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Author : K. R. Czarnecki
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.:/5 (31 download)
Download or read book Effects of Cone Angel, Mach Number, and Nose Blunting on Transition at Supersonic Speeds written by K. R. Czarnecki and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : E. R. Van Driest
Publisher :
ISBN 13 :
Total Pages : 108 pages
Book Rating : 4.3/5 (91 download)
Download or read book Boundary Layer Transition at Supersonic Speeds written by E. R. Van Driest and published by . This book was released on 1961 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experiments carried out in the 12-inch supersonic wind tunnel to investigate the effect of three dimensional roughness elements (spheres) on boundary-layer transition on a 10-degree (apex angle) cone without heat transfer are described. The local Mach number for these tests was 2.71. The data show clearly that the minimum (effective) size of trip required to bring transition to its lowest Reynolds number varies power of the distance from the apex of the cone to the trip. Use of available data at other Mach numbers indicates that the Mach number influence for effective tripping is taken into account by a simple expression. Some remarks concerning the roughness variation for transition on a blunt body are made. Finally, a general criterion is introduced which gives insight to the transition phenomenon and anticipates effects of external and internal disturbances, Mach number transfer.
Author : P. Calvin Stainback
Publisher :
ISBN 13 :
Total Pages : 82 pages
Book Rating : 4.:/5 (31 download)
Download or read book Effect of Unit Reynolds Number, Nose Bluntness, Angle of Attack, and Roughness on Transition on a 5° Half-angle Cone at Mach 8 written by P. Calvin Stainback and published by . This book was released on 1969 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : James E. Brunk
Publisher :
ISBN 13 :
Total Pages : 168 pages
Book Rating : 4.3/5 (91 download)
Download or read book Free Flight Hypersonic Heat Transfer and Boundary Layer Transition Studies written by James E. Brunk and published by . This book was released on 1961 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two HTV-1 Hypersonic Test Vehicles, Rounds A-40 and A-41, were flown at Holloman AFB in October 1959, with blunted and sharp 20 degree half angle nose cones, respectively. Round A-40 also incorporated nose cone incidence and a pitch disturber rocket. A maximum flight velociety of 5800 feet per second was attained, corresponding to a local shap cone Mach number and unit Reynolds number of 3.4 and 50 x 10(6) per foot respectively. Fligh dynamics data for the second stage of Round A-40 were obtained from analyses of the vector angle of attack history. The measured maximum trim angle of attack (1.5 degrees) agreed closely with the predicted trim based on an elastic structure and a nose cone incidence of 0.36 degrees. Surface temperatures and aerodynamic heating rates were obtained for one station and three radial positions on the conical portion of the blunted nose cone (Round A-40) and at 3 stations on each of the two longitudinal rays on the sharp cone (Round A-41). In addition, the temperature and heating rates were determined on the cylindrical portion of the Round A-41 payload and on the base of on Stage II fin for both vehicles. The maximum heating rate for the sharp cone was about 30 percent greater for the blunt cone as a result of higher local Mach numbers and Reynolds numbers on the sharp cone. Correlation of the blunted cone circumferential heating rates with the measured angle of attack showed that only a small increase in heating rate (less than about 5 percent increase from the zero angle of attack heating rate) occurs on the windward ray for turbulent heating conditions. The measured decrease in Stanton mumber with increasing Reynolds number (running length) for the sharp cone was found to be in close agreement with turbulent flow theory. Boundary layer transition reversal from turbulent to laminar flow was experienced on both the sharp and blunted tip cones. Transition reversal for the sharp cone, which had almost twice the local Mach number of the blunted cone, was found to occur at an enthalpy ratio, hw/hr, 30 percent greater than for the blunted cone. For both cones turbulent flow occurred within the Mach number and enthalpy region for complete stability of two dimensional disturbance as defined by Dunn and Lin. The possible effects of surface roughness in producing the observed transition reversal are discussed.
Author : K. R. Czarnecki
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.3/5 (91 download)
Download or read book Factors Affecting Transition at Supersonic Speeds written by K. R. Czarnecki and published by . This book was released on 1953 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper surveys the available material and summarizes what is known to date about boundary-layer transition at supersonic speeds. Variables studied include Mach number, Reynolds number, pressure gradients, heat transfer, surface roughness, and angle of attack. The discussion is limited to bodies of revolution because similar reliable data for wings is lacking.
Author : James M. Cubbage
Publisher :
ISBN 13 :
Total Pages : 66 pages
Book Rating : 4.:/5 (31 download)
Download or read book Effect of Nose Bluntness and Controlled Roughness on the Flow on Two Hypersonic Inlet Center Bodies Without Cowling at Mach 5.98 written by James M. Cubbage and published by . This book was released on 1965 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Charles B. Rumsey
Publisher :
ISBN 13 :
Total Pages : 42 pages
Book Rating : 4.3/5 (126 download)
Download or read book Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10° 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 1956 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Aerodynamic heat-transfer measurements were at six stations on the 40-inch-long 10° total-angle conical nose of a rocket-propelled model which was flight tested at Mach numbers up to 5.9. The range of local Reynolds number was from 6.6 x 106 to 55.2 x 106. Laminar, transitional, and turbulent heat-transfer coefficients were measured, and, in general, the laminar and turbulent measurements were in good agreement with theory for cones. Experimental transition Reynolds numbers varied from less than 8.5 x 106 to 19.4 x 106. At a relatively constant ratio of wall temperature to local static temperature near 1.2, the transition Reynolds number increased from 9.2 x 106 to 19.4 x 106 as Mach number increased from 1.57 to 3.38. At Mach numbers near 3.7, the transition Reynolds number decreased as the skin temperature increased toward adiabatic wall temperatures.
Author : David S. Shaw
Publisher :
ISBN 13 :
Total Pages : 88 pages
Book Rating : 4.:/5 (31 download)
Download or read book Effects of Nose Bluntness, Fineness Ratio, Cone Angle, and Model Base on the Static Aerodynamic Characteristics of Blunt Bodies at Mach Numbers of 1.57, 1.80, and 2.16 and Angles of Attack Up to 180 ̊ written by David S. Shaw and published by . This book was released on 1963 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Mary W. Jackson
Publisher :
ISBN 13 :
Total Pages : 26 pages
Book Rating : 4.:/5 (31 download)
Download or read book Boundary-layer Transition on a Group of Blunt Nose Shapes at a Mach Number of 2.20 written by Mary W. Jackson and published by . This book was released on 1961 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Nickolai Charczenko
Publisher :
ISBN 13 :
Total Pages : 30 pages
Book Rating : 4.:/5 (31 download)
Download or read book Aerodynamic Characteristics of Towed Cones Used as Decelerators at Mach Numbers from 1.57 to 4.65 written by Nickolai Charczenko and published by . This book was released on 1962 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Towed and sting-supported cones were tested in the wake of various payloads at supersonic speeds to determine their drag and stability characteristics. The investigation extended over a Mach number range from 1.57 to 4.65 and included such variables as Reynolds number, cone angle, ratio of cone base diameter to payload base diameter, and trailing distance. Cones towed in the wake of a symmetrical payload at supersonic speeds, in general, had good drag and stability characteristics if towed in the supersonic flow region. A cone with an included angle between 80 and 90 degrees gave 2 maximum drag while still maintaining stability. In order to minimize wake effects, the ratio of cone base diameter to payload base diameter should be at least one and preferably around three. A trailing distance of three times the payload base diameter, in most cases, is of sufficient length to avoid low drag and instability of the decelerator. (Author).
Author : William A. Cassels
Publisher :
ISBN 13 :
Total Pages : 76 pages
Book Rating : 4.:/5 (31 download)
Download or read book Boundary-layer Transition Study of Several Pointed Bodies of Revolution at Supersonic Speeds written by William A. Cassels and published by . This book was released on 1970 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary-layer transition by the sublimation and impact-pressure techniques and force tests have been performed on three Haack-Adams bodies of revolution of fineness ratios 7, 10, and 13 at zero angle of attack for free-stream Mach numbers of 2.00, 2.75, and 4.63 and a range of Reynolds numbers based on model length of 6 to 15 X 10(to the 6 power) with and without a roughness strip. The grit method of inducing turbulence was found to provide for a nearly complete turbulent flow over the models at the lower Mach numbers and higher Reynolds numbers considered in this study while the amount of trip drag was less than 8 percent of the model drag with transition fixed. A method of interpreting sublimation data was discussed and used and the results compared well with the impact-pressure results.
Author : Simon C. Sommer
Publisher :
ISBN 13 :
Total Pages : 26 pages
Book Rating : 4.3/5 (126 download)
Download or read book The Effect of Bluntness on the Drag of Spherical-tipped Truncated Cones of Fineness Ratio 3 at Mach Numbers 1.2 to 7.4 written by Simon C. Sommer and published by . This book was released on 1952 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The drag of spherically blunted conical models of fineness ratio 3 was investigated in the Ames super-sonic free-flight wind tunnel at Mach numbers from 1.2 to 7.4 in the Reynolds number range from 1.0 x 106 to 7.5 x 106. The models tested had bluntness ratios of nose diameter to base diameter from 0 to 0.50. The use of small amounts of bluntness for minimizing drag and the drag penalties associated with large bluntnesses are discussed.
Author : J. Leith Potter
Publisher :
ISBN 13 :
Total Pages : 166 pages
Book Rating : 4.3/5 (91 download)
Download or read book Effects of Unit Reynolds Number, Nose Bluntness, and Roughness on Boundary Layer Transition written by J. Leith Potter and published by . This book was released on 1960 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt: Condtions encountered in the high Mach number flow regime are show to profoundly affect the longitudinal extent of the boundary layer from beginning to end of transition, the distribution of fluctuation energy in the laminar layer, and effectiveness of surface roughness in promoting transition. A critical layer of intense local energy fluctuations was found at all Mach numbers studied. The existence of such a critical layer is predicted by stability theory. Hot-wire surveys of the laminar, transitional, and turbulent boundary layers are presented to illustrate the critical layer in laminar flow and subsequent development into the transition process. The relation between boundary layer transition on flat plates and cones in supersonic flow is explored and a process for correcting data to account for leading edge bluntness is devised. On the basis of a comparison of data corrected for the effects of leading edge geometry, it is shown that the Reynolds umber of transition on a cone is three times that on a vanishingly thin flate plate. Close agreement between data from various wind tunnels is demonstrated. Study of the effect of finite leading edges yields significant illustrations of the influence of unit Reynolds number on boundary layer transition. A correlation of the effects of surface roughness on transition is achieved. This treatment includes two- and three-dimensional roughness in both subsonic and supersonic streams. At this time only zero pressure gradients have been studied. The entire range of movement of transition from its position with no roughness up to its reaching the roughness element is describable by the procedure give. Examples of application of the correlation results show excellent agreement with experimental data from a variety of sources. Implications concerning tripping hypersonic boundary layers are discussed.
Author : J. Leith Potter
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.3/5 (91 download)
Download or read book Boundary-layer Transition on Cones Near Mach One in an Aeroballistic Range written by J. Leith Potter and published by . This book was released on 1975 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: The feasibility of determining Reynolds numbers of boundary layer transition on sharp, 10-deg, semiangle cones at slightly supersonic free-stream Mach numbers, 1.04 = or
Author :
Publisher :
ISBN 13 :
Total Pages : 1298 pages
Book Rating : 4.3/5 (91 download)
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1968-03 with total page 1298 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Charles F. Merlet
Publisher :
ISBN 13 :
Total Pages : 28 pages
Book Rating : 4.:/5 (31 download)
Download or read book Supersonic Free-flight Measurements of Heat Transfer and Transition on a 10° Cone Having a Low Temperature Ratio written by Charles F. Merlet and published by . This book was released on 1961 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Author : John O. Reller (Jr.)
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.3/5 (91 download)
Download or read book Heat Transfer to Blunt Nose Shapes with Laminar Boundary Layers at High Supersonic Speeds written by John O. Reller (Jr.) and published by . This book was released on 1957 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
