Author: Floyd G. Howard
Publisher:
ISBN:
Category :
Languages : en
Pages : 48
Book Description
Heat Transfer on Unswept and 38 Degrees Swept Cylindrically Blunted Wedge Fins in Free Flight to Mach Number 4.11
Author: Floyd G. Howard
Publisher:
ISBN:
Category :
Languages : en
Pages : 48
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 48
Book Description
Heat Transfer on Unswept and 38 ̊swept Cylindrically Blunted Wedge Fins in Free Flight to Mach Number 4.11
Author: Floyd G. Howard
Publisher:
ISBN:
Category : Fins (Anatomy)
Languages : en
Pages : 56
Book Description
Publisher:
ISBN:
Category : Fins (Anatomy)
Languages : en
Pages : 56
Book Description
Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07
Author: Robert L. O'Neal
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 44
Book Description
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 44
Book Description
Heat Transfer to 0 Degree and 75 Degrees Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07
Author: ROBERT L. O'NEAL
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
A flight investigation of a rocket-powered model was conducted to study the heat transfer to wing leading edges in the vicinity of their juncture with a cylindrical body. Heat-transfer data were obtained on leading edges of 3/4-inch diameter at sweep angles of 0 and 75 degrees, Mach numbers from 1.90 to 3.07, and Reynolds numbers based on leading-edge diameter from 8.05 to 11.80 times 10 to the 5th power. The measured heating rates of both the 0 and 75 degrees swept leading edges were of the magnitude predicted by turbulent theory rather than by laminar theory. It is believed that the high level of heating observed on the leading edges was due to the influence of conditions existing in the turbulent boundary layer of the body. Comparison of the average measured heating on the cylindrical portions of both the swept and unswept leading edges indicates that the heating of the unswept segment was generally about twice that of the swept segment. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
A flight investigation of a rocket-powered model was conducted to study the heat transfer to wing leading edges in the vicinity of their juncture with a cylindrical body. Heat-transfer data were obtained on leading edges of 3/4-inch diameter at sweep angles of 0 and 75 degrees, Mach numbers from 1.90 to 3.07, and Reynolds numbers based on leading-edge diameter from 8.05 to 11.80 times 10 to the 5th power. The measured heating rates of both the 0 and 75 degrees swept leading edges were of the magnitude predicted by turbulent theory rather than by laminar theory. It is believed that the high level of heating observed on the leading edges was due to the influence of conditions existing in the turbulent boundary layer of the body. Comparison of the average measured heating on the cylindrical portions of both the swept and unswept leading edges indicates that the heating of the unswept segment was generally about twice that of the swept segment. (Author).
Heat Transfer to 36.75 and 45 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.70 to 2.99 and From 2.50 to 4.05
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 42
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 42
Book Description
Investigation of Heat Transfer on a Finned Body in the Region of Fin-body Interference in Free Flight at Mach Numbers Up to 11
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 38
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 38
Book Description
Some Effects of Heat Transfer at Mach Number 2.0 at Stagnation Temperatures Between 2,310° and 3,500° R on a Magnesium Fin with Several Leading-edge Modifications
Author: William M. Bland
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Book Description
Abstract: Four models of a thin magnesium fin, with the leading edge swept back 35°, have been tested in the preflight high-temperature jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va., at a Mach number of 2.0 for various stagnation temperatures between 2,310° and 3,500° R. This exploratory investigation was made to determine some effects of aerodynamic heating at high stagnation temperatures on the leading edges of fins and to determine the relative effectiveness of several leading-edge protective schemes.
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Book Description
Abstract: Four models of a thin magnesium fin, with the leading edge swept back 35°, have been tested in the preflight high-temperature jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va., at a Mach number of 2.0 for various stagnation temperatures between 2,310° and 3,500° R. This exploratory investigation was made to determine some effects of aerodynamic heating at high stagnation temperatures on the leading edges of fins and to determine the relative effectiveness of several leading-edge protective schemes.
Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07
Author: Robert L. O'Neal
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 0
Book Description
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 0
Book Description
Heat-transfer Measurements on a Flat Plate and Attached Fins at Mach Numbers of 3.51 and 4.44
Author: Earl A. Price
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 46
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 46
Book Description
Heat Transfer to 36.75° and 45° Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.70 to 2.99 and from 2.50 to 4.05
Author: Robert L. O'Neal
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 37
Book Description
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 37
Book Description