Download or read book Transonic Mach Number Determination in a Blow down Wind tunnel with Solid Walls and a Downstream Throat written by W. J. Bannink and published by . This book was released on 1983 with total page 20 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 1985 with total page 1346 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1985 with total page 486 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
Download or read book NASA SP written by and published by . This book was released on 1986 with total page 544 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Determination of Transition Reynolds Number in the Transonic Mach Number Range written by and published by . This book was released on 1970 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents the results of an investigation to determine the transition Reynolds number characteristics of the Propulsion Wind Tunnel (16T) and the Aerodynamic Wind Tunnel (4T) by measuring the location of boundary-layer transition on a 10-deg total-angle cone. Boundary-layer thickness on the test section walls and test section noise levels were measured in an attempt to determine their influence on boundary-layer transition location. Transition Reynolds number decreased with increasing Mach number in both tunnels with a higher rate of change in Tunnel 4T. Transition Reynolds number decreased with increasing unit Reynolds number for free-stream Mach numbers or = 1.0 and alternated between decreasing and increasing with increasing unit Reynolds number for free-stream Mach numbers 1.0. Test results indicated that boundary-layer transition on the cone surface was affected by test section wall angle, wall porosity, and the noise radiating from the test section walls. The boundary-layer acoustic level, as measured on the cone surface, was relatively unaffected by transition location for subsonic Mach numbers. (Author).
Download or read book Effects of Parallel jet Mixing on Downstream Mach Number and Stagnation Pressure with Application to Engine Testing in Supersonic Tunnels written by Harry Bernstein and published by . This book was released on 1953 with total page 686 pages. Available in PDF, EPUB and Kindle. Book excerpt: A one-dimensional analysis of the results of the parallel-jet mixing encountered in the testing of engines in supersonic wind tunnels is reported. Equations were derived for determining the total pressure and Mach number behind the tunnel terminal shock. The method represents a simple procedure for determining these quantities while a tunnel is still in the design stage. A specific example of the method is included.
Download or read book Determination of Transition Reynolds Number in the Transonic Mach Number Range written by O. P. Credle and published by . This book was released on 1970 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents the results of an investigation to determine the transition Reynolds number characteristics of the Propulsion Wind Tunnel (16T) and the Aerodynamic Wind Tunnel (4T) by measuring the location of boundary-layer transition on a 10-deg total-angle cone. Boundary-layer thickness on the test section walls and test section noise levels were measured in an attempt to determine their influence on boundary-layer transition location. Transition Reynolds number decreased with increasing Mach number in both tunnels with a higher rate of change in Tunnel 4T. Transition Reynolds number decreased with increasing unit Reynolds number for free-stream Mach numbers or = 1.0 and alternated between decreasing and increasing with increasing unit Reynolds number for free-stream Mach numbers 1.0. Test results indicated that boundary-layer transition on the cone surface was affected by test section wall angle, wall porosity, and the noise radiating from the test section walls. The boundary-layer acoustic level, as measured on the cone surface, was relatively unaffected by transition location for subsonic Mach numbers. (Author).
Download or read book Government Reports Annual Index written by and published by . This book was released on 1985 with total page 966 pages. Available in PDF, EPUB and Kindle. Book excerpt: Sections 1-2. Keyword Index.--Section 3. Personal author index.--Section 4. Corporate author index.-- Section 5. Contract/grant number index, NTIS order/report number index 1-E.--Section 6. NTIS order/report number index F-Z.
Download or read book Government Reports Announcements Index written by and published by . This book was released on 1985 with total page 1224 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Choking Mach Number in High Speed Wind Tunnel with Consideration of the Model Lift written by Bernhard A.. Goethert and published by . This book was released on 1948 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Effect of Plenum Volume on the Test Section Flow Characteristics of a Perforated Wall Transonic Tunnel written by C. F. Anderson and published by . This book was released on 1970 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in the Aerodynamic Wind Tunnel (1T) of the Propulsion Wind Tunnel Facility to determine the effects of test section plenum chamber volume on the centerline Mach number distributions, wave-cancellation properties of perforated walls, model force data, and tunnel acoustics at Mach numbers from 0.6 to 1.3. Results were obtained with plenum chambers of four different sizes at plenum-to-test section volume ratios between 8.3 and 0.8. Reducing plenum volume produced no measurable effect at Mach numbers below 0.95. At Mach numbers above 0.95, decreasing the plenum volume increased the internal plenum losses, increased the plenum suction requirements, and increased the centerline Mach number deviations; however, the Mach number deviations were small at Mach numbers below 1.15. Reducing the plenum volume also produced a small increase in the effective wall porosity but had no measurable effect on measured model forces except to increase the forebody drag coefficient at Mach numbers above 1.05. Changes in the plenum volume had no significant effect on tunnel acoustics. (Author).
Download or read book High speed Wind Tunnels written by Luigi Crocco and published by . This book was released on 1946 with total page 236 pages. Available in PDF, EPUB and Kindle. Book excerpt: The importance assumed in recent times by experimental supersonic wind tunnels, as well as the power required, has brought about the need for a study which would permit a comparison of the types tested and the principal theoretical plans.
Download or read book Calibration of Transonic and Supersonic Wind Tunnels written by T. D. Reed and published by . This book was released on 1977 with total page 292 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Sidewall Mach Number Distributions for the NASA Langley Transonic Dynamics Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-11 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Transonic Dynamics Tunnel(TDT) was recalibrated due to the conversion of the heavy gas test medium from R-12 to R-134a. The objectives of the tests were to determine the relationship between the free-stream Mach number and the measured test section Mach number, and to quantify any necessary corrections. Other tests included the measurement of pressure distributions along the test-section walls, test-section centerline, at certain tunnel stations via a rake apparatus, and in the tunnel settling chamber. Wall boundary layer, turbulence, and flow angularity measurements were also performed. This paper discusses the determination of sidewall Mach number distributions.Florance, James R. and Rivera, Jose A., Jr.Langley Research CenterTRANSONIC WIND TUNNELS; CALIBRATING; FLOW MEASUREMENT; PRESSURE MEASUREMENT; TURBULENT FLOW; TEST CHAMBERS; PRESSURE DISTRIBUTION; MACH NUMBER; FREE FLOW
Download or read book Measurement of the Pressure Fluctuations in the Test Section of the 1 foot Transonic Tunnel in the Frequency Range from 5 to 1250 Cps written by J. E. Robertson and published by . This book was released on 1962 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Cumulative Index to a Continuing Bibliography on Aeronautical Engineering written by and published by . This book was released on 1986 with total page 554 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government Reports Annual Index Keyword A L written by and published by . This book was released on 1985 with total page 886 pages. Available in PDF, EPUB and Kindle. Book excerpt:
