NASA Scientific and Technical Aerospace Reports

spatial ability (Waller, 1999), several additional standardized metrics were utilized to assess process measures, including
spatial ability (Ekstrom, French, & Harman, 1976), navigation skill (Hegarty, Richardson, Montello, Lovelace, &
Subbiah, 2002) , workload (Hart & Staveland, 1988) , self-efficacy (Scott, 2000) and simulator sickness (Kennedy, Lane,
Serbaum, & Lilienthal, 1993). To assess terrain association skill, a test was developed in which participants were asked
to correlate out- the-window views with topographical maps and vice versa.
DTIC
Air Navigation; Education; Navigation; Space Perception; Spatial Distribution
05
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Includes all stages of design of aircraft and aircraft structures and systems. Also includes aircraft testing, performance, and evaluation,
and aircraft and flight simulation technology. For related information see also 18 Spacecraft Design, Testing and Performance; and 39
Structural Mechanics. For land transportation vehicles see 85 Technology Utilization and Surface Transportation.
20040068163 NASA Langley Research Center, Hampton, VA, USA
Wind Tunnel to Atmospheric Mapping for Static Aeroelastic Scaling
Heeg, Jennifer; Spain, Charles V.; Rivera, J. A.; [2004]; 12 pp.; In English; 45th AIAA/ASME/ASCE/AHS/ASC Structures,
Structural Dynamics and Materials Conference, 19-22 Apr. 2004, Palm Springs, CA, USA
Contract(s)/Grant(s): 23-762-20-31
Report No.(s): AIAA Paper 2004-2044; No Copyright; Avail: CASI; A03, Hardcopy
Wind tunnel to Atmospheric Mapping (WAM) is a methodology for scaling and testing a static aeroelastic wind tunnel
model. The WAM procedure employs scaling laws to define a wind tunnel model and wind tunnel test points such that the
static aeroelastic flight test data and wind tunnel data will be correlated throughout the test envelopes. This methodology
extends the notion that a single test condition - combination of Mach number and dynamic pressure - can be matched by wind
tunnel data. The primary requirements for affecting this extension are matching flight Mach numbers, maintaining a constant
dynamic pressure scale factor and setting the dynamic pressure scale factor in accordance with the stiffness scale factor. The
scaling is enabled by capabilities of the NASA Langley Transonic Dynamics Tunnel (TDT) and by relaxation of scaling
requirements present in the dynamic problem that are not critical to the static aeroelastic problem. The methodology is
exercised in two example scaling problems: an arbitrarily scaled wing and a practical application to the scaling of the Active
Aeroelastic Wing flight vehicle for testing in the TDT.
Author
Wind Tunnel Models; Atmospheric Models; Aeroelasticity; Wind Tunnel Tests
20040068182 NASA Ames Research Center, Moffett Field, CA, USA
CAD-Based Aerodynamic Design of Complex Configurations using a Cartesian Method
Nemec, Marian; Aftosmis, Michael J.; Pulliam, Thomas H.; December 15, 2003; 13 pp.; In English; 42nd AIAA Aerospace
Sciences Conference, 5-8 Jan. 2004, Reno, NV, USA
Report No.(s): AIAA Paper 2004-0113; No Copyright; Avail: CASI; A03, Hardcopy
A modular framework for aerodynamic optimization of complex geometries is developed. By working directly with a
parametric CAD system, complex-geometry models are modified nnd tessellated in an automatic fashion. The use of a
component-based Cartesian method significantly reduces the demands on the CAD system, and also provides for robust and
efficient flowfield analysis. The optimization is controlled using either a genetic or quasi-Newton algorithm. Parallel efficiency
of the framework is maintained even when subject to limited CAD resources by dynamically re-allocating the processors of
the flow solver. Overall, the resulting framework can explore designs incorporating large shape modifications and changes in
topology.
Author
Computer Aided Design; Aerodynamic Configurations; Optimization; Mathematical Models; Cartesian Coordinates;
Automatic Control
20040068309, Boeing Co., Wichita, KS, USA
Bonded Repair of Aircraft Composite Sandwich Structures
Tomblin, J. S.; Salah, L.; Welch, J. M.; Borgman, M. D.; Feb. 2004; In English
Report No.(s): PB2004-105463; No Copyright; Avail: National Technical Information Service (NTIS)
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