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A Comparison Of The Performance Of Four Side Mounted Inlets Over A Mach Number Range Of 088 To 22 And Angles Of Attack To 14
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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 50 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 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 Deg by :
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 Deg written by and published by . This book was released on 1960 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1965 with total page 1068 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of an Underslung Half-cone Inlet with Compression Surface Mounted Outboard from Fuselage at Mach Numbers of 1.5, 1.8, and 2.0 by : Richard A. Yeager
Download or read book Investigation of an Underslung Half-cone Inlet with Compression Surface Mounted Outboard from Fuselage at Mach Numbers of 1.5, 1.8, and 2.0 written by Richard A. Yeager and published by . This book was released on 1958 with total page 22 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 High-angle-of-attack Performance of a 14 Degree Ramp-type Inlet in Various Circumferential Body Locations Mach Number Range 1.5 to 2.0 by : Glenn A. Mitchell
Download or read book Investigation of High-angle-of-attack Performance of a 14 Degree Ramp-type Inlet in Various Circumferential Body Locations Mach Number Range 1.5 to 2.0 written by Glenn A. Mitchell and published by . This book was released on 1957 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Preliminary Investigation of Shield to Improve Angle-of-attack Performance of Nacelle-type Inlet by : Milton A. Beheim
Download or read book Preliminary Investigation of Shield to Improve Angle-of-attack Performance of Nacelle-type Inlet written by Milton A. Beheim and published by . This book was released on 1957 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted at Mach numbers between 1.6 and 2.0 on the use of a shield along the upper-half periphery of the cowl of a conical inlet to improve performance at angle of attack. The best results were obtained with the shield mounted in such a manner that an air gap existed between the shield and the cowl lip. Zero-angle-of-attack performance was not appreciably affected. At an angle of attack of 8 degrees distortion was about half that without the shield, and subcritical stability was improved.
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 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Jane's All the World's Aircraft by :
Download or read book Jane's All the World's Aircraft written by and published by . This book was released on 1989 with total page 864 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Documentation of the Phase III 0.192-scale Northrop/McDonnell-Douglas F-18 Inlet Performance Test at Mach Numbers 0 to 1.55 by : Jimmy Walker
Download or read book Documentation of the Phase III 0.192-scale Northrop/McDonnell-Douglas F-18 Inlet Performance Test at Mach Numbers 0 to 1.55 written by Jimmy Walker and published by . This book was released on 1978 with total page 222 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Zero-angle-of-attack Performance of Two-dimensional Inlets Near Mach Number 3 by : Richard R. Woollett
Download or read book Zero-angle-of-attack Performance of Two-dimensional Inlets Near Mach Number 3 written by Richard R. Woollett and published by . This book was released on 1956 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: An extensive program was undertaken to investigate the effect of several geometric variables on the performance of two-dimensional inlets. This investigation included inlets having single-wedge, double-wedge, and isentropic compression ramps with various side-plate configurations and subsonic diffusers. The tests were conducted over a range of Reynolds number based on inlet height from 0.50 to 2.67(sup x)10(sup 6). Generally, the performance levels of the two-dimensional inlets were somewhat below those obtained previously with comparable axisymmetric models. At Mach number 3.05 the optimum total-pressure recovery was obtained with an isentropic inlet which compressed the external flow to a Mach number of 1.88. Rectangular side plates and a long high-exit-Mach-number subsonic diffuser with filleted corners were used with this inlet. A critical total-pressure recovery of 0.71 was realized with a corresponding mass-flow ratio of 0.965. Subcritical stability to a mass-flow ratio of 0.60 was obtained.
Book Synopsis Results of a 0.1-scale B-1 Inlet Model Test at Transonic and Supersonic Mach Numbers by : F. J. Graham
Download or read book Results of a 0.1-scale B-1 Inlet Model Test at Transonic and Supersonic Mach Numbers written by F. J. Graham and published by . This book was released on 1971 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented of a wind tunnel investigation of a 0.1-scale model of the left-hand dual inlet air induction system of the B-1 aircraft. The test was conducted from Mach number 0.55 to 2.2 over an angle-of-attack range from -4 to 13 deg and yaw angles of -8 to 5 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion, and turbulence index is presented as a function of inlet mass-flow ratios for various inlet geometries and model attitudes. The total-pressure recovery of the mixed-compression inlet was very good, but the total-pressure distortion at critical massflow ratios was higher than normally desired for satisfactory turbine engine operation. Best performance was realized with ramp and throat height schedules determined from previous testing. Effects of angle of attack and yaw were seen as general sidewash effects. The addition of canard-type fins had negligible effect on inlet performance. (Author).
Book Synopsis Results of a 0.2-scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers by : John F. Riddell
Download or read book Results of a 0.2-scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers written by John F. Riddell and published by . This book was released on 1972 with total page 250 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented of a wind tunnel investigation of a 0.2-scale model of the left-hand dual-inlet air induction system of the B-1 aircraft. The test was conducted at Mach numbers from 0.55 to 2.3 over an angle-of-attack range from -2 to 13 deg and yaw angles of -6 to 6 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion and turbulence index is presented as a function of engine-face mass-flow ratio for various inlet geometries and model attitudes. Generally, increasing angle of attack caused greated decreases in the performance of the inboard inlet at supersonic Mach numbers and of the outboard inlet at subsonic Mach numbers. Noticeable effects occurred when the structural mode control vanes were varied at the subsonic Mach number at low angles of attack and at negative yaw. (Author).
Book Synopsis A Pivoting-cowl-and-spike Technique for Efficient Angle-of-attack Operation of Supersonic Inlets by : Nick E. Samanich
Download or read book A Pivoting-cowl-and-spike Technique for Efficient Angle-of-attack Operation of Supersonic Inlets written by Nick E. Samanich and published by . This book was released on 1958 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Comparisons of In-flight F-111A Inlet Performance for On- and Off-scheduled Inlet Geometry at Mach Numbers of 0.68 to 2.18 by : Richard A. Martin
Download or read book Comparisons of In-flight F-111A Inlet Performance for On- and Off-scheduled Inlet Geometry at Mach Numbers of 0.68 to 2.18 written by Richard A. Martin and published by . This book was released on 1971 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: In-flight F-111 data on total and static pressure from left inlet during automatically scheduled and manually controlled off-schedule positioning of spike at Mach 0.68 to 2.18.
Book Synopsis 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 by : John L. Allen
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:
