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Book Flight Determination of the Drag and Pressure Recovery of an NACA 1 40 250 Nose Inlet at Mach Numbers from 0 9 to 1 8

Download or read book Flight Determination of the Drag and Pressure Recovery of an NACA 1 40 250 Nose Inlet at Mach Numbers from 0 9 to 1 8 written by R. I. Sears and published by . This book was released on 1951 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made with rocket-propelled models in free flight to determine the external drag and pressure recovery of the NACA 1-40-250 nose inlet at zero angle of attack. The Mach number range of the tests was from 0.9 to 1.8 and the corresponding Reynolds numbers based on body diameter varied from 4,000,000 to 10,000,000. A technique was developed for varying the internal air flow during flight so that the drag and pressure-recovery characteristics were measured as functions of both mass-flow ratio and Mach number. A pointed parabolic-arc body having the same contour as that of the inlet model aft of the inlet region was also tested to serve as a basis for drag comparison.

Book Flight Determination of the Drag and Pressure Recovery of an NACA 1 40 250 Nose Inlet at Mach Numbers from 0 9 to 1 8

Download or read book Flight Determination of the Drag and Pressure Recovery of an NACA 1 40 250 Nose Inlet at Mach Numbers from 0 9 to 1 8 written by R. I. Sears and published by . This book was released on 1954 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made with rocket-propelled models in free flight to determine the external drag and pressure recovery of the NACA 1-40-250 nose inlet at zero angle of attack. The Mach number range of the tests was from 0.9 to 1.8 and the corresponding Reynolds numbers based on body diameter varied from 4,000,000 to 10,000,000. A technique was developed for varying the internal air flow during flight so that the drag and pressure-recovery characteristics were measured as functions of both mass-flow ratio and Mach number. A pointed parabolic-arc body having the same contour as that of the inlet model aft of the inlet region was also tested to serve as a basis for drag comparison.

Book Flight Determination of Drag and Pressure Recovery of Two Scoop Inlets Located at Maximum body diameter Station at Mach Numbers from 0 8 to 1 8

Download or read book Flight Determination of Drag and Pressure Recovery of Two Scoop Inlets Located at Maximum body diameter Station at Mach Numbers from 0 8 to 1 8 written by Leonard W. Putland and published by . This book was released on 1956 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two models each utilizing a scoop inlet located at the maximum-body-diameter station operating mass-flow ratios from 0.76 to 0.96 have been flight tested at an angle of attack of approximately zero degrees over a Mach number range from 0.8 to 1.8, and a Reynolds number range from 2,000,000 to7,000,000 based on body maximum diameter. One of the scoop inlets had a circular cross section with a boundary-layer diverter. The other scoop inlet had a semicircular cross section wrapped partly around the body with a boundary-layer splitter plate ahead of the inlet.

Book Flight Determination of Drag and Pressure Recovery of a Nose Inlet of Parabolic Profile at Mach Numbers from 0 8 to 1 7

Download or read book Flight Determination of Drag and Pressure Recovery of a Nose Inlet of Parabolic Profile at Mach Numbers from 0 8 to 1 7 written by Richard I. Sears and published by . This book was released on 1951 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Technical Note National Advisory Committee for Aeronautics

Download or read book Technical Note National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1958 with total page 1274 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Subsonic Flight Investigation of Methods to Improve the Damping of Lateral Oscillations by Means of a Viscous Damper in the Rudder System in Conjuction with Adjusted Hinge moment Parameters

Download or read book Subsonic Flight Investigation of Methods to Improve the Damping of Lateral Oscillations by Means of a Viscous Damper in the Rudder System in Conjuction with Adjusted Hinge moment Parameters written by Harold L. Crane and published by . This book was released on 1958 with total page 654 pages. Available in PDF, EPUB and Kindle. Book excerpt: A flight investigation at subsonic speeds of a method to improve the damping of lateral oscillations by means of a viscous damping cylinder used in the rudder system in conjunction with adjusted hinge-moment parameters has been conducted. The damping device has been applied to a modern fighter-type jet-powered airplane. The rudder was made to float with the relative wind by the addition of trailing-edge strips. In order to amplify the floating tendency (by reducing the restoring moment), a highly geared balancing tab was incorporated. Lag of the motion of the free rudder with respect to the yawing of the airplane was introduced by means of a small viscous damping cylinder linked to the rudder.

Book Subject Index to Unclassified ASTIA Documents

Download or read book Subject Index to Unclassified ASTIA Documents written by Defense Documentation Center (U.S.) and published by . This book was released on 1960 with total page 308 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Tests of a Small scale NACA Submerged Inlet at Transonic Mach Numbers

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 Flight Investigation at High Mach Numbers of Several Methods of Measuring Static Pressure on an Airplane Wing

Download or read book Flight Investigation at High Mach Numbers of Several Methods of Measuring Static Pressure on an Airplane Wing written by John A. Zalovcik and published by . This book was released on 1944 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: A flight investigation was made to compare static pressures in subsonic and supersonic flow over an airplane wing as measured by static-pressure tubes, a static-pressure belt, and orifices flush with the wing surface. The measurements were made on the upper surface of the wing of the P-47D airplane over a range of flight conditions in which local Mach numbers from 0.34 to 1.41 were obtained at the measurement stations. For some of the tests, a total-pressure tube was mounted on the wing surface to determine its characteristics in supersonic flow. The results indicated that static-pressure measurements obtained with suitably designed and installed flush orifices, static-pressure tubes, and static-pressure belt will be in reasonable agreement for both subsonic and supersonic flow. The pressures in supersonic flow measured by the total-pressure tube mounted on the wing surface were found to be in close agreement with values predicted by theory.

Book Flight Determination of Drag of Normal shock Nose Inlets with Various Cowling Profiles at Mach Numbers from 0 9 to 1 5

Download or read book Flight Determination of Drag of Normal shock Nose Inlets with Various Cowling Profiles at Mach Numbers from 0 9 to 1 5 written by R. I. Sears and published by . This book was released on 1956 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Preliminary Flight Measurements of the Total Pressure Recovery of a Split Wing Ram Jet Inlet at Mach Numbers from 1 4 To 3 16

Download or read book Preliminary Flight Measurements of the Total Pressure Recovery of a Split Wing Ram Jet Inlet at Mach Numbers from 1 4 To 3 16 written by A. H. Hinners and published by BiblioGov. This book was released on 2013-07 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NASA Technical Reports Server (NTRS) houses half a million publications that are a valuable means of information to researchers, teachers, students, and the general public. These documents are all aerospace related with much scientific and technical information created or funded by NASA. Some types of documents include conference papers, research reports, meeting papers, journal articles and more. This is one of those documents.