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Investigation Of An Axisymmetric Internal Compression Inlet At A Mach Number Of About 38
Download Investigation Of An Axisymmetric Internal Compression Inlet At A Mach Number Of About 38 full books in PDF, epub, and Kindle. Read online Investigation Of An Axisymmetric Internal Compression Inlet At A Mach Number Of About 38 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Investigation of an Axisymmetric Internal Compression Inlet at a Mach Number of about 3.8 by : John H. Lundell
Download or read book Investigation of an Axisymmetric Internal Compression Inlet at a Mach Number of about 3.8 written by John H. Lundell and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of an Axisymmetric Internal Compression Inlet at a Mach Number of about 3.8 by : John H. Lundell
Download or read book Investigation of an Axisymmetric Internal Compression Inlet at a Mach Number of about 3.8 written by John H. Lundell and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An idealized axisymmetric, all-internal compression inlet was designed for a Mach number of 3.75. The objective of the design was to obtain a steady, one-dimensional transonic flow and a high over-all total-pressure recovery. Boundary-layer removal was employed in the vicinity of the inflection point of the supersonic contour. Static- and total-pressure fluctuations were measured in the transonic flow region. A total-pressure recovery of about 90 percent was obtained with a boundary-layerremoval mass-flow rate of 15 percent of the inlet mass-flow rate. The accompanying root-meansquare total-pressure fluctuation in the throat region was only 1 percent of the free-stream total pressure. The test Mach number was 3.80 and the Reynolds number based on inlet diameter was 2.63 times 10 to the 6th power. (Author).
Book Synopsis Investigation of a Mixed-compression Axisymmetric Inlet System at Mach Numbers 0.6 to 3.5 by : Donald B. Smeltzer
Download or read book Investigation of a Mixed-compression Axisymmetric Inlet System at Mach Numbers 0.6 to 3.5 written by Donald B. Smeltzer and published by . This book was released on 1970 with total page 252 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 Performance of Three Isentropic All Internal Compression Axisymmetric Inlets Designed for Mach 2.5 by : Bernhard H. Anderson
Download or read book Performance of Three Isentropic All Internal Compression Axisymmetric Inlets Designed for Mach 2.5 written by Bernhard H. Anderson and published by . This book was released on 1960 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of a Nearly Isentropic Mixed-compression Axisymmetric Inlet System at Mach Numbers 0.6 to 3.2 by : Donald B. Smeltzer
Download or read book Investigation of a Nearly Isentropic Mixed-compression Axisymmetric Inlet System at Mach Numbers 0.6 to 3.2 written by Donald B. Smeltzer and published by . This book was released on 1968 with total page 162 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of the Flow in an Axisymmetric Internal-compression Inlet for M by : Earl C. Watson
Download or read book An Experimental Investigation of the Flow in an Axisymmetric Internal-compression Inlet for M written by Earl C. Watson and published by . This book was released on 1961 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Comparison of the Performance of Four Side-mounted Inlets Over a Mach Number Range of 0.88 to 2.2 and Angles of Attack to 14° by : Leroy L. Presley
Download or read book A Comparison of the Performance of Four Side-mounted Inlets Over a Mach Number Range of 0.88 to 2.2 and Angles of Attack to 14° written by Leroy L. Presley and published by . This book was released on 1960 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Performance of Three Isentropic All Internal Compression Axisymmetric Inlets Designed for Mach 2.5 by :
Download or read book Performance of Three Isentropic All Internal Compression Axisymmetric Inlets Designed for Mach 2.5 written by and published by . This book was released on 1960 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book NASA Technical Note written by and published by . This book was released on 1969 with total page 712 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of the Flow in an Axisymmetric Internal-compression Inlet for M by : Earl C. Watson
Download or read book An Experimental Investigation of the Flow in an Axisymmetric Internal-compression Inlet for M written by Earl C. Watson and published by . This book was released on 1961 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis PERFORMANCE SUMMARY AND ANALYSIS OF A MACH 3.0 DESIGN AXISYMMETRIC ALL-EXTERNAL-COMPRESSION DOUBLE-CONE INLET FROM MACH NUMBER 3.0 TO 0.8 by :
Download or read book PERFORMANCE SUMMARY AND ANALYSIS OF A MACH 3.0 DESIGN AXISYMMETRIC ALL-EXTERNAL-COMPRESSION DOUBLE-CONE INLET FROM MACH NUMBER 3.0 TO 0.8 written by and published by . This book was released on 1960 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 Experimental Investigation of a Large-scale, Two-dimensional, Mixed-compression Inlet System by : Norman D. Wong
Download or read book Experimental Investigation of a Large-scale, Two-dimensional, Mixed-compression Inlet System written by Norman D. Wong and published by . This book was released on 1971 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: A large-scale, variable-geometry inlet model with a design Mach number of 3.0 was tested at Mach numbers from 1.55 to 3.2. Variable features of the inlet for off-design operation are an adjustable-height ramp system and a translating cowl. This report presents experimental results for a diffuser and boundary-layer bleed configuration which was optimized at the design Mach number. Overall performance was high with throat-mounted vortex generators, which were effective in reducing flow distortion in the subsonic diffuser at the higher Mach numbers.
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 Tests of a Mixed Compression Axisymmetric Inlet with Large Transonic Mass Flow at Mach Numbers 0.6 to 2.65 by : Donald B. Smeltzer
Download or read book Tests of a Mixed Compression Axisymmetric Inlet with Large Transonic Mass Flow at Mach Numbers 0.6 to 2.65 written by Donald B. Smeltzer and published by . This book was released on 1972 with total page 196 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 38.8-cm (15.28-in.) capture diameter model of a mixed-compression axisymmetric inlet system with a translating cowl was designed and tested. The internal contours, designed for Mach number 2.65, provided a throat area of 59 percent of the capture area when the cowl was retracted for transonic operation. Other model features included a boundary-layer removal system, vortex generators, an engine airflow bypass system, cowl support struts, and rotating rakes at the engine face. All tunnel testing was conducted at a tunnel total pressure of about 1 atm (a unit Reynolds number of about 8.53 million/m at Mach number 2.65) at angles of attack from 0 deg to 4 deg. Results for the following were obtained: total-pressure recovery and distortion at the engine face as a function of bleed mass-flow ratio, the effect of bleed and vortex generator configurations on pressure recovery and distortion, inlet tolerance to unstart due to changes in angle of attack or Mach number, surface pressure distributions, boundary-layer profiles, and transonic additive drag. At Mach number 2.65 and with the best bleed configurations, maximum total pressure recovery at the engine face ranged from 91 to 94.5 percent with bleed mass-flow ratios from 4 to 9 percent, respectively, and total-pressure distortion was less than 10 percent. At off-design supersonic Mach numbers above 1.70, maximum total-pressure recoveries and corresponding bleed mass flows were about the same as at Mach number 2.65, with about 10 to 15 percent distortion. In the transonic Mach number range, total pressure recovery was high (above 96 percent) and distortion was low (less than 15 percent) only when the inlet mass-flow ration was reduced 0.02 to 0.06 from the maximum theoretical value (0.590 at Mach number 1.0).
