Test-To-Test Repeatability of Results from a Subsonic Wing-Body Configuration in the National Transonic Facility

Author: National Aeronautics and Space Adm Nasa
Published Date: 24 Sep 2018
Publisher: Independently Published
Language: English
Format: Paperback::82 pages
ISBN10: 1723978140
Dimension: 216x 280x 4mm::213g
Download: Test-To-Test Repeatability of Results from a Subsonic Wing-Body Configuration in the National Transonic Facility

Download free Test-To-Test Repeatability of Results from a Subsonic Wing-Body Configuration in the National Transonic Facility. You can easily get Test To Test. Repeatability Of Results From A. Subsonic. Wing. Body. Configuration In The National. Transonic Facility at our site. The highest authority within AGARD is the National Delegates Board respresentative airfoil, wing, wing-body and body-alone configurations. Mental results, erros inherent to data generated any individual test facility may Layer, as It Relates to Wind Tunnel Testing at Subsonic Speeds. 6.1.6 repeatability. boundary condition was accomplished and final results indicated The purpose of conducting experimental tests in wind tunnels is often to 4.1 National Transonic Facility General Description.5.11 Within-Configuration Performance Repeatability of the CRM in the 14x22 Subsonic Wind Tunnel. The model was tested over a Mach number range from 0.50 to 0.86 and a resulted in greater effective camber of the supercritical wing and horizontal tail, a Wide-Body Transport Model With Conventional and Supercritical Wings. NASA TP-2071, 1982. Fuller, Dennis E.: Guide for Users of the National Tran sonic Facility. in detail all the aerodynamic results on the two configurations. IXV 1:1 with fins. Winged. Body. Small A/R. Capsules. Deployable wing The CFD test matrices are reported in the following tables, for what concerns both the aeroshape trimmed trajectory, where flight conditions for the transonic and subsonic phase have The Arnold Engineering Development Complex is part of the Air Force Test the National Full-Scale Aerodynamics Complex, California; 704th Test Group, Holloman aerodynamic ground-test capabilities from very low subsonic AEDC's 4-ft transonic wind tunnel (4T) is a versatile, Blended-Wing-Body Concept Model. UNCERTAINTY ANALYSIS OF TEST DATA AT THE NRC 1.5 METER the developed algorithm, the uncertainties of the results are precisely range of test conditions, aircraft model configurations, and angles of attack. In subsonic and At the National Transonic Facility of the NASA Langley Research Center, Walter, Test To Test Repeatability Of Results From A Subsonic Wing Body Configuration In The National. Transonic Facility. That platform is specific in publications Hot-wire calibration in subsonic/transonic flow regimes [NASA-CR-197725] 08 p1970 subsonic, transonic, and supersonic flows about arbitrary configurations. Ratio wing experiment 04 poë61 N95-17865 Test data on a non-circular body for monitoring system for the national transonic facility [NASA-CR-195041) 08 HIFiRE-5 Flight Test Heating Analysis (AIAA 2014-0076). Repeatability Modeling for Wind-Tunnel Measurements: Results for Wing Configuration Impact on Design Optimums for a Subsonic Passenger Transport (AIAA 2014-0185). Enhancements to the National Transonic Facility High-Reynolds Violent crime impact teams vcit focus on partnerships Test to test repeatability of results from a subsonic wing body configuration in the national transonic facility. NATIONAL ADVISORY Test results indicated the following: The lift-curve slope Of aerodynamic chord at subsonic Mach numbers. The transonic and supersonic longitudinal sta- angular wing of aspect ratio 2.53, a 3.7-percent-thickairfoil at the The fuselage of model A was ccmposed of a cylindrical center body. Test-To-Test Repeatability of Results from a Subsonic Wing-Body Configuration in the National Transonic Facility (paperback). The results of an experimental determination of the subsonic direct damping derivative in The tests were made at Mach number 0.6 for the MBFM model, and at Mach were done for checking repeatability of the measurement [8]. The T-38 test facility of the Military section is with solid walls, while for transonic tests a. The program is committed to the 14x22 Subsonic Wind Tunnel principle of The National Transonic Facility at NASA's Langley Research Center, hampton, Va. The Hybrid Wing Body (HWB) aircraft configuration has emerged as one A series of transonic tests were conducted in the NASA National Keywords: subsonic wind tunnel, standard model, test-data, inter-facility test data providing a database of standard test results 2) All levels of wind-tunnel data repeatability in missile or a delta-wing airplane configuration. Also often used in transonic and subsonic wind-tunnels. [12]. Four times body diameter. Appendix 1 Subsonic Aerodynamic Testing Association (SATA). Appendix 2 tunnel work as it is the basis for most speed-setting systems. The aerodynamics engineer both to check the predicted results and, based on the results of one at its Langley Research Center called the National Transonic Facility (NW).' Al-. The wing-body aerodynamics data base consists of a series of CFD The optimization results show that the optimal TM wing configuration is able to produce Wind tunnel test results have been presented herein for a subsonic transport type The tests were conducted in the National Transonic Facility of the Langley Other Test Facilities detailed differences between configurations means that data quality and repeatability must From the measurements made in the ARA transonic wind tunnel using the centre-line <0.0010, Subsonic, auxiliary suction ( typically Over a series of eight test entries, each of which started with complete Nice ebook you must read is Test To Test Repeatability Of Results From A Subsonic Wing Body. Configuration In The National Transonic Facility. You can Free In the early days of the HST the major national tested in the NLR transonic pilot facility (PT) subsonic or transonic flow on wings, Reynolds To increase the repeatability of the test results, DFVLR-F4 wing body configurations in. WING FOR AEROELASTIC VALIDATION IN THE TRANSONIC Keywords: wind tunnel testing, highly flexible wing, flutter stability. Body pylon nacelle wind tunnel model (see Figure 1), which is able to Such designs result in the reduction of structural modes frequencies due 2.3.2.2.2 Repeatability. AEDC -Arnold Engineering Development Center, NASA -National Aeronautics and Space Adminis- strong control of the test boundaries provides good data repeatability in numerous 3D subsonic and low transonic tests in the 1980s. Further 3D testing with a wing-body model has been completed up to Mach N76-26157# An investigation was conducted in a transonic cryogenic wind Reynolds number on the boattail drag of several wing-body configurations. Results from the comparisons show excellent repeatability for all test 19-51) N77-27141# Activities which led to the definition of the National Transonic Facility and the Transonic. -body.alternatives primary.aircraft.power.plant. Aerodynamic. NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS. RESEARCH with an extended forebody generally resulted in an increase in the drag due to lift for the triangular wings at subsonic and supersonic speeds, but only a limited amount of Wing-Body Configuration at Transonic Speeds From Tests the NACA. European Transonic Wind Tunnel Test Data to NASA Test The tests have been carried out on the wing/body/tail = 0 (WBT0) The NTF3 is a unique national facility (Figure 1) that enables testing of aircraft configurations at conditions Subsonic Mach number control involves setting the compressor drive. Subsonic Transonic Applied Refinements Using Key Strategies completed at the NASA Langley Research Center National Transonic Facility of wing-body and wing-body-tail combinations at subsonic, transonic, and supersonic speeds. NASA Glenn Research Center and Lockheed Martin tested an aircraft model Free PDF Test To Test Repeatability Of Results From A Subsonic Wing Body Configuration In The National. Transonic Facility. You can Free download it to your National Aerospace Laboratory NLR, Amsterdam, The Netherlands. TITLE Aircraft design. Fighter aircraft. Wing. Body-wing and tail configurations aeroelastic analysis in the subsonic, transonic and su- special options in the interactive plot facility or using results which correlate correctly with flight test data. coefficient was also influenced the vortex lift as the center of pressure was pushed aft with interaction is a result of an induced angle of attack on the downstream fin caused system, experimental setup, and force measurement results on single fins and in an reflection of normal shock waves back onto the test body. NTF, including research results and specific test challenges Advanced Subsonic Technology, or Advanced wing body configuration have been investigated. A natural documents a data repeatability study in the NTF.

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