Decadal Survey of Civil Aeronautics Foundation for the Future (2006) / Chapter Skim
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A R&T Challenges for Aerodynamics and Aeroacoustics
A R&T Challenges for Aerodynamics and Aeroacoustics
Pages 71-88
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Appendixes
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Research radiation patterns. Key milestones include into improved techniques for propulsionairframe integration would improve aircraft flexibility and performance, es- · Validate the predictive capablity for 3-D mean and dypecially as aircraft speeds increase.
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74 DECADAL SURVEY OF CIVIL AERONAUTICS TABLE A-1 Prioritization of R&T Challenges for Area A: Aerodynamics and Aeroacoustics Strategic Objective Why NASA? s nt e nce yt ski orc lity rforma ronmeivn R S ecuri ucturert Sponsor of E Pe S e vel core Reliabi the native Le and with Spac ity Infras S lignment Composite and and es tot iorr A Alter iate ting P ority city iency gy of k ASA Pri fety fic er nergi ppor ppor ssion N Capa Sa Ef En Sy Su Su Mi Lac Appropr y R&T Challenge Weight 1 5 3 1 National /4 each Wh NASA A1 Integrated system performance through novel 9 3 9 9 9 9 132 3 9 3 9 6.0 792 propulsionairframe integration A2 Aerodynamic performance improvement through 9 3 9 9 3 3 120 3 9 3 9 6.0 720 transition, boundary layer, and separation control A3 Novel aerodynamic configurations that enable high 9 3 9 9 3 1 118 3 9 3 9 6.0 708 performance and/or flexible multimission aircraft A4a Aerodynamic designs and flow control schemes to 9 1 3 9 3 1 90 3 9 3 9 6.0 540 reduce aircraft and rotor noise A4b Accuracy of prediction of aerodynamic performance of complex 3-D configurations, including improved 3 3 9 3 3 3 72 9 9 3 9 7.5 540 boundary layer transition and turbulence models and associated design tools A6 Aerodynamics robust to atmospheric disturbances 9 9 3 1 9 1 112 3 9 3 3 4.5 504 and adverse weather conditions, including icing A7a Aerodynamic configurations to leverage advantages 3 1 9 9 3 1 78 3 9 9 3 6.0 468 of formation flying A7b Accuracy of wake vortex prediction, and vortex 9 9 3 1 1 1 104 3 9 3 3 4.5 468 detection and mitigation techniques A9 Aerodynamic performance for V/STOL and ESTOL, 9 3 3 1 3 1 76 3 9 3 9 6.0 456 including adequate control power A10 Techniques for reducing/mitigating sonic boom 3 1 3 9 3 1 60 9 9 3 9 7.5 450 through novel aircraft shaping A11 Robust and efficient multidisciplinary design tools 3 3 9 9 3 3 90 3 9 3 3 4.5 405 A12 Accurate predictions of thermal balance and techniques for the reduction of heat transfer to 1 1 3 1 9 9 40 9 9 3 9 7.5 300 hypersonic vehicles A13 Low-speed takeoff and landing flight characteristics 1 3 1 1 3 9 38 3 9 9 9 7.5 285 for access-to-space vehicles A14 Efficient control authority of advanced configurations to permit robust operations at hypersonic speeds and 1 1 3 1 9 9 40 3 9 3 9 6.0 240 for access-to-space vehicles A15 Decelerator technology for planetary entry 1 1 1 1 3 9 28 3 9 9 9 7.5 210 A16 Low-Reynolds-number and unsteady aerodynamics 1 1 3 1 9 3 34 3 9 3 9 6.0 204 for small UAVs A17 Low-drag airship designs to enable long-duration 1 3 1 3 9 1 42 3 3 3 9 4.5 189 stratospheric flight A18 Prediction of communication capability through reentry trajectory and techniques to mitigate impact of 1 1 1 1 9 9 34 3 9 3 3 4.5 153 communication blackouts A19 Aircraft protective countermeasures based on a range 1 3 1 1 9 1 36 3 3 3 3 3.0 108 of small deployed air vehicles
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ing distances, which is a critical challenge for V/STOL and ESTOL airplanes and for accommodating larger conven tional airplanes on existing runways. Flow control can also A2 Aerodynamic performance improvement through increase cruise efficiency, which reduces fuel usage even as transition, boundary layer, and separation control capability increases.
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: NASA possesses relevant tools is needed to move beyond empirical design tools.4 In wind tunnels, infrastructure, and computational infrastruc- addition, flight testing is a critical element of a successful ture. The tunnels permit high-Reynolds-number testing (e.g., research program in novel configurations.
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required are advances is the ability to predict rotor dynamic stall, to predict wake vortex dynamics, and to design rotor blades that minimize the time derivative of the blade's aero A4a Aerodynamic designs and flow control schemes to dynamic loading response to sharp-edged disturbances. Key reduce aircraft and rotor noise milestones include Reducing the aerodynamic noise from fixed- and rotarywing aircraft at or near airports is a long-term issue that must · Improve techniques for prediction and control of the be addressed to increase capacity at many airports.
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: The analysis tools will en performance of complex 3-D configurations, including able designs with higher aerodynamic efficiency and hence improved boundary layer transition and turbulence reduced fuel burn. models and associated design tools Synergy with National and Homeland Defense (3)
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wind tunnels and research aircraft that complement infra At present, wind-shear warning systems are built into structure in academia and industry. commercial aircraft, icing hazards are handled by regulatory Mission Alignment (9)
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: Formation flying may have some effect on into techniques to predict the formation, trajectory, and decay capacity through reduced takeoff weight, which will lead to of vortices needs to be performed. Key milestones include reduced spacing requirements and fewer noise-related restrictions.
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development of a low-drag, high-lift system, simple boundary layer control systems to prevent wing leading-edge separation, systems to provide pitch trim and control power at Why NASA? low speeds, a reversing deflecting exhaust nozzle, and wing design and fuselage shaping to reduce cruise drag in the tran- Supporting Infrastructure (3)
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disciplines have reached a level of maturity and fidelity that Key milestones include should be exploited by design tools. For example, aeroelastic design tools are now within reach that couple CFD and finite · Develop guidelines for allowable exposure of the pub- element analyses for full aircraft configurations.
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novel airframe configurations by comparing code pre- Relevant techniques include novel aerodynamic shaping, dictions with ground and flight tests. active flow control, transpiration cooling, and emissivity control.
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More accurate tools are A14 Efficient control authority of advanced needed to predict the effects of flow control, vehicle shap configurations to permit robust operations at ing, and propulsionairframe integration techniques on hypersonic speeds and for access-to-space vehicles boundary layer behavior and flow separation. In addition, integrated system analysis tools must be developed and vali- Hypersonic vehicles have the potential to provide afforddated to predict how modifications to improve takeoff and able access to space, safe and predictable entry from space, landing performance will affect vehicle performance flight in other planetary atmospheres, prompt global reach, throughout the flight profile.
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provide the required aerodynamic loads in a robust and reKey milestones include liable system while yielding efficient, low-mass thermal protection. · Develop techniques to accurately predict flow control Relevant research includes characterization of planetary authority in shock-dominated flows and in transitional atmospheric conditions and chemistry; development and flows.
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Aerodynamic issues of interest include boundary of these vehicles. Key milestones include layer transition prediction for flexible thin-wall hulls, pre diction of viscous drag in the regions of turbulent flow, · Generate and validate time-resolved experimental data boundary layer separation control, and unsteady aerodynam for highly unsteady low-Reynolds-number flows.
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Relshear and boundary layers, and the relationship between sig- evant technologies include flow control approaches for flight nal transmission and the flow physics. Several promising control in subsonic (and, perhaps, supersonic)
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ports relevant R&T, although it is focused on protecting mili tary aircraft. Relevance to Strategic Objectives Appropriate Level of Risk (3)
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