Author: Walter B. Sturek
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 34
Book Description
Measurements are reported of the total temperature profile in the turbulent boundary layer on a supersonic tunnel nozzle wall for two values of tunnel total temperature. The resulting two conditions of tunnel wall heat transfer history significantly affected the temperature profiles. The trend of the data is shown to agree with the wall heat transfer history when evaluated in terms of the enthalpy flux deficit. (Author).
Wall Heat Transfer Effects on Supersonic Nozzle Wall Boundary-layer Temperature Profiles
Author: Walter B. Sturek
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 34
Book Description
Measurements are reported of the total temperature profile in the turbulent boundary layer on a supersonic tunnel nozzle wall for two values of tunnel total temperature. The resulting two conditions of tunnel wall heat transfer history significantly affected the temperature profiles. The trend of the data is shown to agree with the wall heat transfer history when evaluated in terms of the enthalpy flux deficit. (Author).
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 34
Book Description
Measurements are reported of the total temperature profile in the turbulent boundary layer on a supersonic tunnel nozzle wall for two values of tunnel total temperature. The resulting two conditions of tunnel wall heat transfer history significantly affected the temperature profiles. The trend of the data is shown to agree with the wall heat transfer history when evaluated in terms of the enthalpy flux deficit. (Author).
Measurements of Upstream History Effects in Compressible Turbulent Boundary Layers
Author: David F. Gates
Publisher:
ISBN:
Category : Supersonic nozzles
Languages : en
Pages : 124
Book Description
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).
Publisher:
ISBN:
Category : Supersonic nozzles
Languages : en
Pages : 124
Book Description
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).
A Review of High-speed, Convective, Heat-transfer Computation Methods
Author: Michael E. Tauber
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 44
Book Description
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 44
Book Description
Survey of Boundary Layer Heat Transfer at High Velocities and High Temperatures
Author: Ernst Rudolf Georg Eckert
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 118
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 118
Book Description
Comparison of Prediction Methods and Studies of Relaxation in Hypersonic Turbulent Nozzle-wall Boundary Layers
Author: Dennis M. Bushnell
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 44
Book Description
Turbulent boundary layer measurements on axisymmetric hypersonic nozzle walls.
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 44
Book Description
Turbulent boundary layer measurements on axisymmetric hypersonic nozzle walls.
Determination of the Heat Transfer Properties of a Turbulent Boundary Layer in the Case of Supersonic Flow when the Temperature Distribution Along the Constraining Wall is Arbitrarily Assigned
Scientific and Technical Aerospace Reports
Heat Transfer and Boundary Layer in Conical Nozzles
Author: Donald R. Boldman
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 68
Book Description
A review of a comprehensive experimental investigation of the heat transfer and boundary layer in 30 deg to 15 deg and 60 deg to 15 deg conical nozzles is presented. The experiments were conducted with air at a stagnation temperature of 539 K (970 R) and throat Reynolds numbers based on a diameter ranging from 6 x 10 to the 5th power to 5 x 10 to the 6th power. Nozzle wall surface finish was varied from a smooth machine finish to a 826 x 10 to the minus 6th power cm (325 x 10 to the minus 6th in.) rms sandblasted finish. Measured heat transfer and wall temperatures are tabulated.
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 68
Book Description
A review of a comprehensive experimental investigation of the heat transfer and boundary layer in 30 deg to 15 deg and 60 deg to 15 deg conical nozzles is presented. The experiments were conducted with air at a stagnation temperature of 539 K (970 R) and throat Reynolds numbers based on a diameter ranging from 6 x 10 to the 5th power to 5 x 10 to the 6th power. Nozzle wall surface finish was varied from a smooth machine finish to a 826 x 10 to the minus 6th power cm (325 x 10 to the minus 6th in.) rms sandblasted finish. Measured heat transfer and wall temperatures are tabulated.
Boundary-layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6
Supersonic Free-flight Measurements of Heat Transfer and Transition on a 10° Cone Having a Low Temperature Ratio
Author: Charles F. Merlet
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
Book Description
Heat-transfer coefficients in the form of Stanton number and boundary-layer transition data were obtained from a free-flight test of a 100-inch-long 10° total-angle cone with a 1/16-inch tip radius which penetrated deep into the region of infinite stability of laminar boundary layer over a range of wall-to-local-stream temperature radius and for local Mach numbers from 1.8 to 3.5. Experimental heat-transfer coefficients, obtained at Reynolds numbers up to 160 x 106, were in general somewhat higher than theoretical values. A maximum Reynolds number of transition of only 33 x 106 was obtained. Contrary to theoretical and some other experimental investigations, the transition Reynolds number initially increased while the wall temperature ratio increased at relatively constant Mach number. Further increases in wall temperature ratio were accompanied by a decrease in transition Reynolds number. Increasing transition Reynolds number with increasing Mach number was also indicated at a relatively constant wall temperature ratio.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
Book Description
Heat-transfer coefficients in the form of Stanton number and boundary-layer transition data were obtained from a free-flight test of a 100-inch-long 10° total-angle cone with a 1/16-inch tip radius which penetrated deep into the region of infinite stability of laminar boundary layer over a range of wall-to-local-stream temperature radius and for local Mach numbers from 1.8 to 3.5. Experimental heat-transfer coefficients, obtained at Reynolds numbers up to 160 x 106, were in general somewhat higher than theoretical values. A maximum Reynolds number of transition of only 33 x 106 was obtained. Contrary to theoretical and some other experimental investigations, the transition Reynolds number initially increased while the wall temperature ratio increased at relatively constant Mach number. Further increases in wall temperature ratio were accompanied by a decrease in transition Reynolds number. Increasing transition Reynolds number with increasing Mach number was also indicated at a relatively constant wall temperature ratio.