Download or read book Development of NACA Submerged Inlets and a Comparison with Wing Leading edge Inlets for a 1 4 scale Model of a Fighter Airplane written by Emmet A. Mossman and published by . This book was released on 1947 with total page 50 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 1949 with total page 750 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1953 with total page 274 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of NACA Submerged Air Inlets on a 1 5 scale Model of a Fighter Airplane written by Donald E. Gault and published by . This book was released on 1947 with total page 40 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 1951 with total page 568 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Title Announcement Bulletin written by and published by . This book was released on 1953 with total page 1088 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Heat Transfer and Fluid Flow Data Books Fluid flow written by General Electric Company. Research and Development Center and published by . This book was released on 1980 with total page 374 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book 41st AIAA Aerospace Sciences Meeting Exhibit written by and published by . This book was released on 2003 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of the Design Variables for NACA Submerged Duct Entrances written by Emmet A. Mossman and published by . This book was released on 1948 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Tests of Submerged Duct Installation on a Modified Fighter Airplane in the Ames 40 by 80 foot Wind Tunnel written by Norman J. Martin and published by . This book was released on 1947 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Research Abstracts and Reclassification Notice written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1951 with total page 596 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 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 Ram recovery Characteristics 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 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: The data indicate only a slight decrease in ram-recovery ratio for the inlets ahead of or just behind the wing leading edge as Mach number increased, but showed large decreases at high Mach numbers for the inlets aft of the point of maximum thickness of the wing.
Download or read book A New Dimension Wallops Island Flight Test Range written by Joseph Adams Shortal and published by . This book was released on 1978 with total page 808 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12 foot span Fighter type Wing of NACA 230 series Airfoil Sections written by E. O. Pearson and published by . This book was released on 1945 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Force and pressure-distribution measurements were made on a fighter-type wing model of conventional NACA 230-series airfoil sections in the Langley 16-foot high-speed tunnel to determine the effects of compressibility on the maximum lift characteristics and the span-wise load distribution. The range of angle of attack investigated was from -10 to +24 degrees. The Mach range of from 0.20 to 0.70 at small and medium angles of attack and from 0.15 to 0.625 at very large angles of attack. Maximum lift coefficient increased up to a Mach number of 0.3, decreased rapidly to a Mach number of 0.55, and then decreased moderately. At high speeds, maximum lift coefficient was reached at from 10 to 12 degrees beyond the stalling angle. In high-speed stalls, resultant load underwent a moderate shift outward.
