SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS
A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 43, ISSUE 18 - SEPTEMBER 09, 2005
05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE - PART II
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.
20050207342 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
Fighter Pilot Inventory and Requirements Model; A Ten Year Look with Impact of UAV Increase
Garner, Russell S.; Villem, Paul A.; Jun. 2005; 63 pp.; In English; Original contains color illustrations Report No.(s): AD-A436323; AFIT/EN/TR-05-02; No Copyright; Avail: CASI; A04, Hardcopy
Historically, managing fighter pilot requirements has been a continual challenge for the Air Force Personnel Center. In recent years, Unmanned Aerial Vehicles have become a highly sought after commodity, and the number of UAV billets have increased, with more increases expected in the near future. Currently 45% of UAV squadrons are manned by combat aircrew. Fighter pilots fills the majority of these slots. This dramatic increase in UAV requirements demands analysis for the impact on fighter pilot requirements. An increase in UAV fighter pilot billets represents a direct increase in force requirements, however, there may be an indirect effect on training and man year requirements. DTIC
Drone Vehicles; Inventories; Models; Personnel Management; Pilots
20050207358 Naval Surface Warfare Center, Dahlgren, VA USA
A Definitive Work on Factors Impacting the Arming of Unmanned Vehicles
Canning, John S.; May 2005; 48 pp.; In English Report No.(s): AD-A436214; NSWCDD/TR-05/36; No Copyright; Avail: CASI; A03, Hardcopy
We realize that the weaponizing of unmanned vehicles (UXVs) takes us into largely uncharted waters. This document is an attempt to examine as many of the issues surrounding this area as possible. DTIC
Combat; Weapons; Unmanned Ground Vehicles; Command and Control
20050207436 NASA Glenn Research Center, Cleveland, OH, USA
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Geometry and Reynolds-Number Scaling on an Iced Business-Jet Wing
Lee, Sam; Ratvasky, Thomas P.; Thacker, Michael; Barnhart, Billy P.; August 2005; 20 pp.; In English; 43rd Aerospace Sciences Meeting and Exhibit, 10-13 Jan. 2005, Reno, NV, USA Contract(s)/Grant(s): WBS 22-077-41-09 Report No.(s): NASA/TM-2005-213575; AIAA Paper 2005-1066; E-15034; No Copyright; Avail: CASI; A03, Hardcopy
A study was conducted to develop a method to scale the effect of ice accretion on a full-scale business jet wing model to a 1/12-scale model at greatly reduced Reynolds number. Full-scale, 5/12-scale, and 1/12-scale models of identical airfoil section were used in this study. Three types of ice accretion were studied: 22.5-minute ice protection system failure shape, 2-minute initial ice roughness, and a runback shape that forms downstream of a thermal anti-ice system. The results showed that the 22.5-minute failure shape could be scaled from full-scale to 1/12-scale through simple geometric scaling. The 2-minute roughness shape could be scaled by choosing an appropriate grit size. The runback ice shape exhibited greater Reynolds number effects and could not be scaled by simple geometric scaling of the ice shape. Author
General Aviation Aircraft; Scale Effect; Reynolds Number; Aircraft Icing; Wings
20050207465 NASA Marshall Space Flight Center, Huntsville, AL, USA
Transient Three-Dimensional Analysis of Nozzle Side Load in Regeneratively Cooled Engines
ng, Ten-See; May 26, 2005; 31 pp.; In English; 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 10-13 Jul. 2005, Tucson, AZ, USA Report No.(s): AIAA Paper 2005-3942; No Copyright; Avail: CASI; A03, Hardcopy
Nozzle side loads are potentially detrimental to the integrity and life of almost all launch vehicles. the lack of a detailed prediction capability results in reducing life and increased weight for reusable nozzle systems. A clear understanding of the mechanism that contribute to side loads during engine startup, shutdown, and steady-state operations must be established. A CFD based predictive tool must be developed to aid the understanding of side load physics and development of future reusable engine. Derived from text
Nozzle Efficiency; Three Dimensional Models; Regenerative Cooling
20050209958 NASA Langley Research Center, Hampton, VA, USA
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Aerodynamic Parameter Estimation for the X-43A (Hyper-X) from Flight Data
Morelli, Eugene A.; Derry, Stephen D.; Smith, Mark S.; [2005]; 15 pp.; In English; AIAA Atmospheric Flight Mechanics Conference and Exhibit, 15-18 Aug. 2005, San Francisco, CA, USA Contract(s)/Grant(s): 23-723-63-5L Report No.(s): AIAA Paper 2005-5921; No Copyright; Avail: CASI; A03, Hardcopy
Aerodynamic parameters were estimated based on flight data from the third flight of the X-43A hypersonic research vehicle, also called Hyper-X. Maneuvers were flown using multiple orthogonal phase-optimized sweep inputs applied as simultaneous control surface perturbations at Mach 8, 7, 6, 5, 4, and 3 during the vehicle descent. Aerodynamic parameters, consisting of non-dimensional longitudinal and lateral stability and control derivatives, were estimated from flight data at each Mach number. Multi-step inputs at nearly the same flight conditions were also flown to assess the prediction capability of the identified models. Prediction errors were found to be comparable in magnitude to the modeling errors, which indicates accurate modeling. Aerodynamic parameter estimates were plotted as a function of Mach number, and compared with estimates from the pre-flight aerodynamic database, which was based on wind-tunnel tests and computational fluid dynamics. Agreement between flight estimates and values computed from the aerodynamic database was excellent overall. Author
Aerodynamic Characteristics; X-43 Vehicle; Flight Characteristics; Data Acquisition; Mathematical Models
20050209961 NASA Langley Research Center, Hampton, VA, USA
Longitudinal Aerodynamic Characteristics and Wing Pressure Distributions of a Blended-Wing-Body Configuration at Low and High Reynolds Numbers
Re, Richard J.; August 2005; 108 pp.; In English Contract(s)/Grant(s): WU 23-714-80-VG Report No.(s): NASA/TM-2005-213754; L-19113; No Copyright; Avail: CASI; A06, Hardcopy
Force balance and wing pressure data were obtained on a 0.017-Scale Model of a blended-wing-body configuration (without a simulated propulsion system installation) to validate the capability of computational fluid dynamic codes to predict the performance of such thick sectioned subsonic transport configurations. The tests were conducted in the National Transonic Facility of the Langley Research Center at Reynolds numbers from 3.5 to 25.0 million at Mach numbers from 0.25 to 0.86. Data were obtained in the pitch plane only at angles of attack from -1 to 8 deg at Mach numbers greater than 0.25. A configuration with winglets was tested at a Reynolds number of 25.0 million at Mach numbers from 0.83 to 0.86. Author
Aerodynamic Characteristics; Scale Models; Pressure Distribution; Wings; Blended-Wing-Body Configurations
20050209967 Research and Technology Organization, Neuilly-sur-Seine, France
Introduction to Flight Test Engineering, Volume 14
Stoliker, Fred N.; July 2005; 456 pp.; In English; See also 20050209968 - 20050210000 Report No.(s): RTO-AG-300-Vol-14; AC/323(SCI-FT3)TP/74-Vol-14; Copyright; Avail: CASI; C01, CD-ROM; A20, Hardcopy
Flight test is at the core of what organizations must do in order to validate the operation and systems on an aircraft. While the AGARDograph series 300 and 160 series deal with aspects of this testing, this volume pulls it all together as an introduction to the process required to do effective flight test engineering.
This volume was originally published in 1995. Its utility has been proven in that many flight test organizations and universities have requested copies for their engineers and students. It was felt that re-issuing it in a new format designed for electronic publication would be valuable to the community. This second printing changes none of the text, but rather reformats it. All the original references to AGARD (instead of RTO) are left in place so that none of the flavor of the original publication is lost.
This is the Introductory Volume to the Flight Test Techniques Series. It is a general introduction to the various activities and aspects of Flight Test Engineering that must be considered when planning, conducting, and reporting a flight test program. Its main intent is to provide a broad overview to the novice engineer or to other people who have a need to interface with specialists within the flight test community.
The first two Sections provide some insight into the question of why flight test and give a short history of flight test engineering. Sections 3 through 10 deal with the preparation for flight testing. They provide guidance on the preliminary factors that must be considered; the composition of the test team; the logistic support requirements; the instrumentation and data processing requirements; the flight test plan; the associated preliminary ground tests; and last, but by no means least, discuss safety aspects. Sections 11 through 27 describe the various types of flight tests that are usually conducted during the development and certification of a new or modified aircraft type.
Each Section offers a brief introduction to the topic under consideration, and the nature and the objectives of the tests to be conducted. It lists the test instrumentation (and, where appropriate, other test equipment and facilities) required, describes the test maneuvers to be executed, and indicates the way in which the test data is selected, analyzed, and presented. The various activities that should take place between test flights are presented next.
Items that are covered are: who to debrief; what type of reports to send where: types of data analysis required for next flight; review of test data to make a comparison to predicted data and some courses of action if there is not good agreement; and comments on selecting the next test flight. The activities that must take place upon completion of the test program are presented. The types of reports and briefings that should take place and a discussion of some of the uses of the flight test data are covered. A brief forecast is presented of where present trends may be leading. Author
Flight Tests; Data Processing; Ground Tests
20050209969 Test Wing (0046th), Eglin AFB, FL, USA
Armament Testing and Stores Separation, Chapter 25
Mosher, Raymond E.; Introduction to Flight Test Engineering, Volume 14; July 2005, pp. 25-1 - 25-5; In English; See also 20050209967; Copyright; Avail: CASI; A01, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document
To ensure that specified weapons and stores (bombs, missiles, pods, guns, and fuel tanks) will safely and successfully operate from a particular aircraft platform, compatibility flight testing is usually required. The objective of this testing is to demonstrate that the aircraft can fire its gun and carry its intended stores safely and satisfactorily and achieve the required levels of maneuverability and performance for each stores configuration. In addition, the store must be capable of withstanding the captive flight environment, separate cleanly, and follow a predictable trajectory to its target. Note that aircraft limits and the flight envelope may be significantly reduced when carrying stores. Before beginning any tests or analyses, checks must be accomplished to assure that the store configuration selected is physically compatible with the aircraft. This initial fit test, using scale drawings, is often referred to as a ‘paper fit check’. If the configuration passes the paper fit test, an ‘all-up fit check’ using the actual hardware should be conducted as early as possible using the standardized fit test procedures specified in MIL-STD-1289. Derived from text
Captive Tests; External Store Separation; Flight Tests; Missiles; Pods (External Stores)
20050209971 Aeroplane and Armament Experimental Establishment, Boscombe Down, UK
Introduction, Chapter 1
Appleford, J. K.; Introduction to Flight Test Engineering, Volume 14; July 2005, pp. 1-1 - 1-4; In English; See also 20050209967; Copyright; Avail: CASI; A01, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document
This AGARDograph is intended, as the title and Foreword indicate, to provide an introduction to flight test engineering. It is aimed at personnel entering the field with little or no prior experience of the subject, and those whose work in other branches of aeronautics requires them to have an appreciation of the issues involved. Hence, it concentrates on the more universally applicable aspects of the subject which will be encountered during the development and certification of any new aircraft design. This Section ‘sets the scene’ by offering some background on, and justification for, flight testing and outlining the differences between ‘development’ and ‘certification’ testing. Derived from text
Flight Tests; Certification; Engineering
20050209977 Naval Air Warfare Center, Patuxent River, MD, USA
Post-Test Operations, Chapter 29
Oblen, Ronald J.; Introduction to Flight Test Engineering, Volume 14; July 2005, pp. 29-1 - 29-7; In English; See also 20050209967; Copyright; Avail: CASI; A02, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document
Once a flight test program is completed there is normally a series of briefings and reporting requirements that must be met. This section will describe, in general terms, the briefings one should be prepared to perform, the types of reports that may be required including preparation of the final technical report, and data that can be provided for handbooks, simulators, and operator’s manuals. Be sure to refer to and use your present organization’s guides/requirements for reporting. Derived from text
Flight Tests; Handbooks; Simulators
20050209978 Air Force Flight Test Center, Edwards AFB, CA, USA
Testing under Environmental Extremes, Chapter 18
Ford, James A.; Introduction to Flight Test Engineering, Volume 14; July 2005, pp. 18-1 - 18-5; In English; See also 20050209967; Copyright; Avail: CASI; A01, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document
This section presents the typical elements of the test conduct phase of all-weather flight and ground testing. The following paragraphs will familiarize the reader with the purpose of all-weather testing, how the test vehicle is evaluated, and what the products of this type of testing are. The specific examples given in this Section will illustrate the approach taken and the tools used by the USA Air Force; however, they are exemplary of those used by other test organizations. Author
All-Weather Air Navigation; All-Weather Landing Systems; Flight Tests
Source: NASA.
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