A Wind Tunnel Investigation Of The Longitudinal Aerodynamic Charachteristics Of Two Full Scale Helicopter Fuselage Models With Appendages PDF Download
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Author | : Julian L. Jenkins |
Publisher | : |
Total Pages | : 46 |
Release | : 1962 |
Genre | : Aerodynamics |
ISBN | : |
Download A Wind-tunnel Investigation of the Longitudinal Aerodynamic Charachteristics of Two Full-scale Helicopter Fuselage Models with Appendages Book in PDF, ePub and Kindle
Author | : James C. Biggers |
Publisher | : |
Total Pages | : 44 |
Release | : 1962 |
Genre | : Aerodynamics |
ISBN | : |
Download Wind-tunnel Tests of Two Full-scale Helicopter Fuselages Book in PDF, ePub and Kindle
Author | : George E. Sweet |
Publisher | : |
Total Pages | : 54 |
Release | : 1962 |
Genre | : Drag (Aerodynamics) |
ISBN | : |
Download Wind-tunnel Investigation of the Drag and Static Stability Characteristics of Four Helicopter Fuselage Models Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 36 |
Release | : 1963 |
Genre | : |
ISBN | : |
Download Full-Scale Wind-Tunnel Investigation of the Drag Characteristics of an HU2K Helicopter Fuselage Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 132 |
Release | : 1963 |
Genre | : |
ISBN | : |
Download NASA Technical Note Book in PDF, ePub and Kindle
Author | : John L. McCloud |
Publisher | : |
Total Pages | : 40 |
Release | : 1963 |
Genre | : Aerodynamics |
ISBN | : |
Download Full-scale Wind-tunnel Tests of a Medium-weight Utility Helicopter at Forward Speeds Book in PDF, ePub and Kindle
Author | : Henry L. Kelley |
Publisher | : |
Total Pages | : 36 |
Release | : 1992 |
Genre | : Helicopters |
ISBN | : |
Download Two-dimensional Aerodynamic Characteristics of Several Polygon-shaped Cross-sectional Models Applicable to Helicopter Fuselages Book in PDF, ePub and Kindle
Author | : Robert J. Huston |
Publisher | : |
Total Pages | : 44 |
Release | : 1971 |
Genre | : Helicopters |
ISBN | : |
Download A Wind-tunnel Investigation of Helicopter Directional Control in Rearward Flight in Ground Effect Book in PDF, ePub and Kindle
An investigation was conducted in the Langley full-scale tunnel to study the aerodynamics that produce directional-control problems for a helicopter with a tail rotor in low-speed rearward flight in ground effect. A helicopter model mounted close to the tunnel floor was tested in tail winds from 0 to 25 knots.
Author | : James L. Williams |
Publisher | : |
Total Pages | : 736 |
Release | : 1956 |
Genre | : Helicopters |
ISBN | : |
Download Wind-tunnel Investigation of Effects of Fuselage Cross-sectional Shape, Fuselage Bend, and Vertical-tail Size on Directional Characteristics of Nonoverlap-type Helicopter Fuselage Models Without Rotors Book in PDF, ePub and Kindle
A low-speed investigatio was made in the Langley stability tunnel to determine the directional stability characteristics of tandem nonoverlap-type helicopter fuselages without rotors. The investigation consisted of a study of both bent and straight fuselages having either circular or essentially elliptical cross sections and with two vertical-tail sizes.
Author | : National Aeronautics and Space Adm Nasa |
Publisher | : |
Total Pages | : 34 |
Release | : 2018-10-15 |
Genre | : |
ISBN | : 9781728805993 |
Download Two-Dimensional Aerodynamic Characteristics of Several Polygon-Shaped Cross-Sectional Models Applicable to Helicopter Fuselages Book in PDF, ePub and Kindle
A wind-tunnel investigation was conducted to determine 2-D aerodynamic characteristics of nine polygon-shaped models applicable to helicopter fuselages. The models varied from 1/2 to 1/5 scale and were nominally triangular, diamond, and rectangular in shape. Side force and normal force were obtained at increments of angle of flow incidence from -45 to 90 degrees. The data were compared with results from a baseline UH-60 tail-boom cross-section model. The results indicate that the overall shapes of the plots of normal force and side force were similar to the characteristic shape of the baseline data; however, there were important differences in magnitude. At a flow incidence of 0 degrees, larger values of normal force for the polygon models indicate an increase in fuselage down load of 1 to 2.5 percent of main-rotor thrust compared with the baseline value. Also, potential was indicated among some of the configurations to produce high fuselage side forces and yawing moments compared with the baseline model. Kelley, Henry L. and Crowell, Cynthia A. and Wilson, John C. Langley Research Center DA PROJ. 1L2-36003-D-313; RTOP 505-59-36-01...