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Preliminary Results From A Free Flight Investigation Of Boundary Layer Transition And Heat Transfer On A Highly Polished 8 Inch Diameter Hemisphere Cylinder At Mach Numbers Up To 3 And Reynolds Numbers Based On A Length Of 1 Foot Up To 177 X 106
Download Preliminary Results From A Free Flight Investigation Of Boundary Layer Transition And Heat Transfer On A Highly Polished 8 Inch Diameter Hemisphere Cylinder At Mach Numbers Up To 3 And Reynolds Numbers Based On A Length Of 1 Foot Up To 177 X 106 full books in PDF, epub, and Kindle. Read online Preliminary Results From A Free Flight Investigation Of Boundary Layer Transition And Heat Transfer On A Highly Polished 8 Inch Diameter Hemisphere Cylinder At Mach Numbers Up To 3 And Reynolds Numbers Based On A Length Of 1 Foot Up To 177 X 106 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Preliminary Results from a Free-flight Investigation of Boundary-layer Transition and Heat Transfer on a Highly Polished 8-inch-diameter Hemisphere-cylinder at Mach Numbers Up to 3 and Reynolds Numbers Based on a Length of 1 Foot Up to 17.7 X 106 by : James R. Hall
Download or read book Preliminary Results from a Free-flight Investigation of Boundary-layer Transition and Heat Transfer on a Highly Polished 8-inch-diameter Hemisphere-cylinder at Mach Numbers Up to 3 and Reynolds Numbers Based on a Length of 1 Foot Up to 17.7 X 106 written by James R. Hall and published by . This book was released on 1957 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer and Boundary-layer Transition on a Highly Polished Hemisphere-cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X 106 by : James J. Buglia
Download or read book Heat Transfer and Boundary-layer Transition on a Highly Polished Hemisphere-cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X 106 written by James J. Buglia and published by . This book was released on 1961 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A highly polished hemisphere-cone having a ratio of nose radius to base radius of 0.74 and a half-angle of 14.5 was flight tested at Mach numbers up to 4.70. Temperature and pressure data were obtained at Mach numbers up to 3.14 and a free-stream Reynolds number of 24 x 106 based on body diameter. The nose of the model had a surface roughness of 2 to 5 microinches as measured with an interferometer. The measured Stanton numbers were in good agreement with theory. Transition Reynolds numbers based on the laminar boundary-layer momentum thickness at transition ranged from 2,190 to 794. Comparison with results from previous tests of blunt shapes having a surface roughness of 20 to 40 microinches showed that the high degree of polish was instrumental in delaying the transition from laminar to turbulent flow.
Book Synopsis Heat Transfer and Boundary-layer Transition on a Highly Polished Hemisphere-cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X (10)6 by : James J. Buglia
Download or read book Heat Transfer and Boundary-layer Transition on a Highly Polished Hemisphere-cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X (10)6 written by James J. Buglia and published by . This book was released on 1957 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Heat Transfer and Boundary-layer Transition on an 8-inch-diameter Hemisphere-cylinder in Free Flight for a Mach Number Range of 2.00 to 3.88 by : Benjamine J. Garland
Download or read book Measurements of Heat Transfer and Boundary-layer Transition on an 8-inch-diameter Hemisphere-cylinder in Free Flight for a Mach Number Range of 2.00 to 3.88 written by Benjamine J. Garland and published by . This book was released on 1957 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Influence of Low Wall Temperature on Boundary-layer Transition and Local Heat Transfer on 2-inch-diameter Hemispheres at a Mach Number of 4.95 and a Reynolds Number Per Foot of 73.2 X 106 by : Morton Cooper
Download or read book The Influence of Low Wall Temperature on Boundary-layer Transition and Local Heat Transfer on 2-inch-diameter Hemispheres at a Mach Number of 4.95 and a Reynolds Number Per Foot of 73.2 X 106 written by Morton Cooper and published by . This book was released on 1960 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer Measurements Boundary-layer Transition, and the Effects of Superpolishing Observed in Two Free-flight Tests Up to Mach Number 5.0 at Reynolds Number Per Foot Up to 8 X 106 by : James Rudyard Hall
Download or read book Heat-transfer Measurements Boundary-layer Transition, and the Effects of Superpolishing Observed in Two Free-flight Tests Up to Mach Number 5.0 at Reynolds Number Per Foot Up to 8 X 106 written by James Rudyard Hall and published by . This book was released on 1961 with total page 186 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Examination of the Existing Data on the Heat Transfer of Turbulent Boundary Layers at Supersonic Speeds from the Point of View of Reynolds Analogy by : Alvin Seiff
Download or read book Examination of the Existing Data on the Heat Transfer of Turbulent Boundary Layers at Supersonic Speeds from the Point of View of Reynolds Analogy written by Alvin Seiff and published by . This book was released on 1954 with total page 654 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer data from four wind-tunnel experiments and two free-flight experiments with turbulent boundary layers have been examined to see whether or not they are well represented by the Reynolds analogy or a modification thereof. The heat-transfer results are put into the form of dimensionless Stanton numbers based on fluid properties at the outer edge of the boundary layer and are compared with skin-friction coefficients for the same Mach numbers and wall to free-stream temperature ratios as obtained from an interpolation of the existing skin-friction data. The effective Reynolds number is taken to be the length Reynolds number measured from the effective turbulent origin, a position which differs importantly from the leading edge of the test surface in some cases.
Book Synopsis Local Aerodynamic Heat Transfer and Boundary-layer Transition on Roughened Sphere-ellipsoid Bodies at Mach Number 3.0 by : William D. Deveikis
Download or read book Local Aerodynamic Heat Transfer and Boundary-layer Transition on Roughened Sphere-ellipsoid Bodies at Mach Number 3.0 written by William D. Deveikis and published by . This book was released on 1961 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 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 by :
Download or read book 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 written by and published by . This book was released on 1960 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7 by : Charles R. Rumsey
Download or read book Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7 written by Charles R. Rumsey and published by . This book was released on 1961 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer in Turbulent Separated Regions at a Mach Number of 1.8 by : Benjamine J. Garland
Download or read book Measurements of Aerodynamic Heat Transfer in Turbulent Separated Regions at a Mach Number of 1.8 written by Benjamine J. Garland and published by . This book was released on 1958 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer and Pressure Measurements on a Flat-plate Surface and Heat-transfer Measurements on Attached Protuberances in a Supersonic Turbulent Boundary Layer at Mach Numbers of 2.65, 3.51, and 4.44 by : Paige B. Burbank
Download or read book Heat-transfer and Pressure Measurements on a Flat-plate Surface and Heat-transfer Measurements on Attached Protuberances in a Supersonic Turbulent Boundary Layer at Mach Numbers of 2.65, 3.51, and 4.44 written by Paige B. Burbank and published by . This book was released on 1962 with total page 430 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Turbulent-boundary-layer Heat-transfer and Transition Measurements with Surface Cooling at Mach 6 by : Aubrey M. Cary
Download or read book Turbulent-boundary-layer Heat-transfer and Transition Measurements with Surface Cooling at Mach 6 written by Aubrey M. Cary and published by . This book was released on 1970 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Interference Heating on a Swept Cylinder in Region of Intersection with a Wedge at Mach Number 8 by : Dennis M. Bushnell
Download or read book Interference Heating on a Swept Cylinder in Region of Intersection with a Wedge at Mach Number 8 written by Dennis M. Bushnell and published by . This book was released on 1965 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 by : Charles B. Rumsey
Download or read book Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 written by Charles B. Rumsey and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07 by : Robert L. O'Neal
Download or read book Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07 written by Robert L. O'Neal and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
