by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va .
Written in English
|Statement||P.J.W. Block and Garl L. Gentry, Jr|
|Series||NASA technical memorandum -- 85721|
|Contributions||Gentry, Garl L, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch|
|The Physical Object|
|Pagination||iii, 25 p. :|
|Number of Pages||25|
Tunnel Description ( m) long, 60 ft ( m) wide, and 32 ft ( m) Tunnel Circuit high. The floor was not removed for the test. There are two test bays which are indicated by the large circles The Langley 4- by 7-Meter Tunnel (formerly the in figure 3. The rear bay . An experimental and theoretical evaluation of the Langley 4- by 7- Meter Tunnel was conducted to determine its suitability for obtaining propeller noise data. The tunnel circuit and open test section are described. An experimental evaluation is performed using microphones placed in and on the tunnel : P. J. W. Block and Jr. G. L. Gentry. Evaluation of the Langley 4- by 7-meter tunnel for propeller noise measurements / By P. J. W. Block, Garl L. Gentry and United States. National Aeronautics and Space Administration. Facility.- The tests were conducted in the Langley 4- x 7-Meter Tunnel. This is a closed single-return atmospheric wind tunnel allowing open or closed test section operation. Amore detailed description of this facility and an acoustic evaluation of the open test section (OTS) are given in reference 2. Figure 7 is a.
The NASA Aircraft Noise Prediction Program improved Propeller Analysis System [microform] / L. Cathy Nguyen; Directivity and trends of noise generated by a propeller in a wake [microform] / P.J.W. Block and Carl L Evaluation of the Langley 4- by 7-meter tunnel for propeller noise measurements [microform] / P.J.W. Bl. Experimental data were obtained in the Langley 4 by 7 Meter Tunnel for a wing with various sweep angles, aspect ratios, and flap deflections both in and out of ground effect. A measurement scheme which permitted measurements of each of these configurations in the Langley 4- by 7-meter low speed tunnel is also described. View Show abstract. One approach to investigate propeller noise is to perform measurements in a wind tunnel. In the present paper, the process of designing and constructing a test stand for acoustic and aerodynamic measurements on model propellers in the small aeroacoustic wind tunnel at BTU Cottbus is shown. Thereby, special attention is paid to.
The design was a radical change from tunnels customarily built 5 feet in diameter. The foot, 8-bladed propeller was powered by two diesel submarine engines from the Navy. The foot stream of air reached miles per : Langley Research Center. Applied Acoustics 40 () Evaluation of Ship Radiated Noise Level from Near-Field Measurements Takaaki Musha Acoustics Department, Ono Sokki Co. Ltd, , Hakusan, Midori-ku, Yokohama, Japan & Akira Shinohara Faculty of Textile Science and Technology, Shinshu University, Ueda, Nagano-ken, Japan (Received 29 May revised manuscript Cited by: 4. NASA Langley research center's high temperature wind tunnel is used to test hypersonic aircraft as well as reentry systems and thermal protection systems. It is capable of sustaining speeds of. Langley full-scale tunnel investigation of the factors affecting the directional stability and trim characteristics of a.