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Pressure Distribution And Pressure Drag For A Hemispherical Nose At Mach Numbers 205 254 And 204
Download Pressure Distribution And Pressure Drag For A Hemispherical Nose At Mach Numbers 205 254 And 204 full books in PDF, epub, and Kindle. Read online Pressure Distribution And Pressure Drag For A Hemispherical Nose At Mach Numbers 205 254 And 204 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Pressure Distribution and Pressure Drag for a Hemispherical Nose at Mach Numbers 2.05, 2.54, and 2.04 by : Leo T. Chauvin
Download or read book Pressure Distribution and Pressure Drag for a Hemispherical Nose at Mach Numbers 2.05, 2.54, and 2.04 written by Leo T. Chauvin and published by . This book was released on 1952 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: an experimental investigation of the pressure distributions on a hemispherical nose 3.98 inches in diameter, mounted on a cylindrical support, has been made at Mach numbers of 2.05, 2.54 and 3.04 and for Reynolds numbers of 4.44 x 106, 4.57 x 106, and 4.16 x 106, respectively. The Reynolds number was based on body diameter and free-stream conditions. Pressure-drag coefficients were calculated and good agreement was obtained between these tests and other investigations.
Book Synopsis An Investigation of Several NACA 1-series Nose Inlets with and Without Protruding Central Bodies at High-subsonic Mach Numbers and at a Mach Number of 1.2 by : Robert E. Pendley
Download or read book An Investigation of Several NACA 1-series Nose Inlets with and Without Protruding Central Bodies at High-subsonic Mach Numbers and at a Mach Number of 1.2 written by Robert E. Pendley and published by . This book was released on 1950 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of three NACA 1-series nose inlets, two of which were fitted with protruded central bodies, was conducted in the Langley 8-foot high-speed tunnel. An elliptical-nose body, which had a critical Mach number approximately equal to that of one of the nose inlets, was also tested. Tests were made near zero angle of attack for a Mach number range from 0.4 to 0.925 and for the supersonic Mach number of 1.2. The inlet-velocity-ratio range extended from zero to a maximum value of 1.34. Measurements included pressure distribution, external drag, and total-pressure loss of the internal flow near the inlet. Drag was not measured for the tests at the supersonic Mach number.
Book Synopsis Investigation of the Flow Over a Spiked-nose Hemisphere-cylinder at a Mach Number of 6.8 by : Davis H. Crawford
Download or read book Investigation of the Flow Over a Spiked-nose Hemisphere-cylinder at a Mach Number of 6.8 written by Davis H. Crawford and published by . This book was released on 1959 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1.59 to 1.99 by : L. J. Obery
Download or read book Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1.59 to 1.99 written by L. J. Obery and published by . This book was released on 1951 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation to determine the external and internal flow characteristics of a typical ram-jet-inlet configuration of an external-compression type utilizing an isentropic spike and a subsonic diffuser was conducted in the NACA Lewis 8- by 6-foot supersonic wind tunnel. The model was investigated of a range of mass-flow ratios at angles of attack up to 10 degrees, free-stream Mach numbers of 1.59, 1.79, and 1.99, and a Reynolds number of approximately 2,400,000 based on inlet diameter.
Book Synopsis Reynolds Number Effects on the Induced Pressures of Cylindrical Bodies with Different Nose Shapes and Nose Drag Coefficients in Helium at a Mach Number of 24 by : Richard D. Wagner (Jr.)
Download or read book Reynolds Number Effects on the Induced Pressures of Cylindrical Bodies with Different Nose Shapes and Nose Drag Coefficients in Helium at a Mach Number of 24 written by Richard D. Wagner (Jr.) and published by . This book was released on 1963 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Exact inviscid pressure distributions and shock shapes, obtained by the method of characteristics, are compared with experimental data. The results indicate a strong dependence of induced pressures upon Reynolds number, especially in the region immediately downstream of the nose-cylinder junction. The measured shock shapes revealed no discernible effect of Reynolds number variations.
Book Synopsis Local Pressure Distribution on a Blunt Delta Wing for Angles of Attack Up to 35 Degrees at Mach Numbers of 3.4 and 4.7 by : Marvin Kussoy
Download or read book Local Pressure Distribution on a Blunt Delta Wing for Angles of Attack Up to 35 Degrees at Mach Numbers of 3.4 and 4.7 written by Marvin Kussoy and published by . This book was released on 1962 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9 by : Harold Mirels
Download or read book Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9 written by Harold Mirels and published by . This book was released on 1949 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic trailing edge. The wing section was a symmetrical wedge of 5 degrees 43 minutes total included angle in the free-stream direction. The investigation was conducted over a range of angles of attack from -10 to 10 degrees at a Reynolds number of 3,400,000 per foot.
Book Synopsis Experimental Determination of the Pressure Distribution on a Rectangular Wing Oscillating in the First Bending Mode for Mach Numbers from 0.24 to 1.30 by : Henry C. Lessing
Download or read book Experimental Determination of the Pressure Distribution on a Rectangular Wing Oscillating in the First Bending Mode for Mach Numbers from 0.24 to 1.30 written by Henry C. Lessing and published by . This book was released on 1960 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flow-field Study about a Hemisphere-cylinder in the Transonic and Low Supersonic Mach Number Range by : T. Hsieh
Download or read book Flow-field Study about a Hemisphere-cylinder in the Transonic and Low Supersonic Mach Number Range written by T. Hsieh and published by . This book was released on 1975 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: A theoretical and experimental study has been conducted of a flow field about a hemisphere-cylinder at zero incidence in the transonic and low supersonic Mach number range (M = 0.7 to 2.0). For M less than or equal to 1, the method used is a combination of the time-dependent solution for the hemispherical nose portion and the method-of-characteristics solution for the cylindrical body portion. The relaxation method has been used for Mach numbers from 0.7 to 1.3. Experimental results indicate a strong interaction of the shock and boundary layer for M approximately equal to 0.8.
Book Synopsis Experimental Pressure Distributions Over Two Wing-body Combinations at Mach Number 1.9 by : Barry Moskowitz
Download or read book Experimental Pressure Distributions Over Two Wing-body Combinations at Mach Number 1.9 written by Barry Moskowitz and published by . This book was released on 1951 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Pressure distributions on two wing-body combinations were obtained at Mach number of 1.9 to investigate wing-body interference. A rectangular wing, a triangular wing, and a cylindrical body having an ogive nose were investigated alone and in combination. Pressure distributions over the wing body combination compared favorable with theoretical calculations based primarily on a generalization of the method of Nielsen and Matteson, except at the root section of wings where boundary layer of body modified the flow.
Book Synopsis Investigation of the Drag of Blunt-nosed Bodies of Revolution in Free Flight at Mach Numbers from 0.6 to 2.3 by : Harvey A. Wallskog
Download or read book Investigation of the Drag of Blunt-nosed Bodies of Revolution in Free Flight at Mach Numbers from 0.6 to 2.3 written by Harvey A. Wallskog and published by . This book was released on 1953 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Induced Pressures on Cylindrical Rods with Various Nose Drags and Nose Shapes at Mach Numbers of 17 and 21 by : Robert D. Witcofski
Download or read book Induced Pressures on Cylindrical Rods with Various Nose Drags and Nose Shapes at Mach Numbers of 17 and 21 written by Robert D. Witcofski and published by . This book was released on 1962 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Compressibility and Large Angles of Yaw on Pressure Indicated by a Total-pressure Tube by : Milton D. Humphreys
Download or read book Effects of Compressibility and Large Angles of Yaw on Pressure Indicated by a Total-pressure Tube written by Milton D. Humphreys and published by . This book was released on 1945 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: The effects of compressibility and angle of yaw on the pressure measured by a round-nose and a flat-nose total-pressure tube have been investigated. The tests were conducted in the Langley rectangular high-speed tunnel at Mach numbers from 0.3 to 0.9 for angles of yaw from 0° to 180°. The results indicated that no error was incurred in the measurement of total pressure by either tube for angles of yaw from 0° to 10° in the Mach number range investigated. At constant Mach numbers, the round-nose tube had a linear variation of total-pressure error with angle of yaw at angles ranging from 50° to 70°. This characteristic is desirable in yaw heads of the Y-type. The flat-nose tube had a nonlinear variation of total-pressure error with angle of yaw in this range.
Book Synopsis A Method for Designing Low-drag Nose-inlet-body Combinations for Operation at Moderate Supersonic Speeds by : Robert R. Howell
Download or read book A Method for Designing Low-drag Nose-inlet-body Combinations for Operation at Moderate Supersonic Speeds written by Robert R. Howell and published by . This book was released on 1954 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Investigation at Mach Numbers from 0.6 to 1.7 to Determine Drag and Base Pressures on a Blunt-trailing-edge Airfoil and Drag of Diamond and Circular-arc Airfoils at Zero Lift by : John D. Morrow
Download or read book Flight Investigation at Mach Numbers from 0.6 to 1.7 to Determine Drag and Base Pressures on a Blunt-trailing-edge Airfoil and Drag of Diamond and Circular-arc Airfoils at Zero Lift written by John D. Morrow and published by . This book was released on 1950 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models having rectangular 6-percent-thick wings are presented for a Mach number range of 0.6 to 1.7. Wings of aspect ratio 2.7 having diamond, circular-arc, and blunt-trailing edge airfoil sections were tested. Pressures were measured on the base of the blunt-trailing-edge airfoil which had a rectangular section with a 40-percent-chord beveled leading edge. Although the blunt-trailing-edge airfoil had high drag throughout the Mach number range investigated, because of high base suction pressures, it is believed that the data presented can be used in the design of more nearly optimum blunt-base airfoils. Of the airfoils tested the circular-arc section had lowest drag at high-subsonic speeds, and the diamond section had lowest drag at supersonic speeds.
Book Synopsis Evaluation of Boattail Geometry and Exhaust Plume Temperature Effects on Nozzle Afterbody Drag at Transonic Mach Numbers by : L. L. Galigher
Download or read book Evaluation of Boattail Geometry and Exhaust Plume Temperature Effects on Nozzle Afterbody Drag at Transonic Mach Numbers written by L. L. Galigher and published by . This book was released on 1976 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental program was conducted to investigate the interaction effects which occur between the nozzle exhaust flow and the external flow field associated with isolated nozzle afterbody configurations at transonic Mach numbers. Pressure data were obtained from three afterbody geometries with boattail angles of 10, 15, and 25 deg at Mach numbers from 0.6 to 1.5 at zero angles of attack and sideslip. Cold (High-pressure air) and hot (Air/ethylene combustion) jet test techniques were used to simulate and duplicate, respectively, the nozzle exhaust flow for a sonic jet installation. Nozzle exhaust temperature was varied from 540 to approximately 2,900 R. The most significant results pertain to those effects on boattail pressure drag caused by exhaust plume temperature and flow asymmetry (Model support strut induced). The differences obtained in boattail pressure drag between the cold jet simulation and hot jet duplication results were significant at nozzle pressure ratios representative for turbofan and turbojet engines at subsonic Mach numbers. Adjusting the cold jet nozzle pressure ratio to correct for changes in the exhaust plume specific heat ratio with temperature did not account for the differences observed. Flow asymmetry effects were Mach number and nozzle pressure ratio dependent and increased in severity as the boattail angle was increased.
