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:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1976 with total page 1072 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 A Wind Tunnel Investigation of Three NACA 1 Series Inlets at Mach Numbers Up To 0 92 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 184 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distributions on three NACA 1-series inlets have been obtained in the Langley 16-Foot Transonic Tunnel. The cowl diameter ratio (ratio of cowl highlight diameter to cowl maximum diameter) was 0.85 for all three inlets. The cowl length ratio (ratio of cowl length to cowl maximum diameter) was 1.0 for two of the inlets (NACA 1-85-100) and 0.439 for the other (NACA 1-85-43.9) inlet. One of the inlets with a cowl length ratio of 1.0 had an internal contraction ratio (ratio of highlight area to throat area) of 1.009 and the other had a contraction ratio of 1.250. The inlet with a cowl length ratio of 0.439 also had an internal contraction ratio of 1.250. All three inlets had longitudinal rows of static pressure orifices on the top and bottom external cowl surfaces. The inlet with a contraction ratio of 1.009 also had a row of static pressure orifices on the side of the cowl (external surface). The two inlets with a contraction ratio of 1.250 had a longitudinal row of static pressure orifices on the diffuser surface. Re, Richard J. and Abeyounis, William K. Langley Research Center WIND TUNNEL TESTS; PRESSURE DISTRIBUTION; STATIC PRESSURE; ENGINE INLETS; AIRCRAFT ENGINES; MACH NUMBER; ANGLE OF ATTACK; SUBSONIC FLOW; CONTRACTION; NACELLES; FOREBODIES; MASS FLOW; PRESSURE MEASUREMENT; AXISYMMETRIC BODIES...
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 1955 with total page 51 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 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.
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.
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.
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 Index to NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960-07 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Research Abstracts written by United States. National Advisory Committee for Aeronautics and published by . This book was released on with total page 442 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Selected Listing of NASA Scientific and Technical Reports for written by and published by . This book was released on 1959 with total page 296 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Download or read book Index of NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960 with total page 448 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Research Memorandum written by and published by . This book was released on 1948 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Wind Tunnel Investigation of Three NACA 1 Series Inlets at Mach Numbers Up to 0 92 written by and published by . This book was released on 1996 with total page 188 pages. Available in PDF, EPUB and Kindle. Book excerpt:
