Download or read book Force and Pressure recovery Characteristics of a Conical type Nose Inlet Operating at Mach Numbers of 1 6 to 2 0 and at Angles of Attack to 9 Degrees written by Andrew Beke and published by . This book was released on 1952 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book 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 published by . This book was released on 1951 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1 59 to 1 99 written by Robert T. Madden and published by . This book was released on 1951 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: As part of a general investigation of supersonic inlets in the NACA Lewis 8- by 6-foot supersonic wind tunnel, tests were conducted to determine the force and pressure-recovery characteristics of a model utilizing a single-shock spike-type inlet with a perforated cowl. External and internal pressure distributions, pressure recovery, and lift, drag, and pitching moment were measured for a range of mass-flow ratios at angles of attack from 0 to 10 degrees for free-stream Mach number of 1.59, 1.79, and 1.99. The average Reynolds number based on the inlet diameter was approximately 2,400,000.
Download or read book Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1 59 to 1 99 written by Maynard I. Weinstein and published by . This book was released on 1951 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the NACA Lewis 8- by 6-foot supersonic wind tunnel to determine the force and pressure characteristics of an all-external compression inlet having a conical spike and a supersonic cowl lip. Measurements of lift, drag pitching moment, and internal and external pressures were made at free-stream Mach numbers of 1.59, 1.79, and 1.99 for a range of mass-flow ratios and angles of attack to 10 degrees. The average Reynolds number based on inlet diameter was 2,300,000.
Download or read book Force and Pressure recovery Characteristics at Supersonic Speeds of a Conical Nose Inlet with Bypass Discharging Outward from the Body Axis written by Andrew Beke and published by . This book was released on 1953 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1 59 to 1 99 written by Fred T. Esenwein and published by . This book was released on 1951 with total page 73 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Characteristics of Four Nose Inlets as Measured at Mach Numbers Between 1 4 and 2 0 written by George B. Brajnikoff and published by . This book was released on 1956 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: The pressure recovery, mass flow, and axial force of four bodies with nose inlets were measured at Mach numbers between 1.4 and 2.0 and angles of attack of 0, 3, 6, and 9 degrees. The Reynolds number based on the model inlet diameters varied between 0.4 and 0.8 million. Schlieren photographs of models at 0 degrees angle of attack were used for calculation of the external wave drag resulting from the bow shock waves.
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.
Download or read book An Investigation of Several NACA 1 series Nose Inlets with and Without Protruding Central Bodies at High subsonic Mach Numbers and at a Mach Number of 1 2 written by Robert E. Pendley and published by . This book was released on 1950 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of three NACA 1-series nose inlets, two of which were fitted with protruded central bodies, was conducted in the Langley 8-foot high-speed tunnel. An elliptical-nose body, which had a critical Mach number approximately equal to that of one of the nose inlets, was also tested. Tests were made near zero angle of attack for a Mach number range from 0.4 to 0.925 and for the supersonic Mach number of 1.2. The inlet-velocity-ratio range extended from zero to a maximum value of 1.34. Measurements included pressure distribution, external drag, and total-pressure loss of the internal flow near the inlet. Drag was not measured for the tests at the supersonic Mach number.
Download or read book Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1 59 to 1 99 written by Robert T. Madden and published by . This book was released on 1951 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers from 1 59 to 1 99 written by E. Howard and published by . This book was released on 1951 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Nose Bluntness Fineness Ratio Cone Angle and Model Base on the Static Aerodynamic Characteristics of Blunt Bodies at Mach Numbers of 1 57 1 80 and 2 16 and Angles of Attack Up to 180 written by David S. Shaw and published by . This book was released on 1963 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Investigation of an Underslung Nose Inlet with Various Nose Configurations at Mach Numbers from 1 55 to 2 23 written by and published by . This book was released on 1959 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Preliminary Investigation of the Total pressure recovery Characteristics of a Symmetric and an Asymmetric Nose Inlet Over a Wide Range of Angle of Attack at Supersonic Mach Numbers written by Howard S. Carter and published by . This book was released on 1953 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Performance of a Translating double cone Axisymmetric Inlet with Cowl Bypass at Mach Number from 2 0 to 3 5 written by James F. Connors and published by . This book was released on 1957 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Force and Pressure Recovery Characteristics at Supersonic Speeds of a Conical Spike Inlet with a Bypass Discharging from the Top Or Bottom of the Diffuser in an Axial Direction written by J.L. Allen and published by . This book was released on 1953 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
