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Book Tests of a Mixed Compression Axisymmetric Inlet with Large Transonic Mass Flow at Mach Numbers 0 6 to 2 65

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contours, designed for Mach number 2.65, provided a throat area of 59 percent of the capture area when the cowl was retracted for transonic operation.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).

Book 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

Download or read book 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 published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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

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 Scientific and Technical Aerospace Reports

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Inlet Performance Characteristics of a Generalized 1 4 scale Tactical Aircraft Models at Transonic and Supersonic Mach Numbers

Download or read book Inlet Performance Characteristics of a Generalized 1 4 scale Tactical Aircraft Models at Transonic and Supersonic Mach Numbers written by R. F. Lauer (Jr.) and published by . This book was released on 1971 with total page 164 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Transonic Off design Drag and Performance of an Axisymmetric Inlet with 40 pertcent Internal Contraction on Design

Download or read book Transonic Off design Drag and Performance of an Axisymmetric Inlet with 40 pertcent Internal Contraction on Design written by Richard R. Woollett and published by . This book was released on 1974 with total page 53 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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

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: