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An Investigation Of Several Naca 1 Series Inlets At Mach Numbers From 04 To 129 For Mass Flow Ratios Near 10
Download An Investigation Of Several Naca 1 Series Inlets At Mach Numbers From 04 To 129 For Mass Flow Ratios Near 10 full books in PDF, epub, and Kindle. Read online An Investigation Of Several Naca 1 Series Inlets At Mach Numbers From 04 To 129 For Mass Flow Ratios Near 10 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis An investigation of several NACA 1-series inlets at Mach numbers from 0.4 to 1.29 for mass-flow ratios near 1.0 by : Richard J. Re
Download or read book An investigation of several NACA 1-series inlets at Mach numbers from 0.4 to 1.29 for mass-flow ratios near 1.0 written by Richard J. Re and published by . This book was released on 1976 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of Several NACA 1-series Axisymmetric Inlets at Mach Numbers from 0.4 to 1.29 by : Richard J. Re
Download or read book An Investigation of Several NACA 1-series Axisymmetric Inlets at Mach Numbers from 0.4 to 1.29 written by Richard J. Re and published by . This book was released on 1974 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Tests of a Small-scale NACA Submerged Inlet at Transonic Mach Numbers by : L. Stewart Rolls
Download or read book Tests of a Small-scale NACA Submerged Inlet at Transonic Mach Numbers written by L. Stewart Rolls and published by . This book was released on 1950 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: The pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 have been measured in the Mach number range 0.60 to 1.08 by the wing-flow method. The variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60.
Book Synopsis An Experimental Investigation of NACA Submerged Inlets at High Subsonic Speeds by : Charles F. Hall
Download or read book An Experimental Investigation of NACA Submerged Inlets at High Subsonic Speeds written by Charles F. Hall and published by . This book was released on 1948 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: The data show that variations in the mass of air entering the inlet had a large effect on the ram-recovery ratio. Representative values of ram-recovery ratio were 0.50 with zero flow, 0.90 with 0.6 mass-flow coefficient, and 0.95 with 1.00 mass-flow coefficient. Variations in Mach number and angle of attack, in general, caused less than a 0.03 variation in the ram-recovery ratio.
Book Synopsis Preliminary Investigation of the Transonic Characteristics of an NACA Submerged Inlet by : John A. Axelson
Download or read book Preliminary Investigation of the Transonic Characteristics of an NACA Submerged Inlet written by John A. Axelson and published by . This book was released on 1950 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: A preliminary investigation of an NACA submerged inlet operating over a range of mass-flow ratios and oncoming flow angles was conducted through a Mach number range from 0.70 to 1.15 by the use of a transonic bump. Ram recovery and pressure distribution were measured for mass-flow ratios up to 0.67. For approximately constant mass-flow ratio, the ram-recovery ratio decreased about 0.05 in the Mach number from 0.85 to 1.1, but generally improved above a Mach number of 1.0 to 1.1. The ram-recovery ratio decreased about 0.05 when the angle between the inlet center plane and the free stream was increased from 0 to 4 degrees, but increased about 0.02 from this reduced value when the angle was increased from 4 to 8 degrees. Increasing the mass flow into the inlet increased the ram recovery, but the improvement became progressively less at the higher mass flows and higher Mach numbers. Static-pressure and total-pressure surveys inside the inlet indicated that the losses in ram recovery were caused principally by the entrance of low-energy air from the surrounding boundary layer which passed over the sharp edges of the ramp walls and mixed with the higher-energy air entering the inlet.
Book Synopsis A Variable-geometry Annular Cascade-type Inlet at Mach Numbers of 1.9 and 3.05 by : James F. Connors
Download or read book A Variable-geometry Annular Cascade-type Inlet at Mach Numbers of 1.9 and 3.05 written by James F. Connors and published by . This book was released on 1956 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: An axisymmetric variable-geometry cascade inlet has been proposed and demonstrated. By means of a translating spike, an annular double-passage cascade arrangement was formed at a Mach number of 1.9 and a single-passage configuration with an internal area discontinuity (vortex trap) was effected at a Mach number of 3.05.
Book Synopsis Effect of Centerbody Boundary-layer Removal Near the Throat of Three Conical Nose Inlets at Mach 1.6 to 2.0 by : Emil J. Kremzier
Download or read book Effect of Centerbody Boundary-layer Removal Near the Throat of Three Conical Nose Inlets at Mach 1.6 to 2.0 written by Emil J. Kremzier and published by . This book was released on 1955 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation at Mach Numbers from 2.1 to 3.0 of Circular Internal-compression Inlets Having Translatable Centerbodies and Provisions for Boundary-layer Removal by : Earl C. Watson
Download or read book An Experimental Investigation at Mach Numbers from 2.1 to 3.0 of Circular Internal-compression Inlets Having Translatable Centerbodies and Provisions for Boundary-layer Removal written by Earl C. Watson and published by . This book was released on 1960 with total page 32 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 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 Some Considerations Concerning Inlets and Ducted Bodies at Mach Numbers from 0.8 to 2.0 by : Richard I. Sears
Download or read book Some Considerations Concerning Inlets and Ducted Bodies at Mach Numbers from 0.8 to 2.0 written by Richard I. Sears and published by . This book was released on 1953 with total page 22 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:
Book Synopsis Performance of External-compression Bump Inlet at Mach Numbers of 1.5 to 2.0 by : Paul C. Simon
Download or read book Performance of External-compression Bump Inlet at Mach Numbers of 1.5 to 2.0 written by Paul C. Simon and published by . This book was released on 1957 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation at Supersonic and Subsonic Mach Numbers of Auxiliary Inlets Supplying Secondary Air Flow to Ejector Exhaust Nozzles by : Donald P. Hearth
Download or read book Investigation at Supersonic and Subsonic Mach Numbers of Auxiliary Inlets Supplying Secondary Air Flow to Ejector Exhaust Nozzles written by Donald P. Hearth and published by . This book was released on 1956 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results indicated increases in auxiliary-inlet pressure recovery with increases in scoop height relative to the boundary-layer thickness. The pressure recovery increased at about the same rate as theoretically predicted for an inlet in a boundary layer having a one-seventh power profile, but was only about 0.68 to 0.75 of the theoretically obtainable values. Under some operating conditions, flow from the primary jet was exhausted through the auxiliary inlet. This phenomenon could be predicted from the ejector pumping characteristics.
Book Synopsis An Inlet Design Concept to Reduce Flow Distortion at Angle of Attack by : Carl F. Schueller
Download or read book An Inlet Design Concept to Reduce Flow Distortion at Angle of Attack written by Carl F. Schueller and published by . This book was released on 1957 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Detailed pressure measurements were made of the flow distortion just inside the cowl lip of a fixed-cone planar-cowl inlet, a pivoting-cone planar-cowl inlet and a pivoting-cone swept-cowl inlet operated at angles of attack from 0 to 14 degrees and at a Mach number of 1.91. The overa-all pressure recovery and flow distortion at the exit of the three diffusers were also measured.
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 An Approximate Solution of Additive-drag Coefficient and Mass-flow Ratio for Inlets Utilizing Right Circular Cones at Zero Angle of Attack by : Vincent R. Mascitti
Download or read book An Approximate Solution of Additive-drag Coefficient and Mass-flow Ratio for Inlets Utilizing Right Circular Cones at Zero Angle of Attack written by Vincent R. Mascitti and published by . This book was released on 1969 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Incompressible approximation solution of additive drag coefficient and mass flow ratio for inlets with right circular cones.
