flow uniformity. The nozzle contour was greatly influenced by boundary-layer thickness. Boundary-layer removal involved suction through perforated walls where local nozzle static pressures exceeded the pressure in the large tank which enclosed the nozzle and test section.
Author: Kenneth Morris Jones
Publisher:
ISBN:
Category :
Languages : en
Pages : 276
Get Book Here
Book Description
Author: James Daryl Cox (1LT, USAF.)
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 64
Get Book Here
Book Description
Author: Serge A. Waiter
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 44
Get Book Here
Book Description
Author: Norman Ellis Scaggs
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 78
Get Book Here
Book Description
An experimental investigation made to determine the flow parameter profiles across the boundary layer on contoured, axisymmetric hypersonic nozzles is described. The pitot pressure and total temperature profiles measured across the boundary layers on nozzles of Mach number seven and twelve are shown in graphical form. The static temperature and velocity profiles, calculated with the assumption of constant static pressure across the boundary layer, are given. A correlation is shown to exist between the exponent of the velocity profile power law and the product of the ratios of wall temperature to free stream total temperature and axial distance to momentum thickness. The static temperature profiles, calculated from the measured data is compared with Crocco's relationship for the static temperature in terms of the velocity profile. (Author).
