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| Author | : Richard Frank Kilburg |
| Publisher | : |
| Total Pages | : |
| Release | : 1957 |
| Genre | : Harvesting machinery |
| ISBN | : |
| Author | : James C. Biggers |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1962 |
| Genre | : Aerodynamics |
| ISBN | : |
| Author | : John L. McCloud |
| Publisher | : |
| Total Pages | : 40 |
| Release | : 1963 |
| Genre | : Aerodynamics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 648 |
| Release | : 1973 |
| Genre | : Union catalogs |
| ISBN | : |
Includes entries for maps and atlases.
| Author | : GENERAL ELECTRIC CO CINCINNATI OHIO ADVANCED ENGINE AND TECHNOLOGY Dept |
| Publisher | : |
| Total Pages | : 414 |
| Release | : 1964 |
| Genre | : |
| ISBN | : |
The report presents the results from the wind tunnel tests of a 1/8-scale conventional model of the U.S. Army XV-5A Lift Fan Flight Research Aircraft. The tests were performed to determine the subsonic aerodynamic characteristics of the XV-5A in its conventional flight configuration. Volume I contains the tabulated force and moment data from the low speed (M = 0.285) tests.
| Author | : Edward Pearson Warner |
| Publisher | : |
| Total Pages | : 552 |
| Release | : 1925 |
| Genre | : Aerodynamics |
| ISBN | : |
The tests described herein were made in 1918, in the old four-foot wind tunnel at the Massachusetts Institute of Technology and at the request of the Engineering Division of the U.S. Army Air Service.
| Author | : |
| Publisher | : |
| Total Pages | : 648 |
| Release | : 1964 |
| Genre | : American literature |
| ISBN | : |
| Author | : W. Z. Stepniewski |
| Publisher | : Courier Corporation |
| Total Pages | : 640 |
| Release | : 2013-04-22 |
| Genre | : Technology & Engineering |
| ISBN | : 0486318516 |
DIVClear, concise text covers aerodynamic phenomena of the rotor and offers guidelines for helicopter performance evaluation. Originally prepared for NASA. Prefaces. New Indexes. 10 black-and-white photos. 537 figures. /div
| Author | : Philipp A. Lines |
| Publisher | : |
| Total Pages | : 99 |
| Release | : 2003-06-01 |
| Genre | : |
| ISBN | : 9781423501138 |
For over half a century the NPS Aerolab Low Speed Wind Tunnel located in Halligan Hall of the Naval Postgraduate school has served to provide students and facility with meaningful aerodynamic data for research and problem analysis. New data acquisition hardware was installed three years ago but never fully verified, and contained no integrated software program to collect data from the strain-gauge balance pedestal. Existing National Instruments based hardware for the NPS low-speed wind tunnel was reconfigured to obtain data from the strain- gauge pedestal. Additionally, a data acquisition software program was written in LabVIEW(C) to accommodate the hardware. The Virtual Instruments (VI) program collects and plots accurate data from all four strain gauges in real-time, producing non-dimensional force and moment coefficients. A research study on the performance of an OH-6A helicopter fuselage was conducted. NPS Aerolab wind tunnel tests consisted of drag, lift, and pitching moment measurements of the OH-6A along yaw and angle-of attack sweeps. The results of the NPS wind tunnel data were compared against testing conducted on a full-scale OH-6A helicopter in NASA Ames' 40 ft. x 80ft. wind tunnel, along with the U.S. Army's Light Observation Helicopter (LOH) wind tunnel tests. Results of current testing substantiate the LabVIEW(C) code.
| Author | : Michael Anthony Capasso |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1994 |
| Genre | : |
| ISBN | : |
This thesis reports on the construction of a 1/12th scale model of the award winning Arapaho attack helicopter design and wind tunnel test to determine both the model and full scale equivalent flat plate area. Tests were conducted for lg level flight and included yawed flight conditions up to 10 degrees. The significance of equivalent flat plate area for helicopters is that it is the principal parameter that establishes rotor propulsive force requirements. The Model was constructed from the original design submitted by the 1993 NPS Helicopter Design Team and is 47.5 inches long with a 48-inch main rotor diameter. The model was tested in the NPS Low Speed Wind Tunnel to measure the drag force on the main body of the model at wind tunnel velocities up to 72 knots. Drag force on the model was also measured with the rotor head and longbow radome installed, and at various yaw angles up to 10 degrees. The equivalent flat plate area was then calculated from these measurements and compared to other helicopters. Recommendations for further wind tunnel testing were made.
