Includes geosciences (general); earth resources and remote sensing; energy production and conversion; envi- Includes life sciences (general); aerospace medicine; 3043 For noise pollution see 45 Environment Pollution. Includes atomic structure, electron properties, and Includes light phenomena and optical devices. 3086 For related information see also 33 Electronics and Electrical Engineering and 36 Lasers and Masers. AUTHORS CONTRACT OR GRANT Sep. 1988 PUBLICATION DATE Stanley Fay, Stephen Gates, Timothy Henderson, Lester Sackett, (NASA-CR-172095; R-2088; NAS 1.26:172095) Avail: NTIS HC The second Control Of Flexible Structures Flight Experiment AVAILABILITY SOURCE xii SOURCE NATIONA ADMINISTRATION USA VOLUME 27 NUMBER 21 / NOVEMBER 8, 1989 Scientific and Technical Aerospace Reports A Semimonthly Publication of the National Aeronautics and Space Administration N89-26807# Air Force Systems Command, Wright-Patterson AFB, OH. Foreign Technology Div. ACTA AERONAUTICA ET ASTRONAUTICA SINICA, VOLUME 8, NUMBER 12, DECEMBER 1987 (SELECTED ARTICLES) 15 Feb. 1989 71 P Transl. into ENGLISH from Hangkong Xuebao (Peoples Republic of China), v. 8, no. 12, Dec. 1987 p 8557-8562, 8585-8593, and 8601-8610 (AD-A206782; FTD-ID(RS)T-0942-88) Avail: NTIS HC A04/MF A01 CSCL 01/2 Aircraft take off and landing gear are studied in order to understand nose wheel shimmy and provide measures to prevent it. It also deals with an analysis of runway dynamics and other such similar areas as nose wheel operation. Semi-Prepared Airfield and Design of Double-Action Shock Absorber: Airfields, in wars of the future, most necessarily suffer damage. To satisfy the peculiar demands of using this type of airfield, the design concepts of double action or double gas chamber shock shock absorbers. Moreover, as concerns their static and dynamic characteristics as well as the main parameters in the principles for their selection, it makes a relatively detailed comparative analysis. The settlement on standards for the unevenness of airfield runways, is based on the concept of power spectra. It introduces basic methods for measuring random variables from the unevenness of airfield runways. It drafts curves for the power spectra of uneven runways and carries out a preliminary analysis of the dynamic effects in aircraft ground surface taxing. GRA N89-26808*# National Aeronautics and Space Administration. Ames Research Center, Moffett Field, CA. SENSOR DEVELOPMENT PROGRAMS AT NASA AMES RESEARCH CENTER Y.-C. Cho Aug. 1989 8 p Presented at the International Society for Optical Engineering's 1989 Technical Symposia on Aerospace Sensing, Orlando, FL, 27-31 Mar. 1989 (NASA-TM-102217; A-89167; NAS 1.15:102217) Avail: NTIS HC A02/MF A01 CSCL 01B Two sensor development programs being conducted at the Fluid Mechanics Laboratory, NASA Ames Research Center are described, one in progress and the other being initiated. The ongoing program involves digital image velocimetry for velocity field measurements of time-dependent flows. The new program involves advanced acoustic sensors for wind tunnel applications. N89-26809# Author Naval Postgraduate School, Monterey, CA. Dept. of Administrative Sciences. ESTIMATING AND EXPLAINING THE PRODUCTION COST OF HIGH-TECHNOLOGY SYSTEMS: THE CASE OF MILITARY AIRCRAFT O. Douglas Moses 17 May 1989 85 p (AD-A208391; NPS54-89-07) Avail: NTIS HC A05/MF A01 CSCL 01/3 This study tests relationships between measures of the state-of-the-art of technology and advances in technology with production cost. The analysis is conducted using a sample of military aircraft. Parametric cost estimating models are developed. A wind tunnel test was conducted to evaluate the aerodynamic characteristics and wing pressure distributions of a variable wing sweep aircraft having wing panels that are modified to promote laminar flow. The modified wing section shapes were incorporated over most of the exposed outer wing panel span and were obtained by extending the leading edge and adding thickness to the existing wing upper surface forward of 60 percent chord. Two different wing configurations, one each for Mach numbers 0.7 and 0.8, tested on the model simultaneously, with one wing configuration on the left side and the other on the right. The tests were conducted at Mach numbers 0.20 to 0.90 for wing sweep angles of 20, 25, 30, and 35 degrees. Longitudinal, lateral and directional aerodynamic characteristics of the modified and baseline configurations, and selected pressure distributions for the modified configurations, are presented in graphical form without analysis. A tabulation of the pressure data for the modified configuration is available as microfiche. Author were N89-26811*# National Aeronautics and Space Administration. Langley Research Center, Hampton, VA. 14 P A PROCEDURE FOR COMPUTING SURFACE WAVE Equations are derived for computing surface waves on smooth surfaces, including surfaces with a nonuniform wave speed. The prior literature dealt primarily with the theoretical development with little consideration given to computational methods, and examples were limited to waves on surfaces of simple analytic description, such as cones, spheres, and cylinders. The computational procedure presented is a relatively general method. Sample |