by National Aeronautics and Space Administration, Scientific and Technical Information Office, For sale by the National Technical Information Service] in [Washington, DC], [Springfield, Va .
Written in English
|Statement||Neal T. Frink.|
|Series||NASA technical memorandum -- 89101.|
|Contributions||United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.|
|The Physical Object|
Subsonic wind-tunnel measurements of a slender wing-body configuration employing a vortex flap A wind tunnel study at Mach was conducted for a slender wing-body configuration with a leading edge vortex flap of curved planform that is deflectable about a 74 degree swept hinge line. The basic data consist of a unique combination of longitudinal aerodynamic, surface pressure, and vortex flap. Subsonic wind-tunnel measurements of a slender wing-body configuration employing a vortex flap. By Neal T. Frink. Abstract. A wind tunnel study at Mach was conducted for a slender wing-body configuration with a leading edge vortex flap of curved planform that is deflectable about a 74 degree swept hinge line. The basic data consist of a Author: Neal T. Frink. A wind tunnel study at Mach was conducted for a slender wing-body configuration with a leading edge vortex flap of curved planform that is deflectable about a 74 degree swept hinge line. An illustration of an open book. Books. An illustration of two cells of a film strip. Video. An illustration of an audio speaker. Audio An illustration of a " floppy disk. DTIC ADA Two-Dimensional Subsonic Wind Tunnel Evaluation of Two Related Cambered 15 .
An open circuit suction subsonic wind tunnel with a working section of mm by mm and mm long. Package includes the Aerofoil with Tappings, a Three-Component Balance, two Differential Pressure Transducers, a Way Pressure Display Unit and data acquisition (VDAS-F). SUBSONIC WIND TUNNEL mm The complete starter set includes TecQuipment’s Subsonic Wind Tunnel (AF), the Basic Lift and Drag Balance (AFZ) and the Three-dimensional Drag Models (AFJ) - all parts needed for experiments in aerodynamic drag. The Wind Tunnel (AF). Fig. 1 Full model configuration Wind tunnel measurements The model is tested in a tri-sonic wind tunnel which test section dimensions are m2 and the length is m. The test conditions are variable from Mach to , the corresponding Reynolds number of the flow at the test section inlet varies from e06 to e6. Wind Tunnel Measurements. The wind tunnel measurements carried out cover all kinds of model structures and setups. This call for different ways of measuring response and flow parameters, and flexible measuring units are needed. All measuring units are connected to a desktop computer with a data acquisition board and several COM-ports.
For a subsonic wind tunnel, the test section is placed at the end of the contraction section and upstream of the diffuser. From a knowledge of the conservation of mass for subsonic flows, we can design the test section to produce a desired velocity or Mach number since the velocity is a function of the cross-sectional area. High subsonic wind tunnels () and transonic wind tunnels ( subsonic wind tunnels. The highest speed is reached in the test section. The Mach number is approximately 1 with combined subsonic and supersonic flow regions. However, any configuration is possible. As with all AEROLAB wind tunnels, exceptionally steady test section flow with close uniformity of velocity is standard. Turbulence level is typically below percent throughout the full tunnel speed range. Contact AEROLAB with your ideas (size, speed, shape) for a free, custom-made quote. This vehicle configuration is the result of a trade-off study involving several vehicle aeroshapes. As discussed in Ref., this was the configuration that features the best aerodynamic and aerothermodynamic performances at the same concept is conceived as a winged flying test bed (FTB) that will re-enter the Earth's atmosphere, thus allowing performing a number of experiments on.