Download or read book Inlet Sensitivity Study for a Supersonic Transport written by Robert W. Koenig and published by . This book was released on 1967 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1972 with total page 820 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Coupled Supersonic Inlet engine Control Using Overboard Bypass Doors and Engine Speed to Control Normal Shock Position written by Gary L. Cole and published by . This book was released on 1970 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Inlet Flow Field Studies for the Supersonic Transport written by W. A. Reinhart and published by . This book was released on 1965 with total page 9 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 1995 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1980 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Monthly Catalog of United States Government Publications written by United States. Superintendent of Documents and published by . This book was released on 1967 with total page 766 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government wide Index to Federal Research Development Reports written by and published by . This book was released on 1967-04 with total page 1078 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Study of the Sensitivity of a Supersonic Aircraft to the Effect of Various Horizontal Temperature Distributions written by Sidney M. Serebreny and published by . This book was released on 1964 with total page 41 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effect of the variations in the horizontal distribution of temperature on supersonic transport operation in cruise was studied on the New York/London-Paris route. From the data sample the range of temperature variations was established. Temperature variations in 24 cases were run through a NASA computer program and fuel consumption derived. The results of this program closely approximated the theoretical temperature fuel consumption. In none of the cases did the temperature gradient warrant diversion from great circle. The cases chosen reflected extremes of departure from standard and present a seasonal distribution of such variations. Average route temperature differences from 141 seleccted dates substantiate the predominant lack of adequate gradients for such track diversions from great circle. (Author).
Download or read book An Experimental Investigation of Shock Wave Boundary Layer Interaction Dynamics written by Gerald W. Braun and published by . This book was released on 1969 with total page 254 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests were performed which simulated the flow pulsations which are sometimes produced in engine inlets by shock-boundary layer interaction. Shock Mach numbers from 1.2 to 1.4 were used and the boundary layer was influenced by air bleeding in or sucking off. The flow was observed by shodowgraph and static and total pressures were measured by means of low frequency and high frequency response instruments. Static wall pressures, boundary layer pressure profiles, and total pressure distributions across several tunnel cross sections were plotted. The data were analyzed with respect to their rms value and power spectral density. A literature survey and an analytical investigation of the pulsations in a diffuser with nonviscous flow are included. (Author).
Download or read book NASA Scientific and Technical Reports written by United States. National Aeronautics and Space Administration Scientific and Technical Information Division and published by . This book was released on 1968 with total page 428 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Bibliography on Aerodynamics of Airframe engine Integration of High speed Turbine powered Aircraft Volume 1 written by and published by . This book was released on 1980 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Monthly Catalog of United States Government Publications Cumulative Index written by United States. Superintendent of Documents and published by . This book was released on 1970 with total page 1348 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book U S Government Research Development Reports written by and published by . This book was released on 1969-10 with total page 784 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Bibliography on Aerodynamics of Airframe engine Integration of High speed Turbine powered Aircraft written by Mark R. Nichols and published by . This book was released on 1980 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Reference Publication written by and published by . This book was released on 1977 with total page 1092 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Off design Drag and Performance of an Axisymmetric Inlet with 40 Percent Internal Contraction on Design written by Richard R. Woollett and published by . This book was released on 1974 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation determined the drag and pressure performance of an axisymmetric supersonic inlet when operated in the transonic speed range. The inlet configuration was derived from a Mach 2.5 mixed compression inlet design with assumed variable geometry. At typical engine airflows the drag coefficient varied from 0.057 to 0.192 when the Mach number changed from 0.80 to 1.27. The presence of a wing simulator resulted in a sizable increase in total drag at Mach 1.2. This interference drag, which is roughly a 0.1 increase in drag coefficient, originates equally from an increase in both additive and cowl pressure drag.
