Investigation Of A Mixed Compression Axisymmetric Inlet At Mach Number 5 3
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Investigation Of A Mixed Compression Axisymmetric Inlet System At Mach Numbers 0 6 To 3 5
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Author : Donald B. Smeltzer
language : en
Publisher:
Release Date : 1970
Investigation Of A Mixed Compression Axisymmetric Inlet System At Mach Numbers 0 6 To 3 5 written by Donald B. Smeltzer and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1970 with Aerodynamics, Supersonic categories.
Investigation Of An Axisymmetric Internal Compression Inlet At A Mach Number Of About 3 8
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Author : John H. Lundell
language : en
Publisher:
Release Date : 1961
Investigation Of An Axisymmetric Internal Compression Inlet At A Mach Number Of About 3 8 written by John H. Lundell and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with Propulsion systems categories.
Investigation Of A Nearly Isentropic Mixed Compression Axisymmetric Inlet System At Mach Numbers 0 6 To 3 2
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Author : Donald B. Smeltzer
language : en
Publisher:
Release Date : 1968
Investigation Of A Nearly Isentropic Mixed Compression Axisymmetric Inlet System At Mach Numbers 0 6 To 3 2 written by Donald B. Smeltzer and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1968 with Jet engines categories.
Investigation Of A Mixed Compression Axisymmetric Inlet At Mach Number 5 3
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Author : Eldon A. Latham
language : en
Publisher:
Release Date : 1972
Investigation Of A Mixed Compression Axisymmetric Inlet At Mach Number 5 3 written by Eldon A. Latham and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1972 with Axial flow categories.
Experimental Investigation Of A Large Scale Two Dimensional Mixed Compression Inlet System
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Author : Norman D. Wong
language : en
Publisher:
Release Date : 1971
Experimental Investigation Of A Large Scale Two Dimensional Mixed Compression Inlet System written by Norman D. Wong and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1971 with Jet engines categories.
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.
Tests Of A Mixed Compression Axisymmetric Inlet With Large Transonic Mass Flow At Mach Numbers 0 6 To 2 65
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Author : Donald B. Smeltzer
language : en
Publisher:
Release Date : 1972
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 has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1972 with Aerodynamics, Transonic categories.
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).
Performance Of A Mach Number 3 0 Design Axisymmetric Double Cone External Compression Inlet In The Mach Number Range 1 97 To 0 79
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Author : Owen H. Davis
language : en
Publisher:
Release Date : 1960
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 has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with Aerodynamics, Supersonic categories.
Nasa Technical Note
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Author :
language : en
Publisher:
Release Date : 1973
Nasa Technical Note written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1973 with categories.
Performance Summary And Analysis Of A Mach 3 0 Design Axisymmetric All External Compression Double Cone Inlet Mach Number Range 3 0 To 0 8
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Author : John L. Allen
language : en
Publisher:
Release Date : 1960
Performance Summary And Analysis Of A Mach 3 0 Design Axisymmetric All External Compression Double Cone Inlet Mach Number Range 3 0 To 0 8 written by John L. Allen and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with Airplanes categories.
Performance Of External Compression Bump Inlet At Mach Numbers Of 1 5 To 2 0
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Author : Paul C. Simon
language : en
Publisher:
Release Date : 1957
Performance Of External Compression Bump Inlet At Mach Numbers Of 1 5 To 2 0 written by Paul C. Simon and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Aerodynamics, Supersonic categories.