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An Investigation Of Several Naca 1 Series Axisymmetric Inlets At Mach Numbers From 04 To 129
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Book Synopsis An Investigation of Several NACA 1-series Axisymmetric Inlets at Mach Numbers from 0.4 to 1.29 by : Richard J. Re
Download or read book An Investigation of Several NACA 1-series Axisymmetric Inlets at Mach Numbers from 0.4 to 1.29 written by Richard J. Re and published by . This book was released on 1974 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of Several NACA 1-series Axisymmetric Inlets at Mach Numbers from 0.4 to 1.29 by : Richard J. Re
Download or read book An Investigation of Several NACA 1-series Axisymmetric Inlets at Mach Numbers from 0.4 to 1.29 written by Richard J. Re and published by . This book was released on 1974 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An investigation of several NACA 1-series inlets at Mach numbers from 0.4 to 1.29 for mass-flow ratios near 1.0 by : Richard J. Re
Download or read book An investigation of several NACA 1-series inlets at Mach numbers from 0.4 to 1.29 for mass-flow ratios near 1.0 written by Richard J. Re and published by . This book was released on 1976 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Tests of a Small-scale NACA Submerged Inlet at Transonic Mach Numbers by : L. Stewart Rolls
Download or read book Tests of a Small-scale NACA Submerged Inlet at Transonic Mach Numbers written by L. Stewart Rolls and published by . This book was released on 1950 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: The pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 have been measured in the Mach number range 0.60 to 1.08 by the wing-flow method. The variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60.
Book Synopsis Performance of a Mach Number 3.0 Design Axisymmetric Double-cone External-compression Inlet in the Mach Number Range 1.97 to 0.79 by : Owen H. Davis
Download or read book Performance of a Mach Number 3.0 Design Axisymmetric Double-cone External-compression Inlet in the Mach Number Range 1.97 to 0.79 written by Owen H. Davis and published by . This book was released on 1960 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of an NACA Submerged Inlet at Mach Numbers from 1.17 to 1.99 by : Warren E. Anderson
Download or read book Investigation of an NACA Submerged Inlet at Mach Numbers from 1.17 to 1.99 written by Warren E. Anderson and published by . This book was released on 1952 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Three Mach 7 External Compression Axisymmetric Inlets from Mach 1.9 to 6.8 by :
Download or read book Investigation of Three Mach 7 External Compression Axisymmetric Inlets from Mach 1.9 to 6.8 written by and published by . This book was released on 1960 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of a Mach 5 Isentropic Spike Inlet at and Below Design Speed by : Leonard E. Stitt
Download or read book Experimental Investigation of a Mach 5 Isentropic Spike Inlet at and Below Design Speed written by Leonard E. Stitt and published by . This book was released on 1959 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Preliminary Investigation at Mach Number 1.9 of Simulated Wing-root Inlets by : Thomas G. Piercy
Download or read book Preliminary Investigation at Mach Number 1.9 of Simulated Wing-root Inlets written by Thomas G. Piercy and published by . This book was released on 1955 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to study several wing-root inlet configurations at Mach number 1.9. The inlets were of triangular shape, and external compression was provided by two-dimensional wedge surfaces. Inlets were tested alternately with straight diffusers of relatively slow diffusion rate and with curved diffusers; the curved-diffuser models simulate the ducting of proposed fighter aircraft requiring relatively short diffusion length and high rates of turning.
Book Synopsis Investigation of a Mixed Compression Axisymmetric Inlet at Mach Number 5.3 by : Eldon A. Latham
Download or read book Investigation of a Mixed Compression Axisymmetric Inlet at Mach Number 5.3 written by Eldon A. Latham and published by . This book was released on 1972 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Determination of the Drag and Pressure Recovery of an NACA 1-40-250 Nose Inlet at Mach Numbers from 0.9 to 1.8 by : R. I. Sears
Download or read book Flight Determination of the Drag and Pressure Recovery of an NACA 1-40-250 Nose Inlet at Mach Numbers from 0.9 to 1.8 written by R. I. Sears and published by . This book was released on 1951 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made with rocket-propelled models in free flight to determine the external drag and pressure recovery of the NACA 1-40-250 nose inlet at zero angle of attack. The Mach number range of the tests was from 0.9 to 1.8 and the corresponding Reynolds numbers based on body diameter varied from 4,000,000 to 10,000,000. A technique was developed for varying the internal air flow during flight so that the drag and pressure-recovery characteristics were measured as functions of both mass-flow ratio and Mach number. A pointed parabolic-arc body having the same contour as that of the inlet model aft of the inlet region was also tested to serve as a basis for drag comparison.
Book Synopsis Development of Flow Distortions in a Full-scale Nacelle Inlet at Mach Numbers 0.63 and 1.6 to 2.0 by : Thomas G. Piercy
Download or read book Development of Flow Distortions in a Full-scale Nacelle Inlet at Mach Numbers 0.63 and 1.6 to 2.0 written by Thomas G. Piercy and published by . This book was released on 1956 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of Three Transonic Fuselage Air Inlets at Mach Numbers from 0.4 to 0.94 and at a Mach Number of 1.19 by : Robert E. Pendley
Download or read book An Investigation of Three Transonic Fuselage Air Inlets at Mach Numbers from 0.4 to 0.94 and at a Mach Number of 1.19 written by Robert E. Pendley and published by . This book was released on 1950 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of three air inlets which were designed for use at transonic speeds was conducted in the Langley 8-foot high-speed tunnel. The basis of the design of these inlets was the use of a nose which was shaped so that substream velocities are maintained on its surface for high-speed operating conditions. Since subsonic velocities would therefore exist on the nose surface up to a limiting supersonic Mach number determined by the nose shape, adverse boundary-layer shock-interaction effects on the nose ahead of the inlet could be avoided at least up to this Mach number.
Book Synopsis Effect of External Boundary Layer on Performance of Axisymmetric Inlet at Mach Numbers of 3.0 and 2.5 by : N. E. Samanich
Download or read book Effect of External Boundary Layer on Performance of Axisymmetric Inlet at Mach Numbers of 3.0 and 2.5 written by N. E. Samanich and published by . This book was released on 1959 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Performance of a Mach 3.0 External-internal- Compression Axisymmetric Inlet at Mach Numbers from 2.0 to 3.5 by :
Download or read book Performance of a Mach 3.0 External-internal- Compression Axisymmetric Inlet at Mach Numbers from 2.0 to 3.5 written by and published by . This book was released on 1960 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Determination of the Drag and Pressure Recovery of an NACA 1-40-250 Nose Inlet at Mach Numbers from 0.9 to 1.8 by : R. I. Sears
Download or read book Flight Determination of the Drag and Pressure Recovery of an NACA 1-40-250 Nose Inlet at Mach Numbers from 0.9 to 1.8 written by R. I. Sears and published by . This book was released on 1954 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made with rocket-propelled models in free flight to determine the external drag and pressure recovery of the NACA 1-40-250 nose inlet at zero angle of attack. The Mach number range of the tests was from 0.9 to 1.8 and the corresponding Reynolds numbers based on body diameter varied from 4,000,000 to 10,000,000. A technique was developed for varying the internal air flow during flight so that the drag and pressure-recovery characteristics were measured as functions of both mass-flow ratio and Mach number. A pointed parabolic-arc body having the same contour as that of the inlet model aft of the inlet region was also tested to serve as a basis for drag comparison.
Book Synopsis Preliminary Experimental Investigation of a Variable-area, Variable-internal-contraction Air Inlet at Mach Numbers Between 1.42 and 2.44 by : Richard Scherrer
Download or read book Preliminary Experimental Investigation of a Variable-area, Variable-internal-contraction Air Inlet at Mach Numbers Between 1.42 and 2.44 written by Richard Scherrer and published by . This book was released on 1955 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt:
