Author: John R. Jack
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 16
Book Description
An investigation was made at a Mach number of 3.12 to determine the effects of heat transfer on boundary-layer transition. Data were obtained for a cone cylinder and a parabolic-nosed cylinder at Reynolds numbers up to 12,000,000 based on body length. The results show that cooling the cone-cylinder model to a wall-to-free-stream static-temperature ratio of approximately 1.4 increased the transition Reynolds number from a value of about 2,000,000 at equilibrium to 10,600,000. For temperature ratios less than 1.4, the boundary-layer flow was laminar over the entire model. The rapid increase of transition Reynolds number with small reductions in temeprature ratio near 1.4 indicated that temperature ratios slight lower may result in a laminar boundary layer for very high Reynolds numbers. For the parabolic-nosed body, the transition Reynolds number was about twice that of the cone-cylinder model over the temperature range investigated.
Variation of Boundary-layer Transition with Heat Transfer on Two Bodies of Revolution at a Mach Number of 3.12
Author: John R. Jack
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 16
Book Description
An investigation was made at a Mach number of 3.12 to determine the effects of heat transfer on boundary-layer transition. Data were obtained for a cone cylinder and a parabolic-nosed cylinder at Reynolds numbers up to 12,000,000 based on body length. The results show that cooling the cone-cylinder model to a wall-to-free-stream static-temperature ratio of approximately 1.4 increased the transition Reynolds number from a value of about 2,000,000 at equilibrium to 10,600,000. For temperature ratios less than 1.4, the boundary-layer flow was laminar over the entire model. The rapid increase of transition Reynolds number with small reductions in temeprature ratio near 1.4 indicated that temperature ratios slight lower may result in a laminar boundary layer for very high Reynolds numbers. For the parabolic-nosed body, the transition Reynolds number was about twice that of the cone-cylinder model over the temperature range investigated.
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 16
Book Description
An investigation was made at a Mach number of 3.12 to determine the effects of heat transfer on boundary-layer transition. Data were obtained for a cone cylinder and a parabolic-nosed cylinder at Reynolds numbers up to 12,000,000 based on body length. The results show that cooling the cone-cylinder model to a wall-to-free-stream static-temperature ratio of approximately 1.4 increased the transition Reynolds number from a value of about 2,000,000 at equilibrium to 10,600,000. For temperature ratios less than 1.4, the boundary-layer flow was laminar over the entire model. The rapid increase of transition Reynolds number with small reductions in temeprature ratio near 1.4 indicated that temperature ratios slight lower may result in a laminar boundary layer for very high Reynolds numbers. For the parabolic-nosed body, the transition Reynolds number was about twice that of the cone-cylinder model over the temperature range investigated.
Heat Transfer and Boundary-layer Transition on Two Blunt Bodies at Mach Number 3.12
Author: N. S. Diaconis
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 31
Book Description
Local heat-transfer parameters were measured on a hemisphere-cone-cylinder and on a 120 degree-included-angle cone-cylinder at a free-stream Mach number of 3.12 and at free-stream unit Reynolds numbers as high as 1,292.000 per inch. Heat-transfer data are presented for the case of wall temperature approximat&ly equal to free-stream static temperature.
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 31
Book Description
Local heat-transfer parameters were measured on a hemisphere-cone-cylinder and on a 120 degree-included-angle cone-cylinder at a free-stream Mach number of 3.12 and at free-stream unit Reynolds numbers as high as 1,292.000 per inch. Heat-transfer data are presented for the case of wall temperature approximat&ly equal to free-stream static temperature.
Correlation of Boundary-layer Transition Results on Highly Cooled Blunt Bodies
Author: Richard J. Wisniewski
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Book Description
AN EXTENSION OF THE EFFECTS OF HEAT TRANSFER ON BOUNDARY-LAYER TRANSITION ON A PARABOLIC BODY OF REVOLUTION (NACA RM-10) AT A MACH NUMBER OF 1.61
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 25
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 25
Book Description
Experimental Investigation of the Turbulent Boundary Layer at a Mach Number of 6 with Heat Transfer at High Reynolds Numbers
Author: Richard D. Samuels
Publisher:
ISBN:
Category : Skim friction (Aerodynamics)
Languages : en
Pages : 82
Book Description
Publisher:
ISBN:
Category : Skim friction (Aerodynamics)
Languages : en
Pages : 82
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 792
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 792
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Boundary-layer Transition Under Hypersonic Conditions
Author: J. Leith Potter
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 128
Book Description
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 128
Book Description
An Investigation of the Effects of Heat Transfer on Boundary-layer Transition of a Parabilic Body of Revolution (NACA RM-10) at a Mach Number of 1.61
Author: K.R. Czarnecki
Publisher:
ISBN:
Category :
Languages : en
Pages : 11
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 11
Book Description
Applied Mechanics Reviews
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 770
Book Description
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 770
Book Description
Effects of Fixing Boundary-layer Transition for a Swept- and a Triangular-wing and Body Combination at Mach Numbers from 0.60 to 1.40
Author: Louis S. Stivers
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
Book Description