Experiment of an Auxiliary Restart Method for Hypersonic Inlet with Variable-Bleed System

No AccessTechnical NotesInvestigation of Hysteresis Loop in the Starting Process of Supersonic CascadeShuying Zhang, Ling Zhou and Lucheng JiShuying ZhangBeijing Institute of Technology, 100081 Beijing, People’s Republic of China*Graduate Student, School of Aerospace Engineering; .Search for more papers by this author, Ling ZhouBeijing Institute of Technology, 100081 Beijing, People’s Republic of China†Associate Professor, School of Aerospace Engineering; (Corresponding Author).Search for more papers by this author and Lucheng JiTsinghua University, 100084 Beijing, People’s Republic of China‡Professor, Institute of Aero Engine; .Search for more papers by this authorPublished Online:11 Jan 2022https://doi.org/10.2514/1.J061232SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About References [1] Kantrowitz A., “The Formation and Stability of Noemal Shock Waves in Channel Flows,” NACA TN 1225, 1947. Google Scholar[2] Kantrowitz A. and Donaldson C., “Preliminary Investigation of Supersonic Diffusers,” NACA ACR-L5D20, 1945. Google Scholar[3] Van Wie D. M., Kwok F. T. and Walsh R. F., “Starting Characteristics of Supersonic Inlets,” AIAA Paper 1996-2914, 1996. https://doi.org/10.2514/6.1996-2914 LinkGoogle Scholar[4] Tahir R. B., Molder S. and Timofeev E. V., “Unsteady Starting of High Mach Number Air Inlets-A CFD Study,” AIAA Paper 2003-5191, 2003. https://doi.org/10.2514/6.2003-5191 LinkGoogle Scholar[5] Molder S., Timofeev E. V. and Tahir R. B., “Flow Starting in High Compression Hypersonic Air Inlets by Mass Spillage,” AIAA Paper 2004-4130, 2004. https://doi.org/10.2514/6.2004-4130 Google Scholar[6] Najafiyazdi A., Tahir R., Timofeev E. V. and Molder S., “Analytical and Numerical Study of Flow Starting in Supersonic Inlets by Mass Spillage,” AIAA Paper 2007-5072, 2007. https://doi.org/10.2514/6.2007-5072 Google Scholar[7] Timofeev E. V., Tahir R. B. and Molder S., “On Recent Development Related to Flow Starting in Hypersonic Air Intakes,” AIAA Paper 2008-2512, 2008. https://doi.org/10.2514/6.2008-2512 Google Scholar[8] Graham R. C., Klapproth J. F. and Barina F. J., “Investigation of Off-Design Performance of Shock-in-Rotor Type Supersonic Blading,” NACA RM-E51C22, 1951. Google Scholar[9] Qiu M., “Investigation of Shock Organization in Axial Compressor Passages of high Pressure Ratio,” Ph.D. Thesis, Nanjing Univ. of Aeronautics and Astronautics, Nanjing, China, 2014. Google Scholar[10] Ning F. F., “Numerical Simulation of Internal Flow in Transonic Compressor Considering Real Geometric Complexity,” Ph.D. Dissertation, Beijing Univ. of Aeronautics and Astronautics, Beijing, 2002. Google Scholar[11] Ning F. F., “MAP: A CFD Package for Turbomachinery Flow Simulation and Aerodynamic Design Optimization,” ASME Paper GT2014-26515, 2014. https://doi.org/10.1115/gt2014-26515 Google Scholar[12] Edwards J. R., “A Low-Diffusion Flux Splitting Scheme for Navier-Stokes Calculations,” Computers and Fluids, Vol. 26, No. 6, 1997, pp. 635–659. https://doi.org/10.1016/S00-7930(97)00014-5 Google Scholar[13] Ju P. F. and Ning F. F., “Numerical Study of Near-Stall Flow Feature on Transonic Compressor,” Journal of Propulsion Technology, Vol. 37, No. 6, 2016, pp. 1055–1064. https://doi.org/10.13675/j.cnki.tjjs.2016.06.00 Google Scholar[14] Tweedt D. L., Schreiber H. A. and Starken H., “Experimental Investigation of the Performance of a Supersonic Compressor Cascade,” Journal of Turbomachinery, Vol. 110, No. 4, 1988, pp. 456–466. https://doi.org/10.1115/1.3262219 Google Scholar[15] Piovesan T., Magrini A. and Benini E., “Accurate 2-D Modelling of Transonic Compressor Cascade Aerodynamics,” Aerospace, Vol. 6, No. 5, 2019, pp. 57–76. https://doi.org/10.3390/aerospace6050057 CrossrefGoogle Scholar[16] Schreiber H. A. and Starken H., “An Investigation of a Strong Shock-Wave Turbulent Boundary Layer Interaction in a Supersonic Compressor Cascade,” Journal of Turbomachinery, Vol. 114, No. 3, 1992, pp. 494–503. https://doi.org/10.1115/1.2929170 CrossrefGoogle Scholar[17] Fleeter S., Holtman R. and Mcclure R. B., “Experimental Investigation of a Supersonic Compressor Cascade,” ARL TR-75-0208, Washington, D.C., 1975. Google Scholar[18] Jiang X., Qiu M. and Fan Z. L., “Effect of Supersonic Compressor Cascade Throat on Flow Pattern and Cascade Performance,” Acta Aeronautica et Astronautica Sinica, Vol. 38, No. 3, 2017, Paper 120308. https://doi.org/10.7527/S1000-6893.2016.0195 Google Scholar Previous article Next article FiguresReferencesRelatedDetailsCited byAerodynamic Characteristics of Morphing Supersonic Cascade Under Low-Upstream-Mach-Number ConditionChenzhang Li, Tianyu Pan, Zhaoqi Yan, Mengzong Zheng, Qiushi Li and Earl H. Dowell23 December 2022 | AIAA Journal, Vol. 0, No. 0 What's Popular Volume 60, Number 4April 2022 CrossmarkInformationCopyright © 2021 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-385X to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp. TopicsAerodynamicsAeronautical EngineeringAeronauticsComputational Fluid DynamicsFlow RegimesFluid DynamicsFluid MechanicsMagnetic PropertiesMaterial PropertiesMaterials and Structural MechanicsOblique Shock WaveShock WavesTurbulenceTurbulence Models KeywordsHysteresis LoopsAerodynamic SimulationCompressible FluidOblique ShockNumerical SimulationTurbulence ModelsCurved ShocksMach ReflectionStatic PressureTurbomachineryAcknowledgmentsThis work was supported by the National Natural Science Foundation of China (Grant No. 51976010) and the National Major Science and Technology Projects of China (2017-II-0006-0020, 2017-II-0001-0013, J2019-II-0003-0023). We sincerely thank Ning Fangfei, Beihang University, for providing computational fluid dynamics code MAP-S1.PDF Received1 September 2021Accepted2 December 2021Published online11 January 2022

Optimal Tolerance Allocation in Blade Manufacturing by Sensitivity-Based Performance Impact Evaluation

Comparison of Discharge Characteristics of a Hall Thruster with Different Cathode Arrangements

Unsteady Vortex Structure Induced by a Trielectrode Sliding Discharge Plasma Actuator

Performance Impact of Manufacturing Variations for Multistage Steam Turbines

Novel Technique to Determine SparkJet Efficiency

Phased array beamforming results of the F31/A31 historical baseline counter-rotating open rotor blade set were investigated for measurement data taken on the NASA Counter-Rotating Open Rotor Propulsion Rig in the 9- by 15-Foot Low-Speed Wind Tunnel of NASA Glenn Research Center as well as data produced using the LINPROP open rotor tone noise code. The planar microphone array was positioned broadside and parallel to the axis of the open rotor, roughly 2.3 rotor diameters away. The results provide insight as to why the apparent noise sources of the blade passing frequency tones and interaction tones appear at their nominal Mach radii instead of at the actual noise sources, even if those locations are not on the blades. Contour maps corresponding to the sound fields produced by the radiating sound waves, taken from the simulations, are used to illustrate how the interaction patterns of circumferential spinning modes of rotating coherent noise sources interact with the phased array, often giving misleading results, as the apparent sources do not always show where the actual noise sources are located. This suggests that a more sophisticated source model would be required to accurately locate the sources of each tone. The results of this study also have implications with regard to the shielding of open rotor sources by airframe empennages.

Exploring Airfoil Tonal Noise Reduction with Elastic Panel Using Perturbation Evolution Method

No AccessEngineering NotesEfficient Linear Modeling Method of Carrier Landing Flight DynamicsRan Dong, Xingchao Shao, Lipeng Wang, Guoxin Zhao and Xinyi ZhouRan DongBeijing Institute of Petrochemical Technology, 102617 Beijing, People’s Republic of China*Lecturer, College of Information Engineering; (Corresponding Author).Search for more papers by this author, Xingchao ShaoHarbin Engineering University, 150001 Harbin, Heilongjiang, People’s Republic of China†Lecturer, College of Intelligent Systems Science and Engineering; .Search for more papers by this author, Lipeng WangHarbin Engineering University, 150001 Harbin, Heilongjiang, People’s Republic of China‡Lecturer, College of Intelligent Systems Science and Engineering; .Search for more papers by this author, Guoxin ZhaoBeijing Institute of Petrochemical Technology, 102617 Beijing, People’s Republic of China§Professor, College of Information Engineering; .Search for more papers by this author and Xinyi ZhouBeijing Institute of Petrochemical Technology, 102617 Beijing, People’s Republic of China¶Undergraduate Student, College of Information Engineering; .Search for more papers by this authorPublished Online:30 Aug 2021https://doi.org/10.2514/1.C036404SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About References [1] Hess R. A., “Providing Flight-Path Control Bandwidth for Carrier Landings,” Journal of Aircraft, Vol. 55, No. 1, 2018, pp. 406–409. https://doi.org/10.2514/1.C034596 LinkGoogle Scholar[2] Zhen Z., Jiang S. and Jiang J., “Preview Control and Particle Filtering for Automatic Carrier Landing,” IEEE Transactions on Aerospace and Electronic Systems, Vol. 54, No. 6, 2018, pp. 2662–2674. https://doi.org/10.1109/TAES.2018.2826398 CrossrefGoogle Scholar[3] Rudowsky T., Cook S., Hynes M., Heffley R., Luter M., Lawrence T., Niewoehner R., Bollman D., Senn P., Durham W., Beaufrere H., Yokell M. and Sonntag A., “Review of the Carrier Approach Criteria for Carrier-Based Aircraft,” U.S. Naval Air Warfare Center, Aircraft Division, NAWCADPAX TR-2002/71, Patuxent River, MD, Oct. 2002. CrossrefGoogle Scholar[4] Xia G., Dong R., Xu J. and Zhu Q., “Linearized Model of Carrier-Based Aircraft Dynamics in Final-Approach Air Condition,” Journal of Aircraft, Vol. 53, No. 1, 2016, pp. 33–47. https://doi.org/10.2514/1.C033175 LinkGoogle Scholar[5] Stevens B. L., Lewis F. L. and Johnson E. N., Aircraft Control and Simulation, 3rd ed., Wiley, New York, 2016, Chap. 3. Google Scholar[6] Wu X. and Zhang S., MATLAB in the Application of Automatic Control, Xidian Univ. Press, Xi’an, PRC, 2013, pp. 250–254. Google Scholar[7] Chaturvedi D. K., Modeling and Simulation of Systems Using Matlab and Simulation, Taylor and Francis, Abingdon, VA, 2010, Appendix B. Google Scholar[8] “Flying Qualities of Pilot Aircraft,” Department of Defense Handbook, U.S. Dept. of Defense Interface Sandard, MIL-HDBK-1797, 1997. Google Scholar[9] Dong R. and Xia G., “Simulation of the Ship Burble in a Cooperative Carrier Approach Pattern,” The 26th Chinese Control and Decision Conference (2014 CCDC), IEEE Publ., Piscataway, NJ, 2014, pp. 1461–1466. Google Scholar[10] Michael R. E. and Blaise G. M., “Nonlinear Six-Degree-of-Freedom Aircraft Trim,” Journal of Guidance, Control, and Dynamics, Vol. 23, No. 2, 2000, pp. 305–311. https://doi.org/10.2514/2.4523 LinkGoogle Scholar[11] Chudoba B. and Cook M., “Trim Equations of Motion for Aircraft Design: Steady State Straight-Line Flight,” AIAA Atmospheric Flight Mechanics Conference and Exhibit, AIAA, Reston, VA, 2003, pp. 1–11; also AIAA Paper 2003-5691, 2003. https://doi.org/10.2514/6.2003-5691 Google Scholar[12] Marco A. D., Duke E. and Berndt J., “A General Solution to the Aircraft Trim Problem,” AIAA Modeling and Simulation Technologies Conference and Exhibit, AIAA, Reston, VA, 2007, pp. 1–40; also AIAA Paper 2007-6703, 2007. https://doi.org/10.2514/6.2007-6703 Google Scholar[13] Etkin B., Dynamics of Atmospheric Flight, Wiley, New York, 1972, pp. 148–188, 529–548. Google Scholar[14] Misra G. and Bai X., “Output-Feedback Stochastic Model Predictive Control for Glideslope Tracking During Aircraft Carrier Landing,” Journal of Guidance, Control, and Dynamics, Vol. 42, No. 9, 2019, pp. 2098–2105. https://doi.org/10.2514/1.G004160 LinkGoogle Scholar[15] Urnes J. M. and Hess R. K., “Development of the FA-18A Automatic Carrier Landing System,” Journal of Guidance, Control, and Dynamics, Vol. 8, No. 3, 1985, pp. 289–295. https://doi.org/10.2514/3.19978 LinkGoogle Scholar Previous article Next article FiguresReferencesRelatedDetails What's Popular Volume 58, Number 5September 2021 CrossmarkInformationCopyright © 2021 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-3868 to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp. TopicsAerodynamic PerformanceAerodynamicsAeronautical EngineeringAeronauticsAerospace SciencesAircraft Components and StructureAircraft DesignAircraft InstrumentsAircraft Landing SystemsAircraft Operations and TechnologyAircraftsAirspeedFlight DynamicsFlight Mechanics KeywordsFlight Path AngleAerodynamic CoefficientsClosed LoopLift CoefficientAirframesAutomatic Carrier Landing SystemMATLABCarrier Based AircraftFlight VelocityWind Over The DeckAcknowledgmentsThis work was supported by the National Natural Science Foundation of China (no. 61803116) and the Undergraduate Research and Training Program of the Beijing Institute of Petrochemical Technology (no. 2021J00017).PDF Received5 February 2021Accepted28 July 2021Published online30 August 2021

Single-Pixel Particle Image Velocimetry for Characterization of Dielectric Barrier Discharge Plasma Actuators

No AccessTechnical NotesCopula-Based Collaborative Multistructure Damage Diagnosis and Prognosis for Fleet Maintenance Digital TwinsXuan Zhou, Claudio Sbarufatti, Marco Giglio, Leiting Dong and Satya N. AtluriXuan Zhou https://orcid.org/0000-0002-2806-9654Beihang University, 100191 Beijing, People’s Republic of China*Ph.D. Candidate, School of Aeronautic Science and Engineering; also Ph.D. Candidate, Department of Mechanical Engineering, Polytechnic University of Milan, 20156 Milan, Italy.Search for more papers by this author, Claudio Sbarufatti https://orcid.org/0000-0001-5511-8194Polytechnic University of Milan, 20156 Milan, Italy†Associate Professor, Department of Mechanical Engineering; (Co-Corresponding Author).Search for more papers by this author, Marco GiglioPolytechnic University of Milan, 20156 Milan, Italy‡Professor, Department of Mechanical Engineering.Search for more papers by this author, Leiting Dong https://orcid.org/0000-0003-1460-1846Beihang University, 100191 Beijing, People’s Republic of China§Professor and Deputy Dean, School of Aeronautic Science and Engineering; Tianmushan Laboratory, 310023 Hangzhou, People’s Republic of China; (Corresponding Author).Search for more papers by this author and Satya N. AtluriTexas Tech University, Lubbock, Texas 79409¶Professor and Presidential Chair, Department of Mechanical Engineering. Fellow AIAA.Search for more papers by this authorPublished Online:15 Jun 2023https://doi.org/10.2514/1.J063105SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About References [1] Molent L. and Aktepe B., “Review of Fatigue Monitoring of Agile Military Aircraft,” Fatigue and Fracture of Engineering Materials and Structures, Vol. 23, No. 9, 2000, pp. 767–785. https://doi.org/10.1046/j.1460-2695.2000.00330.x CrossrefGoogle Scholar[2] Tuegel E. J., Ingraffea A. R., Eason T. G. and Spottswood S. M., “Reengineering Aircraft Structural Life Prediction Using a Digital Twin,” International Journal of Aerospace Engineering, Vol. 2011, Aug. 2011, Paper 154798. https://doi.org/10.1155/2011/154798 CrossrefGoogle Scholar[3] Zhou X., He S., Dong L. and Atluri S. N., “Real-Time Prediction of Probabilistic Crack Growth with a Helicopter Component Digital Twin,” AIAA Journal, Vol. 60, No. 4, 2022, pp. 2555–2567. https://doi.org/10.2514/1.J060890 LinkGoogle Scholar[4] Zhao F., Zhou X., Wang C., Dong L. and Atluri S. N., “Setting Adaptive Inspection Intervals in Helicopter Components, Based on a Digital Twin,” AIAA Journal, Vol. 61, No. 6, May 2023, pp. 2675–2688. https://doi.org/10.2514/1.J062222 LinkGoogle Scholar[5] Li C., Mahadevan S., Ling Y., Choze S. and Wang L., “Dynamic Bayesian Network for Aircraft Wing Health Monitoring Digital Twin,” AIAA Journal, Vol. 55, No. 3, 2017, pp. 930–941. https://doi.org/10.2514/1.J055201 LinkGoogle Scholar[6] Li T., Sbarufatti C., Cadini F., Chen J. and Yuan S., “Particle Filter-Based Hybrid Damage Prognosis Considering Measurement Bias,” Structural Control and Health Monitoring, Vol. 29, No. 4, 2022, Paper e2914. https://doi.org/10.1002/stc.2914 Google Scholar[7] Patton A. J., “A Review of Copula Models for Economic Time Series,” Journal of Multivariate Analysis, Vol. 110, Sept. 2012, pp. 4–18. https://doi.org/10.1016/j.jmva.2012.02.021 Google Scholar[8] Zhou X., Sbarufatti C., Giglio M. and Dong L., “A Fuzzy-Set-Based Joint Distribution Adaptation Method for Regression and Its Application to Online Damage Quantification for Structural Digital Twin,” Mechanical Systems and Signal Processing, Vol. 191, May 2023, Paper 110164. https://doi.org/10.1016/j.ymssp.2023.110164 Google Scholar[9] Han L., He X., Ning Y., Zhang Y. and Zhou Y., “Fatigue Damage Diagnosis and Prognosis for 2024 Aluminum Plates with Center Holes: A Strain Monitoring Approach,” International Journal of Fatigue, Vol. 170, Jan. 2023, Paper 107535. https://doi.org/10.1016/j.ijfatigue.2023.107535. Google Scholar Next article FiguresReferencesRelatedDetails What's Popular Articles in AdvanceSupplemental Materials CrossmarkInformationCopyright © 2023 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-385X to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp. TopicsAircraft Components and StructureAircraft DesignAircraft Operations and TechnologyApplied MathematicsDigital EngineeringEngineering and Technology ManagementFatigue (Materials)Fracture MechanicsGeneral PhysicsMaterial PropertiesMaterials and Structural MechanicsMathematical AnalysisStatistical AnalysisStructural Material PropertiesStructural Mechanics KeywordsDigital EngineeringStress Intensity FactorCumulative Distribution FunctionAircraft Components and StructureStructural DamageFatigue (Materials)Mathematical AnalysisStructural IntegrityNumber of ParticlesStructural AnalysisAcknowledgmentsThe National Natural Science Foundation of China (grant number 12072011) and the Aeronautical Science Foundation of China (grant number 201909051001) supported the work of the X. Zhou and Leiting Dong. The China Scholarship Council (grant number 202106020002) supported the work of the X. Zhou.PDF Received17 April 2023Accepted17 May 2023Published online15 June 2023

Approximation of Optimal Impulsive Flyby Transfer with Terminal Inspection Constraints

Wall Pressure Fluctuations on the Surface of Sloped Forward-Facing Steps

Efficient Computational Fluid Dynamics Approach for Coaxial Rotor Simulations in Hover

Additively Manufactured Acrylonitrile-Butadiene-Styrene–Nitrous-Oxide Hybrid Rocket Motor with Electrostatic Igniter