In supersonic flows with a freestream Mach number of 2.4, the turbulent boundary layer could be separated by an oblique shock wave. The characteristics of the unsteadiness change of the separated flow were experimentally observed when various flow control techniques were applied to control the separated flows. The unsteadiness of the separated flows were analyzed and compared for two different control techniques applied ahead of the separation location; a conventional control technique using supersonic jet ejection and a recently developed supersonic fluidic oscillator. Measurement of high-frequency response pressure guages and statistical analysis of the measured signals were employed to compare the unsteadiness of the separated flows for various locations and control pressures of the control devices, and the fluidic oscillator operated in a specific condition was observed to have favorable control performances.

An experimental study was carried out to control a shock-induced boundary layer separation by utilizing the supersonic sweeping jet from the fluidic oscillator. High-speed schlieren, surface flow visualization, wall pressure measurement and precise Pitot tube measurement were applied to observe the influences of the location and the supply pressure of the fluidic oscillator on the characteristics of the oblique-shock-induced boundary layer separation. The characteristics of the separation control by the present supersonic fluidic oscillator was quantitatively analyzed by comparing with a conventional control method utilizing an air-jet vortex generator.

This paper deals with a study for the guidance control of reusable launch vehicle. For this purpose, modeling of the equation of motion of a reusable launch vehicle with 6 degrees of freedom was performed. With this model, an optimal re-entry path was created and a path-following guidance control simulation was performed to follow the optimal re-entry path. For the design of the path-following guidance controller, the attitude controller applying a time-delay technique that is resistant to modeling uncertainty, disturbance and failure. And the nonlinear path-following guidance law were used. Guidance control simulation using a classical PD controller was performed and compared with the guidance control simulation of a reusable launch vehicle applying a time delay technique.

Three-dimensional numerical study was carried out to evaluate the aerodynamic characteristics of the supersonic grid fins installed on SpaceX Falcon 9. The present three-dimensional flow results were compared to the results by the concept of the unit grid fin previously introduced for more efficient and simpler flow calculations, and the validity of the approach of the unit grid fin were evaluated. The aerodynamic characteristics in supersonic flights Mach 2.8 of SpaceX Falcon 9 with various angle of attacks were also obtained.

An experimental investigation was conducted to control the oblique-shock-induced boundary-layer separation of a freestream Mach number of 2.4. The characteristics of the new control technique using a supersonic sweeping jet was compared with those of the conventional method utilizing air-jet vortex generators. High-speed schlieren, surface-flow visualization, and precise pitot tube measurements were utilized for quantitative evaluation of the boundary-layer characteristics downstream of the separation. It was observed that the supersonic sweeping jet weakened the shock-induced separation bubble and introduced better boundary-layer characteristics as well as greater total pressure recovery downstream of the separation than the conventional technique.

No AccessTechnical NotesCharacteristics of a Supersonic Fluidic Oscillator Using Design of ExperimentSangHoon Park, HeeChang Ko, MoonJung Kang and Yeol LeeSangHoon ParkKorea Aerospace University, Goyang 10540, Republic of Korea, HeeChang KoKorea Aerospace University, Goyang 10540, Republic of Korea, MoonJung KangAgency for Defense Development, Daejeon 34186, Republic of Korea and Yeol LeeKorea Aerospace University, Goyang 10540, Republic of KoreaPublished Online:22 Mar 2020https://doi.org/10.2514/1.J058968SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About References [1] Cattafesta L. N. and Sheplak M., "Actuators for Active Flow Control," Annual Review Fluid Mechanics, Vol. 43, No. 1, 2011, pp. 247–272. https://doi.org/10.1146/annurev-fluid-122109-160634 CrossrefGoogle Scholar[2] Ostermann F., Woszidlo R., Nayeri C. N. and Paschereit C. 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Google Scholar Previous article Next article FiguresReferencesRelatedDetailsCited byInfluence of the Projectile Rotation on the Supersonic Fluidic Element31 December 2022 | Aerospace, Vol. 10, No. 1The Effects of Compressibility on the Performance and Modal Structures of a Sweeping Jet Emitted from Various Scales of a Fluidic Oscillator21 July 2022 | Fluids, Vol. 7, No. 7Thermal pollution level reduction by sweeping jet-based enhanced heat dissipation: A numerical study with calibrated Generalized k-ω (GEKO) modelApplied Thermal Engineering, Vol. 204The Influence of Exit Nozzle Geometry on Sweeping Jet Actuator Performance8 February 2022 | Fluids, Vol. 7, No. 2Sensitivity of a fluidic oscillator to modifications of feedback channel and mixing chamber geometry22 November 2021 | Experiments in Fluids, Vol. 62, No. 12Modal Analysis of a Sweeping Jet Emitted by a Fluidic OscillatorDaniel J. Portillo, Eugene N. Hoffman, Matt Garcia, Elijah LaLonde, Emilio Hernandez, Christopher S. Combs and Lyle Hood28 July 2021Feedback-Free and Single-Feedback Sweeping Jet Oscillators with High Sweeping FrequenciesXin Wen, Ziyan Li, Yingzheng Liu and Shiqi Wang10 March 2021 | AIAA Journal, Vol. 59, No. 7Parametric Analysis on Landing Gear Strut Friction of Light Aircraft for Touchdown Performance11 June 2021 | Applied Sciences, Vol. 11, No. 12 What's Popular Volume 58, Number 6June 2020 CrossmarkInformationCopyright © 2020 by SangHoon Park, HeeChang Ko, MoonJung Kang, and Yeol Lee. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. 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. TopicsAerodynamic PerformanceAerodynamicsAeronautical EngineeringAeronauticsBoundary LayersDesign of ExperimentsFlow RegimesFluid DynamicsFluid Flow PropertiesMechanical and Structural VibrationsMechanism and MachinesStructural Design and DevelopmentStructural EngineeringStructural Kinematics and DynamicsStructures, Design and TestVortex Dynamics KeywordsCentral Composite DesignsSweep AnglePower Spectral DensityIncompressible FlowProbability DistributionStagnation TemperatureAerodynamic DragResonance FrequenciesPressure SensorsImage ProcessingAcknowledgmentThe authors gratefully acknowledge the financial support provided by the Agency for Defense Development under the contract ADD-17-113-501-038.PDF Received16 August 2019Accepted25 February 2020Published online22 March 2020

A study of flow characteristics of supersonic fluidic oscillators with shared feedback channel inside was carried out. Unsteady CFD analysis were performed and the numerical results were validated by comparison with the experimental ones observed for the same operation conditions. It was found that the mass flow between individual oscillators through the shared feedback channel directly influenced on the oscillating flow mechanism inside the oscillator, and finally on the synchronization of the jet oscillations. It was also observed that the oscillator with shared feedback channel provided higher pressure loss as well as higher oscillation frequency as compared to the single oscillator of the same geometric shape.

A numerical study was carried out to evaluate the aerodynamic characteristics of the supersonic grid fins installed on SpaceX Falcon 9. The unit-grid-fin concept was utilized for more efficient and simpler 3-D steady flow calculations. Pre- and post-correction processes that accounted the interference effects by the angle of attack of the missile, the influences of the outer frame of the grid fin and the connecting rods were improved in the study, and it was demonstrated that the present correction method was more accurate as compared to previous studies. Finally, the present approach was applied to evaluate the aerodynamic characteristics in transonic/supersonic flights of SpaceX Falcon 9 with various angle of attacks.

A numerical study was performed to observe the characteristics of the supersonic sweeping jet of a fluidic oscillator using unsteady numerical calculation. The numerical results were compared with experimental results for code validation purposes, and good agreements between two results were observed. The characteristics of six different fluidic oscillators with varied internal shapes were numerically analyzed and compared. It was found that a particular inner configuration of the oscillator shows a higher jet oscillation frequency and that the development of the separation bubble inside the oscillator is one of the critical parameters of the performance of the outflowing sweeping jet.

An experimental study is performed to observe the characteristics of the thrust vectoring control (TVC) of the supersonic jet using proportional control valves. It is observed that three different TVC characteristics exist as the nozzle pressure ratio varies. Strong hysteresis phenomena are also observed during the valve control for a certain range of the nozzle pressure ratio. It is also noticed that the secondary chamber pressure is one of the influencing parameters for the TVC. Therefore, a control algorithm utilizing the secondary chamber pressure coefficient as a predictor is applied to achieve the stable TVC avoiding the hysteresis. Consequently, the stable TVC with the maximum deflection angle of about 20-degree has been realized using the proportional control valves.

No AccessTechnical NoteBidirectional Thrust Vectoring Control of a Rectangular Sonic JetMyungYeon Lee, MyungJun Song, DaBin Kim and Yeol LeeMyungYeon LeeKorea Aerospace University, Goyang-si 10540, Republic of Korea, MyungJun SongKorea Aerospace University, Goyang-si 10540, Republic of Korea, DaBin KimKorea Aerospace University, Goyang-si 10540, Republic of Korea and Yeol LeeKorea Aerospace University, Goyang-si 10540, Republic of KoreaPublished Online:24 Jan 2018https://doi.org/10.2514/1.J056598SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About References [1] Deere K. A., “Summary of Fluidic Thrust Vectoring Research Conducted at NASA Langley Research Center,” 21st AIAA Applied Aerodynamics Conference, AIAA Paper 2003-3800, June 2003. LinkGoogle Scholar[2] Páscoa J., Dumas A., Trancossi M., Stewart P. and Vucinic D., “A Review of Thrust-Vectoring in Support of a V/STOL Non-Moving Mechanical Propulsion System,” Central European Journal of Engineering, Vol. 3, No. 3, 2013, pp. 374–388. CrossrefGoogle Scholar[3] Strykowski P. J., Krothapalli A. and Forliti D. J., “Counterflow Thrust Vectoring of Supersonic Jets,” AIAA Journal, Vol. 34, No. 11, 1996, pp. 2306–2314. doi:https://doi.org/10.2514/3.13395 AIAJAH 0001-1452 LinkGoogle Scholar[4] Flamm J. D., “Experimental Study of a Nozzle Using Fluidic Counterflow for Thrust Vectoring,” 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA Paper 1998-3255, 1998. LinkGoogle Scholar[5] Alvi F. S. and Strykowsk P., “Forward Flight Effects on Counterflow Thrust Vector Control of a Supersonic Jet,” AIAA Journal, Vol. 37, No. 2, 1999, pp. 279–281. doi:https://doi.org/10.2514/2.705 AIAJAH 0001-1452 LinkGoogle Scholar[6] Wing D. J., “Static Investigation of Two Fluidic Thrust-Vectoring Concepts on a Two-Dimensional Convergent Divergent Nozzle,” NASA TM-4574, 1994. Google Scholar[7] Mason M. S. and Crowther W. J., “Fluidic Thrust Vectoring for Low Observable Air Vehicle,” 2nd AIAA Flow Control Conference, AIAA Paper 2004-2210, June–July 2004. LinkGoogle Scholar[8] Banazadeh A., Saghafi F., Ghoreyshi M. and Pilidis P., “Experimental and Computational Investigation into the Use of Co-Flow Fluidic Thrust Vectoring on a Small Gas Turbine,” Aeronautical Journal, Vol. 112, No. 1127, 2008, pp. 17–25. doi:https://doi.org/10.1017/S0001924000001950 AENJAK 0001-9240 CrossrefGoogle Scholar[9] Song M. J., Park S. H. and Lee Y., “Application of Backstep Coanda Flap for Supersonic Coflowing Fluidic Thrust-Vector Control,” AIAA Journal, Vol. 52, No. 10, 2014, pp. 2355–2359. doi:https://doi.org/10.2514/1.J052971 AIAJAH 0001-1452 LinkGoogle Scholar[10] Bettridge M. W., Smith B. L. and Spall R. E., “Aerodynamic Jet Steering Using Steady Blowing and Suction,” Experiments in Fluids, Vol. 40, No. 5, 2006, pp. 776–785. doi:https://doi.org/10.1007/s00348-006-0115-z EXFLDU 0723-4864 CrossrefGoogle Scholar[11] Bevilaqua P. M. and Lee J. D., “Design of Supersonic Coanda Jet Nozzles,” Proceedings of the Circulation-Control Workshop, NASA, 1986, pp. 289–312. Google Scholar[12] Matsuo S., Setoguchi T. and Kaneko K., “Study on the Characteristics of Supersonic Coanda Jet,” Journal of Thermal Science, Vol. 7, No. 3, 1998, pp. 165–175. doi:https://doi.org/10.1007/s11630-998-0012-2 CrossrefGoogle Scholar[13] Lee Y., Park S. H. and Kim Y. S., “Thrust Vectoring of Sonic Jet by Using Coanda Flap and Solenoid Valve,” AIAA Journal, Vol. 54, No. 9, 2016, pp. 2909–2915. doi:https://doi.org/10.2514/1.J054993 AIAJAH 0001-1452 LinkGoogle Scholar[14] Warsop C., “Thrust Vectoring Apparatus for a Jet Engine, Corresponding Jet Engine, Thrust Vectoring Method and Upgrading Method for Jet Engine,” U.S. Patent 2011/0167788 A1, 2011. Google Scholar[15] Santos M. M., “Experimental Study on Counter Flow Thrust Vectoring of a Gas Turbine Engine,” Ph.D. Thesis, Florida State Univ., Tallahassee, FL, 2005. Google Scholar[16] Miyamoto H., Matsuo A., Kojima T. and Testing A., “Effects of Sidewall Configurations on Rectangular Plug Nozzle Performance,” 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, AIAA Paper 2006-4373, July 2006. TCNOAQ 0040-1641 LinkGoogle Scholar[17] Song M. J., Chang H. B., Cho Y. H. and Lee Y., “Development of the High-Accuracy Multi-Component Balance for Fluidic Thrust Vectoring Nozzle of UAV,” Journal of the Korean Society for Aeronautical and Space Sciences, Vol. 41, No. 2, 2013, pp. 142–149. doi:https://doi.org/10.5139/JKSAS.2013.41.2.142 CrossrefGoogle Scholar Previous article Next article FiguresReferencesRelatedDetailsCited byMultiaxis Shock Vectoring Control of Overexpanded Supersonic Jet Using a Genetic AlgorithmFernando Zigunov , MyungJun Song, Prabu Sellappan and Farrukh S. Alvi7 October 2022 | Journal of Propulsion and Power, Vol. 0, No. 0 What's Popular Volume 56, Number 6June 2018 CrossmarkInformationCopyright © 2018 by MyungYeon Lee, MyungJun Song, DaBin Kim, and Yeol Lee. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the ISSN 0001-1452 (print) or 1533-385X (online) to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp. TopicsAerodynamic PerformanceAerodynamicsAeronautical EngineeringAeronauticsAircraft EnginesCombustion ChambersFlow RegimesFluid DynamicsJet EnginesOblique Shock WavePropulsion and PowerRocket EngineRocketryShock Waves KeywordsThrust Vector ControlSonic JetChamber PressureCoanda EffectSupersonic FlowStagnation TemperatureAspect RatioMach DiskThrust Vector AngleOperating CostsAcknowledgmentThis research was supported by the Basic Science Research Program through the National Research Foundation of Korea funded by the Ministry of Education, Science and Technology (2016R1D1A1B03930471).PDF Received5 August 2017Accepted17 December 2017Published online24 January 2018

An experimental study is performed to investigate the characteristics of a supersonic sweeping jet from a feedback fluidic oscillator. Quantitative characteristics of the high-frequency sweeping jet are analyzed using high-speed Schlieren visualizations, sound pressure level measurements, and pressure measurements. The observed operating mechanism of the supersonic sweeping jet is similar to previously studied subsonic cases; however, the frequency does not increase as the nozzle pressure ratio increases. No shock wave is observed inside the oscillator at any of the tested nozzle pressures. A triangle-wave type sweeping behavior of the outflowing jet is confirmed by estimating the total harmonic distortion. A higher supply pressure to the oscillator results in smaller sweeping angles and larger spreading angles in the outflowing jet.

The present study focuses on the characteristics of a supersonic jet flowing from a rectangular nozzle exit on a flat plate. Flow visualization techniques using schlieren and kerosene-lampblack tracing are utilized to investigate shock reflection structures and boundary-layer separations over a flat plate. Wall pressure measurements are also carried out to quantitatively analyze the flow structures. All observations are repeated for multiple jet flow boundary conditions by varying the flap length and nozzle pressure ratio. The experimental results show that the jet flow structures over the flat plate are highly three-dimensional with strong bleeding flows from the plate sides, and that they are sensitive to plate length and nozzle pressure ratio. A multicomponent force measurement device is also utilized to observe the characteristics of the jet flow thrust vectoring over the plate. The maximum thrust deflection angle of the jet is about 8 degrees, demonstrating the applicability of thrust vector control via a flat plate installed at the nozzle exit.

사각노즐에서 발생한 음속제트의 코안다 효과를 이용한 추력편향 제어에 관한 실험적 연구가 수행되었다. 코안다 플랩 표면에서 나타나는 제트유동의 3차원 효과를 저감시키기 위하여 노즐 출구의 코안다 플랩 양쪽에 측판이 설치되었다. 쉴리렌 유동가시화 기법과 정량적인 추력편향각 측정을 통하여, 플랩 양쪽에 설치된 측판에 의하여 제트유동의 플랩 하류에서의 박리현상이 크게 지연되었음을 관찰하였다. 이에 따라 최대 72도의 높은 추력편향각과 약 7% 정도의 적은 추력손실이 관찰되었다. An experimental study for the characteristics of the thrust-vectoring of a sonic jet utilizing the coanda flap installed at a rectangular nozzle exit is performed. Two side plates are installed at both sides of the flap to decrease the three dimensional effects of the jet on the flap surface. Schlieren flow visualizations and quantitative measurements of the deflection angle of thrusting vector show that the side plates are able to delay the separation of the jet at the downstream of the flap surface. Substantial increase in the deflection angle of the jet as high as $72^{\circ}$ and small thrust loss as low as 7% are obtained by the present thrust-vectoring technique using the side plates.

No AccessTechnical NoteThrust Vectoring of Sonic Jet by Using Coanda Flap and Solenoid ValveYeol Lee, SangHoon Park and YounSoo KimYeol LeeKorea Aerospace University, Goyang 412-791, Republic of Korea*Professor, School of Aerospace and Mechanical Engineering, 200-1 Hwajeon-Dong. Senior Member AIAA (Corresponding Author).Search for more papers by this author, SangHoon ParkKorea Aerospace University, Goyang 412-791, Republic of Korea†Graduate Research Assistant, Graduate School, Department of Aerospace and Mechanical Engineering, 200-1 Hwajeon-Dong.Search for more papers by this author and YounSoo KimKorea Aerospace University, Goyang 412-791, Republic of Korea‡Undergraduate Student, Department of Aerospace and Mechanical Engineering, 200-1 Hwajeon-Dong.Search for more papers by this authorPublished Online:30 Jun 2016https://doi.org/10.2514/1.J054993SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About References [1] Deere K. A., “Summary of Fluidic Thrust Vectoring Research Conducted at NASA Langley Research Center,” 21st AIAA Applied Aerodynamics Conference, AIAA Paper 2003-3800, June 2003. LinkGoogle Scholar[2] Wing D. J., “Static Investigation of Two Fluidic Thrust-Vectoring Concepts on a Two-Dimensional Convergent Divergent Nozzle,” NASA TM-4574, 1994. Google Scholar[3] Strykowski P. J., Krothapalli A. and Forliti D. J., “Counterflow Thrust Vectoring of Supersonic Jets,” AIAA Journal, Vol. 34, No. 11, 1996, pp. 2306–2314. LinkGoogle Scholar[4] Alvi F. S. and Strykowsk P., “Forward Flight Effects on Counterflow Thrust Vector Control of a Supersonic Jet,” AIAA Journal, Vol. 37, No. 2, 1999, pp. 279–281. LinkGoogle Scholar[5] Yagle P. J., Miller D. N., Gin K. B. and Hamstra J. W., “Demonstration of Fluidic Throat Skewing for Thrust Vectoring in Structurally Fixed Nozzles,” Journal of Fluid Engineering for Gas Turbines and Power, Vol. 123, No. 3, 2001, pp. 502–507. CrossrefGoogle Scholar[6] Mason M. S. and Crowther W. J., “Fluidic Thrust Vectoring for Low Observable Air Vehicle,” 2nd AIAA Flow Control Conference, AIAA Paper 2004-2210, June–July 2004. LinkGoogle Scholar[7] Flamm J. D., Deere K. A., Mason M. L., Berrier B. L. and Johnson S. K., “Design Enhancements of the Two-Dimensional, Dual Throat Fluidic Thrust Vectoring Nozzle Concept,” 3rd AIAA Flow Control Conference, AIAA Paper 2006-3701, June 2006. LinkGoogle Scholar[8] Saghafi F. and Banazadeh A., “Co-Flow Fluidic Thrust Vectoring Requirements for Longitudinal and Lateral Trim Purpose,” 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, AIAA Paper 2006-4980, July 2006. LinkGoogle Scholar[9] Neely A. J., Gesto F. N. and Young J., “Performance Studies of Shock Vector Control Fluidic Thrust Vectoring,” 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, AIAA Paper 2007-5086, July 2007. LinkGoogle Scholar[10] Clarke A. J., “The Conceptual Design of Novel Future UAV’s Incorporating Advanced Technology Research Components,” Ph.D. Dissertation, Cranfield Univ., Cranfield, England, U.K., 2011. Google Scholar[11] Song M. J., Park S. H. and Lee Y., “Application of Backstep Coanda Flap for Supersonic Coflowing Fluidic Thrust-Vector Control,” AIAA Journal, Vol. 42, No. 10, 2014, pp. 2355–2359. LinkGoogle Scholar[12] Santos M. M., “Experimental Study on Counter Flow Thrust Vectoring of a Gas Turbine Engine,” Ph.D. Dissertation, Florida State Univ., Tallahassee, FL, 2004. Google Scholar[13] Park S. H., Kwak J. Y., Chang H. B. and Lee Y., “Improving the Coanda Effect of the Sonic Jet by Utilizing Side Plates on the Flap,” Proceedings of the 7th Asia-Pacific International Symposium on Aerospace Technology, APISAT2015, Australia, Nov. 2015. Google Scholar[14] Song M. J., Chang H. B., Cho Y. H. and Lee Y., “Development of the High-Accuracy Multi-Component Balance for Fluidic Thrust Vectoring Nozzle of UAV,” Journal of the Korean Society for Aeronautical and Space Sciences, Vol. 41, No. 2, 2013, pp. 142–149. CrossrefGoogle Scholar[15] von Glahn U. H., “Use of the Coanda Effect for Jet Deflection and Vertical Lift with Multiple Flat Plate and Curved Plate Deflection Surfaces,” NACA TN-4377, 1958. Google Scholar Previous article Next article

The dynamics of gas-particle flow from a supersonic abrasive blasting nozzle have been studied by 1-D analytical calculation, including wall friction effects inside the nozzle. The developed code in the present study shows a satisfactory agreement with the other study’s results. By utilizing the code, the redesign and optimization of the inner contour of a commercial abrasive blasting nozzle were carried out, and it was found that the redesigned nozzle in the present study can produce faster particle velocities at the nozzle exit by up to 22% compared with the original commercial nozzle.