Global ETD Search
Search theses and dissertations gathered from participating repositories worldwide. Every result links back to the library that holds it. No account is needed.
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Showing 1 to 19 of 19 for “"flap deflection"”.
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An Investigation of the Dynamic Effects of Flap Deflection on the Aerodynamic Characteristics of an Airplane Wing Using Computational Fluid Dynamics
<p>Flaps are used to increase an airplane's lift and to adjust its stability and maneuverability. This study shows an application of STAR-CD, a commercial computational fluid dynamics (CFD) software, to an investigation of the dynamic effects of flap deflection on the lift, drag and moment …
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Analysis of the vortical flow around a 60 degree delta wing with vortex flap
… plate, delta wing with a leading edge vortex flap. The pressure distributions were measured over a range of angles of attack starting from zero to 40° in 5° interval and flap deflection angles from zero to 45° with 5° increments at a Reynolds number of about 2.14 x 10‘ based on the root chord. …
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Active Flow Control of a Three-Element Airfoil in Unbounded Flow and in Ground Effect
… used to determine the relationship between the flap deflection angle and the lift coefficient for the 30P30N airfoil both in unbounded flow and in ground effect for various flight heights. The airfoil flow field is then subjected to Active Flow Control (AFC) by injecting a uniform jet or by …
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A Study of the Design of Adaptive Camber Winglets
… Camber was altered via a simple plain flap deflection in the winglet, which produced a constant camber change over the winglet span. Hinge points were located at 20%, 50% and 80% of the chord and the trailing edge was deflected between -5° and +5°. Analysis was performed using a …
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Computational analysis of multielement airfoils for wind turbines
… airfoil system with one main element and two flaps at a Reynolds number of 1,000,000, and a well-separated four-element airfoil system with an additional strut at a Reynolds number of 975,000. The two multielement airfoil systems were designed for the inboard section of a 10 MW-scale wind …
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Covert-inspired flow control devices for lift enhancement and stall mitigation
… device consisting of single and multiple rows of flaps for lift enhancement and stall mitigation. The effects of a single static covert-inspired flap during post-stall were first characterized. Specifically, the single flap effects on the aerodynamic forces for various single flap designs, i.e., …
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Aerodynamic modeling of a 2-dimensional airfoil with a covert-inspired deployable flap using a discrete vortex method
… show the benefits of attaching a covert-inspired flap to the suction side of an airfoil. Results from a CFD solver are compared to the experimental results and show good agreement. Furthermore, this work reports on the development of a low-order discrete vortex model meant to predict the lift of …
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Experimental wind tunnel study of airfoils with large flap deflections at low Reynolds numbers
… for four airfoils with trailing edge plain flaps in an attempt to understand the effects of Reynolds number, percent thickness (t/c), percent chord of flap (flap-chord ratio), and flap deflection on airfoil performance. The four airfoils used in this research were the AG40d-02r, AG455ct-02r, …
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Design and implementation of a piezoelectric servo-flap actuation system for helicopter rotor individual blade control
… X-Frame actuator to power a trailing edge servo-flap near the tip was also designed, manufactured and tested. A description of the design and composite manufacturing of the rotor blade and servo-flap is presented. Preliminary bench tests of the active blade actuation system are also presented. …
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An Experimental Investigation of Blown-Flap Airfoils
… In this thesis, the performance of blown-flap wings is investigated to provide both performance estimates and validation data for future work on blowing enabled aircraft. A quasi 2-dimensional wind tunnel model is used to conduct surveys on both the performance and flow characteristics of …
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Assessment of Model Validation, Calibration, and Prediction Approaches in the Presence of Uncertainty
… the airfoil with varying angles of attack and flap deflection angles. Each of these validation/calibration approaches will be assessed for their ability to tightly encapsulate the true value in nature at locations both where experimental results are provided and prediction locations where no …
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Flight envelope protection using flap hinge moment measurement
… experimental investigation of the sensitivity of flap hinge moment to airfoil surface contamination was conducted at the University of Illinois at Urbana-Champaign Aerodynamics Research Lab. Tests were conducted on two airfoil models, an NACA 3415 and an NACA 23012, at Reynolds numbers of 1.8 × …
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Wake deceleration of a racecar multielement airfoil in ground effect
… airfoil consisting of a main element and a flap for a fixed Reynolds number of Re = 1.1 x 10^6. The effects of ground clearance height on the main element decelerated wake were analyzed. The effects of varying flap ratio, flap deflection, angle of attack, and gap sizes on the wake …
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Performance of an airfoil with a power-saving, tab-assisted flap system
… input power with the use of a tab-assisted flap. Wind tunnel tests were conducted at the University of Illinois at Urbana-Champaign (UIUC) on a NACA 3415 airfoil model with a flap including a trim tab. Measurements were taken for two configurations: a baseline fixed tab case where tab …
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Effects of Flow Control on the Aerodynamics of a Tandem Inlet Guide Vane
… A linear cascade of five IGV's was tested with a flap deflection angle of 40 degrees and an inlet Mach number of 0.3. The Reynolds number based on the overall IGV chord length for these experiments was greater than 500,000. The inlet and exit angles of the IGV at this flap setting were 0 degrees …
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Numerical Assessment of the Performance of Jet-Wing Distributed Propulsion on Blended-Wing-Body Aircraft
… a jet-wing with deflected jets replacing flaps and slats and the associated noise. The purpose of this study was to assess the performance benefits of jet-wing distributed propulsion. The Reynolds-averaged, finite-volume, Navier-Stokes code GASP was used to perform parametric computational …
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Optimization Under Uncertainty and Total Predictive Uncertainty for a Tractor-Trailer Base-Drag Reduction Device
… uncertain wind speed and direction and uncertain deflection angles due to mounting accuracy and static aeroelastic loading; the best commercial device of non-optimized design achieves a 12% reduction at 65 mph. Another important outcome is the process by which the optimized design is obtained. …
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Design and Performance of Circulation Control Geometries
… research was to explore the design of the CC flap shape and how it influences the local flow field of the system, in attempt to improve the performance of existing CC flap configurations and provide insight into the aerodynamic characteristics of the geometric parameters that make up the CC …
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Large-scale swept-wing ice accretion modeling in the NASA Glenn Icing Research Tunnel using LEWICE3D
… CFD code, was used to calculate flows around the flapped-hybrid model in the IRT, mounted with the root at the floor and the tip at the ceiling of the test section. Inviscid analysis reveals that the upwash ahead of the model causes the local lift coefficient to increase significantly across the …