An Experimental Study Of Several Wind Tunnel Wall Configurations Using Two V Stol Model Configurations PDF Download
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Author | : T. W. Binion (Jr.) |
Publisher | : |
Total Pages | : 38 |
Release | : 1975 |
Genre | : Jet fighter planes |
ISBN | : |
Download An Experimental Study of Several Wind Tunnel Wall Configurations Using Two V/STOL Model Configurations Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 0 |
Release | : 1975 |
Genre | : |
ISBN | : |
Download An Experimental Study of Several Wind Tunnel Wall Configurations Using Two V/STOL Model Configurations Book in PDF, ePub and Kindle
Experiments were conducted in the low speed wind tunnel using two V/STOL models, a jet-flap and a jet-in-fuselage configuration, to search for a wind tunnel wall configuration to minimize wall interference on V/STOL models. Data were also obtained on the jet-flap model with a uniform slotted wall configuration to provide comparisons between theoretical and experimental wall interference. A test section configuration was found which provided some data in reasonable agreement with interference-free results over a wide range of momentum coefficients.
Author | : Travis W. Binion |
Publisher | : |
Total Pages | : 72 |
Release | : 1971 |
Genre | : Short take-off and landing aircraft |
ISBN | : |
Download An Investigation of Several Slotted Wind Tunnel Wall Configurations with a High Disk Loading V/STOL Model Book in PDF, ePub and Kindle
The investigation reported herein is the experimental portion of a unified theoretical and experimental search for a slotted wind tunnel wall configuration with minimal interference for conventional and V/STOL models. It is shown that theory and experiment are in excellent agreement for the classical case provided an appropriate expression is used to relate the wall geometry to the boundary condition. Classical data correction equations are not appropriate for the V/STOL case, however. An additional term, not predicted by theory, is needed to account for changes in the jet wake. Geometric parameters which influence the wall interference quantities are indicated. Wall configurations are shown which will produce interference-free force data to a jet-to-free-stream velocity ratio of 4.5. (Author).
Author | : Travis W. Binion |
Publisher | : |
Total Pages | : 0 |
Release | : 1971 |
Genre | : Short take-off and landing aircraft |
ISBN | : |
Download An Investigation of Several Slotted Wind Tunnel Wall Configurations with a High Disk Loading V/STOL Model Book in PDF, ePub and Kindle
The investigation reported herein is the experimental portion of a unified theoretical and experimental search for a slotted wind tunnel wall configuration with minimal interference for conventional and V/STOL models. It is shown that theory and experiment are in excellent agreement for the classical case provided an appropriate expression is used to relate the wall geometry to the boundary condition. Classical data correction equations are not appropriate for the V/STOL case, however. An additional term, not predicted by theory, is needed to account for changes in the jet wake. Geometric parameters which influence the wall interference quantities are indicated. Wall configurations are shown which will produce interference-free force data to a jet-to-free-stream velocity ratio of 4.5. (Author).
Author | : T. W Binion (Jr) |
Publisher | : |
Total Pages | : 65 |
Release | : 1971 |
Genre | : |
ISBN | : |
Download An Investigation of Several Slotted Wind Tunnel Wall Configurations with a High Disc Loading V/STOL Model Book in PDF, ePub and Kindle
The investigation reported herein is the experimental portion of a unified theoretical and experimental search for a slotted wind tunnel wall configuration with minimal interference for conventional and V/STOL models. It is shown that theory and experiment are in excellent agreement for the classical case provided an appropriate expression is used to relate the wall geometry to the boundary condition. Classical data correction equations are not appropriate for the V/STOL case, however. An additional term, not predicted by theory, is needed to account for changes in the jet wake. Geometric parameters which influence the wall interference quantities are indicated. Wall configurations are shown which will produce interference-free force data to a jet-to-free-stream velocity ratio of 4.5. (Author).
Author | : |
Publisher | : |
Total Pages | : 64 |
Release | : 1986 |
Genre | : Aeronautics |
ISBN | : |
Download NASA Technical Memorandum Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 972 |
Release | : 1988 |
Genre | : Aeronautics |
ISBN | : |
Download Scientific and Technical Aerospace Reports Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 882 |
Release | : 1975 |
Genre | : Government reports announcements & index |
ISBN | : |
Download Government Reports Annual Index Book in PDF, ePub and Kindle
Author | : T. W. Binion |
Publisher | : |
Total Pages | : 55 |
Release | : 1971 |
Genre | : Porosity |
ISBN | : |
Download An Investigation of Several Slotted Wind Tunnel Wall Configurations with a High Disk Loading V/STOL Model Book in PDF, ePub and Kindle
Author | : W. R. Sears |
Publisher | : |
Total Pages | : 184 |
Release | : 1986 |
Genre | : |
ISBN | : |
Download Experiments in an Adaptable-Wall Wind Tunnel for V/STOL Testing Book in PDF, ePub and Kindle
Experiments were carried out, over a period of two years, in an Adaptable-Wall wind tunnel configured for testing of airplane models at very large lift. The program was intended especially to demonstrate Proof of Concept for this type of wind tunnel, in which the simulated stream vector is inclined appreciably to the tunnel axis. The measured inner flow is matched to the computed, updated outer flow by an iterative process. Wall-adaptation controls in this tunnel are vaned panels in the floor and ceiling of the working section and a variable-angle inlet nozzle. Velocity components are measured by a Laser-Doppler system using a fixed laser and movable optical components. The test model used in these experiments was a high-wing V/STOL configuration having full-span wing flaps with lower-surface blowing of their inboard portions. In all of the experiments reported here, the combination of angle of attack, flap setting, and flap blowing was such as to produce large flow deflection and severe wall interference in a conventional tunnel. The model configuration was always laterally symmetrical, and most runs were made under the assumption of symmetrical flow. The iterative procedure, based on measured control matrices, typically led to minimum matching-discrepancies (root-mean-square values) of about three percent of stream speed after about six iterations. It is estimated that this reflects residual errors at the model of about one percent of stream speed. It is concluded that these results constitute successful Proof of Concept. Suggestions are made regarding the directions of further development of this type of wind tunnel. (Author).