Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

20000061449 British Aerospace Public Ltd. Co., Mathematical Modelling Dept., Bristol, UK
Rapid Aerodynamic Data Generation Using an Iterative Approximation Method
Toomer, C. A., British Aerospace Public Ltd. Co., UK; Aerodynamic Design and Optimisation of Flight Vehicles in a Concurrent
Multi-Disciplinary Environment; June 2000, pp. 33-1 - 33-11; In English; See also 20000061419; Original contains color illustrations;
Copyright Waived; Avail: CASI; A03, Hardcopy
Aerodynamic design and optimisation is a costly and complicated process in which numerically generated information about
the design space plays a vital role. Hence the information needs to be of good quality, i.e. describing the correct physics, and to
be easily accessible from databases using standardised formats. to make this process affordable and efficient, the codes must be
fast, robust and accurate. Aerodynamic design problems tend to involve a large number of design parameters and constraints on
the design. Large data sets are generated and so it is wise to automate the data generating and processing whenever possible. Data
generation is only part of the process. Efficient algorithms to access and interpret the data are required, as is an efficient means
of negotiating through the design space. Optimisation is the usual method by which the data are analysed, and regions within the
design space identified as possible design solutions or improvements to existing designs.
Author
Aerodynamics; Data Bases; Data Processing; Design Analysis; Optimization
20000061450 Naples Univ., Dipartimento di Progettazione Aeronautica, Italy
Design and Aerodynamic Optimization of a New Reconnaissance Very Light Aircraft through Wind-Tunnel Tests
Giordano, V., Naples Univ., Italy; Coiro, D. P., Naples Univ., Italy; Nicolosi, F., Naples Univ., Italy; DiLeo, L., Naples Univ., Italy;
Aerodynamic Design and Optimisation of Flight Vehicles in a Concurrent Multi-Disciplinary Environment; June 2000, pp. 34-1
- 34-8; In English; See also 20000061419; Copyright Waived; Avail: CASI; A02, Hardcopy
Design of a new Very Light Aircraft (V.L.A.) called G97 Spotter has been carried out at DPA (Department of Aeronautical
Engineering) and an extensive wind tunnel test campaign has been performed on both aircraft and airfoil models. Wind tunnel
tests have guided in the design phase allowing configuration optimization. Effects of nacelle and air intake shape, fuselage stretching,
wing incidence and flap/aileron effectiveness have been analyzed through wind tunnel tests. The airfoil has also been designed
and modified with the help of wind tunnel test results obtained for a model. Optimization of the airfoil leading edge shape has
been done and has brought to a sensible drag reduction at high speed conditions. Optimization of the air intake shape on the aircraft
model has been performed leading to a configuration characterized by lower drag. Influence of an air intake fairing has been analyzed
and tested through wind tunnel tests. Wing stall path has been studied. Importance of wind tunnel tests as a device to analyze
and design light aircraft configuration has been highlighted.
Author
Aerodynamic Stalling; Design Analysis; Ailerons; Aircraft Models; Drag Reduction; Light Aircraft; Optimization; Wind Tunnel
Tests
20000061965 Colorado Univ., Dept. of Aerospace Engineering Sciences, Boulder, CO USA
User’s Manual for LINER: FORTRAN Code for the Numerical Simulation of Plane Wave Propagation in a Lined Two-Dimensional
Channel
Reichert, R, S., Colorado Univ., USA; Biringen, S., Colorado Univ., USA; Howard, J. E., Colorado Univ., USA; Apr. 07, 1999;
55p; In English
Contract(s)/Grant(s): NAG1-1864; No Copyright; Avail: CASI; A04, Hardcopy; A01, Microfiche
LINER is a system of FORTRAN 77 codes which performs a 2D analysis of acoustic wave propagation and noise suppression
in a rectangular channel with a continuous liner at the top wall. This new implementation is designed to streamline the usage of
the several codes making up LINER, resulting in a useful design tool. Major input parameters are placed in two main data files,
input.inc and nurn.prm. Output data appear in the form of ASCII files as well as a choice of GNUPLOT graphs. Section 2 briefly
describes the physical model. Section 3 discusses the numerical methods; Section 4 gives a detailed account of program usage,
including input formats and graphical options. A sample run is also provided. Finally, Section 5 briefly describes the individual
program files.
Author
Applications Programs (Computers); Wave Propagation; User Manuals (Computer Programs); Numerical Analysis; Noise
Reduction
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