Performance Of Three Isentropic All Internal Compression Axisymmetric Inlets Designed For Mach 2 5
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Performance Of Three Isentropic All Internal Compression Axisymmetric Inlets Designed For Mach 2 5
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Author : Bernhard H. Anderson
language : en
Publisher:
Release Date : 1960
Performance Of Three Isentropic All Internal Compression Axisymmetric Inlets Designed For Mach 2 5 written by Bernhard H. Anderson 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.
Performance Of Three Isentropic All Internal Compression Axisymmetric Inlets Designed For Mach 2 5
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Author :
language : en
Publisher:
Release Date : 1960
Performance Of Three Isentropic All Internal Compression Axisymmetric Inlets Designed For Mach 2 5 written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with categories.
Scientific And Technical Aerospace Reports
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Author :
language : en
Publisher:
Release Date : 1985
Scientific And Technical Aerospace Reports written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1985 with Aeronautics categories.
Procedures For Estimating Inlet External And Internal Performance
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Author : B. M. Sharp
language : en
Publisher:
Release Date : 1974
Procedures For Estimating Inlet External And Internal Performance written by B. M. Sharp and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1974 with Aerodynamics, Supersonic categories.
Government Wide Index To Federal Research Development Reports
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Author :
language : en
Publisher:
Release Date : 1965
Government Wide Index To Federal Research Development Reports written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1965 with Government publications 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.
Investigation Of Three Mach 7 External Compression Axisymmetric Inlets From Mach 1 9 To 6 8
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Author :
language : en
Publisher:
Release Date : 1960
Investigation Of Three Mach 7 External Compression Axisymmetric Inlets From Mach 1 9 To 6 8 written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with categories.
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.
Force And Pressure Characteristics For A Series Of Nose Inlets At Mach Numbers From 1 59 To 1 99
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Author : L. J. Obery
language : en
Publisher:
Release Date : 1951
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 has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with Aerodynamics, Supersonic categories.
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.
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).