2 edition of Wind tunnel performance test of coannular plug nozzles found in the catalog.
Wind tunnel performance test of coannular plug nozzles
Paul S. Staid
by National Aeronautics and Space Adiministration, Scientific and Technical Information Office, for sale by the National Technical Information Service in Washington, Springfield, Va
Written in English
|Statement||Paul S. Staid.|
|Series||NASA contractor report ; NASA CR-2990, NASA contractor report -- NASA CR-2990.|
|Contributions||United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.|
|The Physical Object|
|Pagination||viii, 107 p. :|
|Number of Pages||107|
With three suction type wind blowers, it can simulate wind speed from m/s all the way up to 11 m/s. For more information on wind tunnel . The High Speed Wind Tunnel is a blowdown-to-atmosphere, transonic-supersonic, adjustable-Mach-number facility. The general arrangement of the facility is shown in an aerial photograph in Figure A schematic drawing indicating wind tunnel circuit layout is provided as Figure Figure High Speed Wind Tunnel General Arrangement.
Wind Tunnel Operations Division Test Planning Guide for High Speed Wind Tunnels AXB2 Revision 5 Ap This is a controlled document. The ramjet engine is mounted to the exit nozzle of the Supersonic Wind Tunnel (SSWT). The duct area dimensions of the ramjet engine are inches wide by inches high to match the exit nozzle of the Super Sonic Wind Tunnel. The overall length of the ramjet engine is six feet long. The length is broken into three equal.
Low and high speed calibrations are available, as well as wind direction. Low Speed Test. Calibrations are performed in the range to 15 m/s. Our measurement uncertainty is ± m/s or ±1% (whichever is greater) at a 95% confidence level with a K coverage factor of 2 unless otherwise stated. High Speed Test. design variables of unsuppressed coannular plug nozzles through a systematic static acoustic and wind tunnel aerodynamic performance measurements. The variables considered were radius ratio, area ratio, inner stream plug geometry, inner and outer stream flow variables, and inner to outer stream velocity and weight-flow ratios.
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The test nozzles were mounted to a cm ( in.) diameter cylindrical sting which was supported in the test section by a perpendicular strut connected to the tunnel : Paul S. Staid. Wind tunnel performance test of coannular plug nozzles. Washington: National Aeronautics and Space Adiministration, Scientific and Technical Information Office ; Springfield, Va.: For sale by the National Technical Information Service, Wind tunnel performance test results and data analyses are presented for dual-flow plug nozzles applicable to supersonic cruise aircraft during takeoff and low-speed flight operation.
Outer exhaust stream pressure ratios from to were tested; inner exhaust stream conditions were varied from very low, or bleed flow rates, up to a pressure ratio of Author: P.
Staid. Wind tunnel performance test of coannular plug nozzles / By Paul S. Staid and United States. National Aeronautics and Space Administration.
Scientific and Technical Information Office. Abstract. Issued Apr. Prepared for Lewis Research Center, Cleveland, Ohio, under grant NASIncludes bibliographical of access. Wind tunnel tests were conducted to evaluate the aerodynamic performance of a coannular exhaust nozzle for a proposed variable stream control supersonic propulsion system.
Tests were conducted with two simulated configurations differing primarily in the fan duct flowpaths: a short flap mechanism for fan stream control with an isentropic contoured flow splitter, and an iris fan nozzle with a.
Tabulated data from wind tunnel tests conducted to evaluate the aerodynamic performance of an advanced coannular exhaust nozzle for a future supersonic propulsion system are presented. Tests were conducted with two test configurations: (1) a short flap mechanism for fan stream control with an isentropic contoured flow splitter, and (2) an iris fan nozzle with a conical flow splitter.
A graphical presentation of the aerodynamic data acquired during coannular nozzle performance wind tunnel tests is given. The graphical data consist of plots of nozzle gross thrust coefficient, fan nozzle discharge coefficient, and primary nozzle discharge coefficient. Normalized model component static pressure distributions are presented as a function of primary total pressure, fan total.
coe cient for each part in the wind-tunnel at a test section speed of 40 m/s. See table 2 and gure 2 for numbering of wind-tunnel parts. A closed circuit wind-tunnel gives better control of the ow conditions such as temperature and pressure and it also reduces the necessary power to run the.
The wind tunnel is driven by a kW ( HP), 69 m^3/s (, cfm) centrifugal fan [Show full abstract] controlled by a variable frequency drive.
Airflow enters the wind tunnel through a. Wind Tunnel testing a Bonneville Landspeed Bagger - Duration: A2 Wind Tun views. Trask Performance at Darko Technologies Wind Tunnel and test ride Wind tunnel test systems are characterized by their high channel count and high sampling frequencies.
A typical wind tunnel test system can therefore generate large amounts of data over a short time, requiring considerable computer processing power, and a high hard-disk performance. As an example, a. A typical nozzle-afterbody configuration is shown in the upper right for an F with experimental maneuvering nozzles.
As with the inlet design, the external nozzle configuration is often designed by the airframer and subjected to wind tunnel testing to determine the performance effects on the airframe.
The internal nozzle is usually the. this program. Figure 3 shows a coannular plug nozzle installed in the NASA 8' x 6' wind tunnel for aero performance testing. All the acoustics testing was carried out in the new General Electric anechoic jet noise facility.
However, given the enormous costs of the wind tunnel, they also want to explore a more. effective use of the current facility. An initial data collection reveals that: The standard fitting time for a cyclist is 2h. On average, the wind tunnel is used for 7. fitting procedures a day (new customers or customers who want a refit).
The wind. Figure 1. UIUC low-speed subsonic wind tunnel. Figure 2. Photograph of wind-tunnel test section. Experimental Facility and Flow Quality Measurements The low Reynolds number airfoil performance measurements described here were conducted in the UIUC low-turbulence subsonic wind tunnel shown in Fig.
The wind tunnel is an open-return type. Comprehensive data report. Volume 2: Tabulated aerodynamic data book 3. By D. Nelson. Abstract. Tabulated data from wind tunnel tests evaluating the aerodynamic performance of coannular exhaust nozzles are given for test runs 37 through Wind tunnel performance test results and data analyses are presented for dual-flow plug nozzles applicable to supersonic cruise aircraft during takeoff and low-speed flight operation.
Outer exhaust stream pressure ratios from to were tested; inner exhaust stream conditions were varied from very low, or bleed flow rates, up to a pressure ratio of Acoustic and aerothermal performance test of the axisymmetric coannular ejector nozzle.
[William Herkes; NASA Glenn Research Center.] Home. WorldCat Home About WorldCat Help. Search. Search # Wind tunnel tests\/span>\n \u00A0\u00A0\u00A0\n schema. Wind Tunnel Test DHAKA DESIGNER ASSET MANAGEMENT LIMITED. Method to visualize and setup Wind Tunnel simulation for comparing - Duration: Daniel Nielsen 2, views.
Homemade. The wind tunnel is a low speed-open loop and driven by a 2 kW, 4 m 3/s, axial flow fan. The main core of the designed wind tunnel is the long section ( m length) devoted to produce and simulate the atmospheric boundary layer (ABL) for various The wind tunnel test section is designed to.
Acoustic and Aerothermal Performance Test of the Axisymmetric Coannular Ejector Nozzle Volume IIuAcoustic Performance William Herkes The Boeing Commerical Airplane Group, Seattle, Washington Prepared under Contract NAS National Aeronautics and Space Administration Glenn Research Center February When the velocity reaches the speed of sound (M = 1), the flow chokes and the Mach number can not be increased beyond M = 1.
We want the highest possible velocity in the test section of the wind tunnel. For a supersonic wind tunnel, we contract the flow until it chokes in the throat of a nozzle. We then diffuse the flow which increases the.The full wind tunnel test evaluates the effectiveness of the candidate sampler at 2 km/hr and 24 km/hr for aerosols of the size specified in table F-2 of this subpart (under the heading, “Full Wind Tunnel Test”).
For each wind speed, a smooth curve is fit to the effectiveness data and corrected for the presence of multiplets in the wind.