Michael Amitay
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Michael Amitay has a total of 67 co-authors. Here are the top co-authors by number of shared publications:
- Kunihiko Taira
University of California, Los Angeles
5 shared publications - Vassilis Theofilis
Center for High-Speed Flight, Faculty of Aerospace Engineering, Technion – Israel Institute of Technology, Haifa 32000, Israel
5 shared publications Chia Min Leong
Rensselaer Polytechnic Institute 2 Mechanical, Aeronautical, and Nuclear Engineering Troy, New York 12180, USA
3 shared publicationsJohn Farnsworth
Mechanical Aerospace and Nuclear Engineering, Rensselaer Polytechnic Institute, Troy, USA
3 shared publications- Kai Zhang
School of Ocean and Civil Engineering Shanghai Jiao Tong University 200240 Shanghai China
3 shared publications Keith Taylor
Center for Flow Physics and Control RPI Watervliet New York
3 shared publications
Latest Publications
- 30 March 2026
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 1032, A3
Three-dimensional separation over swept and tapered finite span cantilevered wings
Experimental investigation is presented to elucidate flow structures and corresponding frequencies on finite span, cantilevered wings as functions of sweep angle and taper ratio. A detailed parameters sweep of planform geometry varied the leading and trailing edge sweep angles of NACA 0015 wings with a semi-aspect ratio of 2. The experiments were performed at Reynolds numbers O ( $10^5$ ) and angles of attack $12^\circ$ – $22^\circ$ . The experiments included flow visualisations, volumetric flow measurements, time-resolved measurements at selected spanwise planes and aerodynamic loads. This is the first time, to the best knowledge of the authors, that multiple configurations were tested under the same exact conditions. The correlation between three-dimensional (3-D) Reynolds stress distributions and 3-D flow separation is presented. Moreover, spectral content reveals modes that vary along the span, as well as for different planforms. For all wings, at the locations of largest reversed flow, power spectral density (PSD) peaks were seen at $0.1\lt St\lt 0.2$ , corresponding to vortex shedding. At spanwise locations near surface spirals the PSD exhibits peaks at lower frequencies of St = O (0.01) due to focus point wandering. The mean flow fields presented here show similarities to previous numerical simulation findings on similar geometries at Reynolds number O ( $10^2$ ). Moreover, the spanwise location of the largest magnitude of turbulent kinetic energy corresponds to the location of the most amplified mode at a Reynolds number of 400 found previously. The present research, complemented by previous low-Reynolds-number work, provides fundamental insights into global flow structures on multiple finite span wings, their corresponding spectral content and the effect on their aerodynamic performance.- 30 March 2026
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 1032, A3
Three-dimensional separation over swept and tapered finite span cantilevered wings
Experimental investigation is presented to elucidate flow structures and corresponding frequencies on finite span, cantilevered wings as functions of sweep angle and taper ratio. A detailed parameters sweep of planform geometry varied the leading and trailing edge sweep angles of NACA 0015 wings with a semi-aspect ratio of 2. The experiments were performed at Reynolds numbers O ( $10^5$ ) and angles of attack $12^\circ$ – $22^\circ$ . The experiments included flow visualisations, volumetric flow measurements, time-resolved measurements at selected spanwise planes and aerodynamic loads. This is the first time, to the best knowledge of the authors, that multiple configurations were tested under the same exact conditions. The correlation between three-dimensional (3-D) Reynolds stress distributions and 3-D flow separation is presented. Moreover, spectral content reveals modes that vary along the span, as well as for different planforms. For all wings, at the locations of largest reversed flow, power spectral density (PSD) peaks were seen at $0.1\lt St\lt 0.2$ , corresponding to vortex shedding. At spanwise locations near surface spirals the PSD exhibits peaks at lower frequencies of St = O (0.01) due to focus point wandering. The mean flow fields presented here show similarities to previous numerical simulation findings on similar geometries at Reynolds number O ( $10^2$ ). Moreover, the spanwise location of the largest magnitude of turbulent kinetic energy corresponds to the location of the most amplified mode at a Reynolds number of 400 found previously. The present research, complemented by previous low-Reynolds-number work, provides fundamental insights into global flow structures on multiple finite span wings, their corresponding spectral content and the effect on their aerodynamic performance.- Open Access
- 24 October 2025
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 1021, A53
Biglobal resolvent analysis of separated flow over a NACA0012 airfoil
The effects of Reynolds number across ${\textit{Re}}=1000$ , $2500$ , $5000$ and $10\,000$ on separated flow over a two-dimensional NACA0012 airfoil at an angle of attack of $\alpha =14^\circ$ are investigated through biglobal resolvent analysis. We identify modal structures and energy amplifications over a range of frequencies, spanwise wavenumbers, and values of the discount parameter, providing insights across various time scales. Using temporal discounting, we find that the shear-layer dynamics dominates over short time horizons, while the wake dynamics becomes the primary amplification mechanism over long time horizons. Spanwise effects also appear over long time horizons, sustained by low frequencies. The low-frequency and high-wavenumber structures are found to be dominated by elliptic mechanisms within the recirculation region. At a fixed angle of attack and across the Reynolds numbers, the response modes shift from wake-dominated structures at low frequencies to shear-layer-dominated structures at higher frequencies. The frequency at which the dominant mechanism changes is independent of the Reynolds number. Comparisons at a different angle of attack ( $\alpha =9^\circ$ ) show that the transition from wake to shear-layer dynamics with increasing frequency only occurs if the unsteady flow is three-dimensional. We also study the dominant frequencies associated with wake and shear-layer dynamics across the angles of attack and Reynolds numbers, and confirm characteristic scaling laws from the literature.- 24 October 2025
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 1021, A53
Open AccessBiglobal resolvent analysis of separated flow over a NACA0012 airfoil
The effects of Reynolds number across ${\textit{Re}}=1000$ , $2500$ , $5000$ and $10\,000$ on separated flow over a two-dimensional NACA0012 airfoil at an angle of attack of $\alpha =14^\circ$ are investigated through biglobal resolvent analysis. We identify modal structures and energy amplifications over a range of frequencies, spanwise wavenumbers, and values of the discount parameter, providing insights across various time scales. Using temporal discounting, we find that the shear-layer dynamics dominates over short time horizons, while the wake dynamics becomes the primary amplification mechanism over long time horizons. Spanwise effects also appear over long time horizons, sustained by low frequencies. The low-frequency and high-wavenumber structures are found to be dominated by elliptic mechanisms within the recirculation region. At a fixed angle of attack and across the Reynolds numbers, the response modes shift from wake-dominated structures at low frequencies to shear-layer-dominated structures at higher frequencies. The frequency at which the dominant mechanism changes is independent of the Reynolds number. Comparisons at a different angle of attack ( $\alpha =9^\circ$ ) show that the transition from wake to shear-layer dynamics with increasing frequency only occurs if the unsteady flow is three-dimensional. We also study the dominant frequencies associated with wake and shear-layer dynamics across the angles of attack and Reynolds numbers, and confirm characteristic scaling laws from the literature. - 1 April 2024
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 62 (4) , 1503-1516
Control of Reverse Flow over Cantilevered Swept Blades Using Passive Camber Morphing
- 1 April 2024
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 62 (4) , 1503-1516
Control of Reverse Flow over Cantilevered Swept Blades Using Passive Camber Morphing
- 24 November 2023
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 976, A6
Laminar post-stall wakes of tapered swept wings
While tapered swept wings are widely used, the influence of taper on their post-stall wake characteristics remains largely unexplored. To address this issue, we conduct an extensive study using direct numerical simulations to characterize the wing taper and sweep effects on laminar separated wakes. We analyse flows behind NACA 0015 cross-sectional profile wings at post-stall angles of attack $\alpha =14^\circ$ – $22^\circ$ with taper ratios $\lambda =0.27$ – $1$ , leading-edge sweep angles $0^\circ$ – $50^\circ$ and semi aspect ratios $sAR =1$ and $2$ at a mean-chord-based Reynolds number of $600$ . Tapered wings have smaller tip chord length, which generates a weaker tip vortex, and attenuates inboard downwash. This results in the development of unsteadiness over a large portion of the wingspan at high angles of attack. For tapered wings with backward-swept leading edges, unsteadiness emerges near the wing tip. On the other hand, wings with forward-swept trailing edges are shown to concentrate wake-shedding structures near the wing root. For highly swept untapered wings, the wake is steady, while unsteady shedding vortices appear near the tip for tapered wings with high leading-edge sweep angles. For such wings, larger wake oscillations emerge near the root as the taper ratio decreases. While the combination of taper and sweep increases flow unsteadiness, we find that tapered swept wings have more enhanced aerodynamic performance than untapered and unswept wings, exhibiting higher time-averaged lift and lift-to-drag ratio. The current findings shed light on the fundamental aspects of flow separation over tapered wings in the absence of turbulent flow effects.- 24 November 2023
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 976, A6
Laminar post-stall wakes of tapered swept wings
While tapered swept wings are widely used, the influence of taper on their post-stall wake characteristics remains largely unexplored. To address this issue, we conduct an extensive study using direct numerical simulations to characterize the wing taper and sweep effects on laminar separated wakes. We analyse flows behind NACA 0015 cross-sectional profile wings at post-stall angles of attack $\alpha =14^\circ$ – $22^\circ$ with taper ratios $\lambda =0.27$ – $1$ , leading-edge sweep angles $0^\circ$ – $50^\circ$ and semi aspect ratios $sAR =1$ and $2$ at a mean-chord-based Reynolds number of $600$ . Tapered wings have smaller tip chord length, which generates a weaker tip vortex, and attenuates inboard downwash. This results in the development of unsteadiness over a large portion of the wingspan at high angles of attack. For tapered wings with backward-swept leading edges, unsteadiness emerges near the wing tip. On the other hand, wings with forward-swept trailing edges are shown to concentrate wake-shedding structures near the wing root. For highly swept untapered wings, the wake is steady, while unsteady shedding vortices appear near the tip for tapered wings with high leading-edge sweep angles. For such wings, larger wake oscillations emerge near the root as the taper ratio decreases. While the combination of taper and sweep increases flow unsteadiness, we find that tapered swept wings have more enhanced aerodynamic performance than untapered and unswept wings, exhibiting higher time-averaged lift and lift-to-drag ratio. The current findings shed light on the fundamental aspects of flow separation over tapered wings in the absence of turbulent flow effects.- 1 September 2023
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 61 (9) , 3923-3934
Hybrid Lumped-Element and Finite Element Model for Novel Synthetic Jet Actuator Shapes
- 1 September 2023
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 61 (9) , 3923-3934
Hybrid Lumped-Element and Finite Element Model for Novel Synthetic Jet Actuator Shapes
- 22 May 2023
- Published by American Physical Society (APS) in Physical Review Fluids
- Vol. 8 (5) , 054701
Interaction of low aspect ratio, cantilevered, chamfered cylindrical pins with a laminar boundary layer
The flow field associated with cantilevered, low aspect ratio cylindrical pins having different chamfered free-ends were investigated using oil flow visualizations and stereoscopic particle image velocimetry at . Two chamfered pins, where the chamfer encompassed either half of the pin's planform or its full planform, were analyzed with the chamfer at various skew angles with respect to the freestream and were compared with a pin without a chamfer. All pins exhibited a complex flow field, including an array of streamwise vortical structures. The chamfered pins resulted in two additional counter-rotating streamwise vortices, named chamfered induced vortices (CIVs). It was shown that changing the skew angle resulted in a change in the strength of these vortical structures, their direction of rotation, and as a result, the net circulation produced. Comparing the two chamfered pins, the pin where the chamfer encompassed half of its planform produced stronger CIVs. These effects are discussed in detail to provide insight into a future use of these pins as flow control devices.- 22 May 2023
- Published by American Physical Society (APS) in Physical Review Fluids
- Vol. 8 (5) , 054701
Interaction of low aspect ratio, cantilevered, chamfered cylindrical pins with a laminar boundary layer
The flow field associated with cantilevered, low aspect ratio cylindrical pins having different chamfered free-ends were investigated using oil flow visualizations and stereoscopic particle image velocimetry at . Two chamfered pins, where the chamfer encompassed either half of the pin's planform or its full planform, were analyzed with the chamfer at various skew angles with respect to the freestream and were compared with a pin without a chamfer. All pins exhibited a complex flow field, including an array of streamwise vortical structures. The chamfered pins resulted in two additional counter-rotating streamwise vortices, named chamfered induced vortices (CIVs). It was shown that changing the skew angle resulted in a change in the strength of these vortical structures, their direction of rotation, and as a result, the net circulation produced. Comparing the two chamfered pins, the pin where the chamfer encompassed half of its planform produced stronger CIVs. These effects are discussed in detail to provide insight into a future use of these pins as flow control devices.- 19 January 2023
- Published by American Physical Society (APS) in Physical Review Fluids
- Vol. 8 (1) , 014703
Three-dimensional separation over unswept cantilevered wings at a moderate Reynolds number
An experimental investigation of separated flows over unswept, cantilevered wings with a NACA 0015 cross section is presented. For all experiments, the chord-based Reynolds number was . The results include qualitative surface topology from oil flow visualizations at angles of attack between and and semiaspect ratios 1, 2, and 4, as well as quantitative three-dimensional flowfield measurements using stereo particle image velocimetry (SPIV) at an angle of attack of and semiaspect ratio 4. For all aspect ratios two counterrotating surface foci appeared on the wings when reversed flow was present. At the lower aspect ratios, the surface foci did not occur until higher angles of attack due to a reduction in separation extent by downwash from the tip vortex which dominates a higher percentage of the span. The volumetric mean flowfield measured with SPIV over the semiaspect ratio of 4 model and in its wake revealed the counterrotating surface foci were connected by an arch vortex. Several vortex identification methods were employed to visualize the location of the arch vortex over the suction surface. The helicity and Reynolds stress fields were shown to be highly influenced by the shape of the arch vortex. The Reynolds shear stresses containing spanwise velocity fluctuations were influenced by the tip vortex and the root horseshoe vortex, and as such had greater magnitude than the spanwise Reynolds stresses measured in a previous study of an induced stall cell on a wall-to-wall wing. In addition, time-resolved flowfield measurements showed that power spectra at the stall cell center had a dominant shedding frequency of . At the center of the stall cell focus, the power spectra peaked at and . Analysis of the instantaneous flowfield at the midspan characterized the shedding of vortices into the near wake as an intermittent phenomenon where the magnitude of velocity fluctuations associated with the shedding would increase and decrease over time at periods on the order of ten shedding cycles.- 19 January 2023
- Published by American Physical Society (APS) in Physical Review Fluids
- Vol. 8 (1) , 014703
Three-dimensional separation over unswept cantilevered wings at a moderate Reynolds number
An experimental investigation of separated flows over unswept, cantilevered wings with a NACA 0015 cross section is presented. For all experiments, the chord-based Reynolds number was . The results include qualitative surface topology from oil flow visualizations at angles of attack between and and semiaspect ratios 1, 2, and 4, as well as quantitative three-dimensional flowfield measurements using stereo particle image velocimetry (SPIV) at an angle of attack of and semiaspect ratio 4. For all aspect ratios two counterrotating surface foci appeared on the wings when reversed flow was present. At the lower aspect ratios, the surface foci did not occur until higher angles of attack due to a reduction in separation extent by downwash from the tip vortex which dominates a higher percentage of the span. The volumetric mean flowfield measured with SPIV over the semiaspect ratio of 4 model and in its wake revealed the counterrotating surface foci were connected by an arch vortex. Several vortex identification methods were employed to visualize the location of the arch vortex over the suction surface. The helicity and Reynolds stress fields were shown to be highly influenced by the shape of the arch vortex. The Reynolds shear stresses containing spanwise velocity fluctuations were influenced by the tip vortex and the root horseshoe vortex, and as such had greater magnitude than the spanwise Reynolds stresses measured in a previous study of an induced stall cell on a wall-to-wall wing. In addition, time-resolved flowfield measurements showed that power spectra at the stall cell center had a dominant shedding frequency of . At the center of the stall cell focus, the power spectra peaked at and . Analysis of the instantaneous flowfield at the midspan characterized the shedding of vortices into the near wake as an intermittent phenomenon where the magnitude of velocity fluctuations associated with the shedding would increase and decrease over time at periods on the order of ten shedding cycles.- Open Access
- 22 June 2022
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 944, A6
Linear modal instabilities around post-stall swept finite wings at low Reynolds numbers
Linear modal instabilities of flow over untapered wings with aspect ratios $AR=4$ and 8, based on the NACA 0015 profile, have been investigated numerically over a range of angles of attack, $\alpha$ , and angles of sweep, $\varLambda$ , at chord Reynolds numbers $100\le Re\le 400$ . Laminar base flows have been generated using direct numerical simulation and selective frequency damping, as appropriate. Several families of unstable three-dimensional linear global (TriGlobal) eigenmodes have been identified and their dependence on geometric parameters has been examined in detail at $Re=400$ . The leading global mode A is associated with the peak recirculation in the three-dimensional laminar separation bubble formed on the wing and becomes unstable when recirculation reaches $\textit {O}(10\,\%)$ . On unswept wings, this mode peaks in the midspan region of the wake and moves towards the wing tip with increasing $\varLambda$ , following the displacement of peak recirculation; its linear amplification leads to wake unsteadiness. Additional amplified modes exist at nearly the same and higher frequencies compared to mode A. The critical $Re$ has been identified and it is shown that amplification increases with increasing sweep, up to $\varLambda \approx 10^\circ$ . At higher $\varLambda$ , all global modes become less amplified and are ultimately stable at $\varLambda =30^\circ$ . An increase in amplification of the leading mode with sweep was not observed over the $AR=4$ wing, where tip vortex effects were shown to dominate.- 22 June 2022
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 944, A6
Open AccessLinear modal instabilities around post-stall swept finite wings at low Reynolds numbers
Linear modal instabilities of flow over untapered wings with aspect ratios $AR=4$ and 8, based on the NACA 0015 profile, have been investigated numerically over a range of angles of attack, $\alpha$ , and angles of sweep, $\varLambda$ , at chord Reynolds numbers $100\le Re\le 400$ . Laminar base flows have been generated using direct numerical simulation and selective frequency damping, as appropriate. Several families of unstable three-dimensional linear global (TriGlobal) eigenmodes have been identified and their dependence on geometric parameters has been examined in detail at $Re=400$ . The leading global mode A is associated with the peak recirculation in the three-dimensional laminar separation bubble formed on the wing and becomes unstable when recirculation reaches $\textit {O}(10\,\%)$ . On unswept wings, this mode peaks in the midspan region of the wake and moves towards the wing tip with increasing $\varLambda$ , following the displacement of peak recirculation; its linear amplification leads to wake unsteadiness. Additional amplified modes exist at nearly the same and higher frequencies compared to mode A. The critical $Re$ has been identified and it is shown that amplification increases with increasing sweep, up to $\varLambda \approx 10^\circ$ . At higher $\varLambda$ , all global modes become less amplified and are ultimately stable at $\varLambda =30^\circ$ . An increase in amplification of the leading mode with sweep was not observed over the $AR=4$ wing, where tip vortex effects were shown to dominate. - Open Access
- 31 May 2022
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 942
Comparing steady and unsteady rectangular jets issuing into a crossflow
The foundational differences of steady and unsteady jets issued into a laminar boundary layer crossflow are considered. Jets have been used widely for flow control applications, due to their ability to enhance mixing and mitigate separation, but it is unclear what role jet steadiness plays in flow control effectiveness. Here we compare experimentally unsteady (synthetic) and steady rectangular jets issued into a flat-plate laminar boundary layer with varying orifice pitch and skew. The coherent streamwise vortices produced by unsteady jets were shown to be much stronger than those produced by steady jets, despite producing similar flow patterns. These differences are rooted in how vorticity is generated in the orifice, through either a Stokes layer (unsteady) or a Blasius boundary layer (steady). Exploring the time- and phase-averaged vorticity transport equation reveals that the time-varying vorticity term is the reason for the enhanced vortical structure. When considering flow control metrics, we find that the unsteady jet produced greater added momentum in the boundary layer and added vorticity when compared to a momentum-matched steady jet. Both the steady and unsteady jets produced similar jet penetration characteristics.
- 31 May 2022
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 942
Open AccessComparing steady and unsteady rectangular jets issuing into a crossflow
The foundational differences of steady and unsteady jets issued into a laminar boundary layer crossflow are considered. Jets have been used widely for flow control applications, due to their ability to enhance mixing and mitigate separation, but it is unclear what role jet steadiness plays in flow control effectiveness. Here we compare experimentally unsteady (synthetic) and steady rectangular jets issued into a flat-plate laminar boundary layer with varying orifice pitch and skew. The coherent streamwise vortices produced by unsteady jets were shown to be much stronger than those produced by steady jets, despite producing similar flow patterns. These differences are rooted in how vorticity is generated in the orifice, through either a Stokes layer (unsteady) or a Blasius boundary layer (steady). Exploring the time- and phase-averaged vorticity transport equation reveals that the time-varying vorticity term is the reason for the enhanced vortical structure. When considering flow control metrics, we find that the unsteady jet produced greater added momentum in the boundary layer and added vorticity when compared to a momentum-matched steady jet. Both the steady and unsteady jets produced similar jet penetration characteristics.
- 24 March 2022
- Published by American Physical Society (APS) in Physical Review Fluids
- Vol. 7 (3) , 034702
Interaction of synthetic jets with a massively separated three-dimensional flow field
The interaction of an array of finite span synthetic jet actuators with a massively separated flow was explored experimentally over a cantilevered, swept, and tapered model having a deflected control surface. The synthetic jet actuators were placed slightly upstream of the control surface hinge-line of the wind tunnel model. The flow physics associated with the interaction of multiple jets and the separated crossflow over the control surface was investigated using stereoscopic particle image velocimetry. Experiments were conducted at two spanwise regions along the model, where separation severity varied. At the outboard region, the baseline flow field was characterized by a severe separation that was quasiuniform in the spanwise direction. At the inboard measurement domain, separation was milder but increased in severity in the outboard direction. When a single jet was activated, separation was reduced downstream and outboard of the jet orifice. In addition, spanwise velocity was augmented outboard of the jet's structures at the outboard measurement domain from an oblique vortex that was observed at the spanwise location where separation severity increased (as the flow approached the baseline state). In the inboard region, this vortex was not observed and the spanwise velocity decreased with a single jet active. When more jets were actuated along the span, the overall severity of separation decreased at both locations. Despite this, in the outboard region, the spanwise velocity near the surface was enhanced, and the strength of the jets’ vortical structures decreased as more jets were activated (i.e., they negatively impacted one another). On the contrary, at the inboard region, the jets beneficially affected each other. These differences were hypothesized to be related to the oblique vortices that were distinguishable outboard but not inboard with all jets active.
- 24 March 2022
- Published by American Physical Society (APS) in Physical Review Fluids
- Vol. 7 (3) , 034702
Interaction of synthetic jets with a massively separated three-dimensional flow field
The interaction of an array of finite span synthetic jet actuators with a massively separated flow was explored experimentally over a cantilevered, swept, and tapered model having a deflected control surface. The synthetic jet actuators were placed slightly upstream of the control surface hinge-line of the wind tunnel model. The flow physics associated with the interaction of multiple jets and the separated crossflow over the control surface was investigated using stereoscopic particle image velocimetry. Experiments were conducted at two spanwise regions along the model, where separation severity varied. At the outboard region, the baseline flow field was characterized by a severe separation that was quasiuniform in the spanwise direction. At the inboard measurement domain, separation was milder but increased in severity in the outboard direction. When a single jet was activated, separation was reduced downstream and outboard of the jet orifice. In addition, spanwise velocity was augmented outboard of the jet's structures at the outboard measurement domain from an oblique vortex that was observed at the spanwise location where separation severity increased (as the flow approached the baseline state). In the inboard region, this vortex was not observed and the spanwise velocity decreased with a single jet active. When more jets were actuated along the span, the overall severity of separation decreased at both locations. Despite this, in the outboard region, the spanwise velocity near the surface was enhanced, and the strength of the jets’ vortical structures decreased as more jets were activated (i.e., they negatively impacted one another). On the contrary, at the inboard region, the jets beneficially affected each other. These differences were hypothesized to be related to the oblique vortices that were distinguishable outboard but not inboard with all jets active.