Author: Paul W. HowardPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 56
Book Description
Effect of Fabrication-type Surface Roughness on Transition on Ogive-cylinder Models at Mach Number of 1.61 and 2.01
Author: Paul W. HowardPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 56
Book Description
Effect of Fabrication-type Surface Roughness on Transition on Ogive-cylinder Models at Mach Number of 1.61 and 2.01
Author: Paul W. HowardPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 48
Book Description
Effect of Fabrication-type Surface Roughness on Transition on Ogive-cylinder Models at Mach Numbers of 1.61 and 2.01
Author: Paul W. HowardBoundary-layer Velocity Profiles and Skin Friction Due to Surface Roughness on an Ogive Cylinder at Mach Numbers of 1.61 and 2.01
Author: K. R. CzarneckiPublisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 54
Book Description
Effect of Mach Number on Boundary-layer Transition in the Presence of Pressure Rise and Surface Roughness on an Ogive-cylinder Body with Cold Wall Conditions
Author: Robert J. CarrosPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 30
Book Description
The effect of Mach number variation from 1.8 to 7.4 on boundary-layer transition was investigated on a slender fin-stabilized ogive-cylinder body in free flight at a constant length Reynolds number of 13.8 million. The wall to free-stream temperature ratio was constant at a value of 1.0 below Mach number 4.5 and at a value of 1.8 above Mach number 4.5. Results of the test showed that increasing Mach number had a very favorable effect of increasing the extent of the laminar boundary layer for a given surface roughness. The transition data, when plotted as a function of a factor indicative of heat transfer, showed that heat transfer was possibly responsible for a good deal of the increase in transition Reynolds number with Mach number.
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Author: Investigation of Effects of Distributed Surface Roughness on a Turbulent Boundary Layer Over a Body of Revolution at a Mach Number of 2.01
Author: John R. SevierPublisher:
ISBN:
Category : Body of revolution
Languages : en
Pages : 31
Book Description
An investigation has been made of the effects of distributed surface roughness, consisting of lathe-tool marks, on the skin friction of a turbulent boundary layer over a body of revolution at a Mach number of 2.01. The investigation was made on three ogive-cylinders at zero angle of attack over a surface-roughness range from 23 to 480 microinches root mean square and for a Reynolds number range based on body length from 4,000,000 to 30,000,000.
An Experimental Investigation of the Effect of Surface Roughness of the Drag of a Cone-cylinder Model at a Mach Number of 2.48
Author: John Henry Terry WadePublisher:
ISBN:
Category :
Languages : en
Pages : 31
Book Description
Investigation of Distributed Surface Roughness on a Body of Revolution at a Mach Number of 1.61
Author: K. R. CzarneckiPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 35
Book Description
An investigation has been made of the effects of distributed surface roughness, consisting of lathe-tool marks, on the skin-friction drag of a body of revolution at a Mach number of 1.61. The tests were made on ogive-cylinders at zero angle of attack over a roughness range from 23 to 480 microinches root mean square and over a Reynolds number range from 2,500,000 to 37,000,000.
Aircraft Excrescence Drag
Author: Alec David YoungPublisher:
ISBN: 9789283513926
Category : Boundary layer
Languages : en
Pages : 159
Book Description