In recent years, airports have experienced increasing airport congestion, partially due to the hub-and-spoke model on which airline operations are based. Current airline operations utilize large airports, focusing traffic to a small number of airports. One way to relieve such congestion is to transition to a more accessible and efficient point-to-point operation, which utilizes a large web of smaller airports. This expansion to regional airports propagates the need for next-generation low-noise aircraft with short take-off and landing capabilities. NASA has attacked this problem with a high-lift, low-noise concept dubbed the Cruise Efficient Short Take-Off and Landing (CESTOL) aircraft. The goal of the CESTOL project is to produce aircraft designs that can further expand the air travel industry to currently untapped regional airports. One method of obtaining a large lifting capability with low noise production is to utilize circulation control (CC) technology. CC is an active flow control approach that makes use of the Coanda effect. A high speed jet of air is blown over a wing flap and/or the leading edge of the wing, which entrains the freestream flow and effectively increases circulation around the wing. A promising tool for predicting CESTOL aircraft performance is computational fluid dynamics (CFD,) due to the relatively low cost and easy implementation in the design process. However, the unique flows that CC introduces are not well understood, and traditional turbulence modeling does not correctly resolve these complex flows (including high speed jet flow, complex shear flows and mixing phenomena, streamline curvature, and other challenging flow phenomena). The recent derivation of the v2-f turbulence model shows theoretical promise in increasing the accuracy of CFD predictions for CC flows, but this has not yet been assessed in great detail. This paper presents a methodical verification of several variations on the v2-f turbulence model. These models are verified using simple, well-understood flows. Results for CC flows are compared to those obtained with more traditional turbulence modeling techniques (including the Spalart-Allmaras, k-ε, and k-ω turbulence models). Wherever possible, computed results are compared to experimental data and more accurate numerical methods. Results indicate that the v2-f turbulence models predict some aspects of circulation control flow fields quite well, in particular the lift coefficient. The linear v2-f, nonlinear v2-f, and nonlinear v2-f-cc turbulence models have generated lift coefficients within 19%, 14%, and -26%, respectively of experimental values, whereas the Spalart-Allmaras, k-ε, and k-ω turbulence models produce errors as high as 85%, 36%, and 39%, respectively. The predicted stagnation points and pressure coefficient distributions match experimental data roughly as well as standard turbulence models do, though the modeling of these aspects of the flow do show some room for improvement. The nonlinear v2-f-cc turbulence model shows very non-physical skin friction coefficient profiles, pressure coefficient profiles, and stagnation points, indicating that the streamline curvature correction terms need attention. Regardless of the source of the discrepancies, the v2-f turbulence models show promise in the modeling of circulation control flow fields, but are not quite ready for application in the design of circulation control aircraft.

The ability to predict the distance required for an aircraft to takeoff is an essential component of aircraft design. It involves aspects related to each of the major aircraft systems: aerodynamics, propulsion, configuration, structures, and stability and control. For an aircraft designed for short takeoffs and landings (STOL), designing the aircraft to provide a short takeoff distance, or more precisely the balanced field length (BFL), often leads to the use of a powered lift technique such as circulation control (CC). Although CC has been around for many years, it has never been used on a production aircraft. This is in part due to the lack of knowledge as to how well CC can actually perform as a high lift device. This research provides a solution to this problem. By utilizing high fidelity computational fluid dynamics (CFD) aerodynamic data, a four-dimensional design space which was populated and modeled using a Monte Carlo approach, and a Gaussian Processes regression technique, an effective aerodynamic model for CC was produced which was then used in a BFL simulation. Three separate models were created of increasing quality which were then used in the BFL performance calculations. A comprehensive gridding methodology was provided as well as computational and grid dependence error analysis. Specific consideration was given to the effect of resolving the turbulent boundary layer in both the gridding and solving processes. Finally, additional turbulence model validation work was performed, both to match previously performed experimental data and to provide a comparison of different models’ abilities to predict separation.

Active pneumatic flow control methods as applied to aerospace applications have shown noteworthy improvements in lift compared to traditional means. The General Aviation Circulation Control (GACC) concept currently under investigation at NASA's Langley Research Center (LaRC) is an attempt at addressing some of the fundamental obstacles related to the successful development and implementation of such techniques. The primary focus of research in the field of high lift pneumatic devices is to investigate ways of obtaining significant improvements in the lift coefficient without resorting to moving surfaces. Though it has been demonstrated that the lift coefficient can be amplified in a variety of ways, the chosen method for the current work is via enhanced circulation stemming from a trailing edge Coanda jet. A secondary objective is to reduce the amount energy expenditure used in these pneumatic techniques by implementing time-variant flow. This paper describes experimental observations of the flow behavior at the trailing edge of a modified water tunnel based supercritical airfoil model that exploits both steady and pulsed Coanda driven circulation control. A total of 10 sets of data, excluding a baseline case of no Coanda jet, were sampled with five cases each for steady and pulsed flow, the latter at a reduced frequency, f+, of 1. Two cases of equal momentum coefficient but with varying forced frequencies were isolated for further study in an attempt to accurately compare the resultant flow dynamics of each method. All measurements were taken at a zero-lift angle of attack by means of a non-invasive time accurate flow visualization technique (DPIV). Vorticity behavior was investigated using Tecplot® and a MATLAB® program was developed to quantify the Strouhal Number of time-averaged velocity fluctuations moving aft of the Coanda surface for each case. / Master of Science

Eftersom användningen av små UAV:s (Unmanned Aerial Vehicles) fortsätter att öka, harbullret från deras framdrivningssystem blivit ett ökande problem. Denna rapport är resultatetav ett masterprojekt med målet att utveckla en framdrivningsmetod med låga bullernivåerför små UAV:s.Projektet startade med en informationssökning där målet var att hitta information ombullerkällor i nuvarande system samt information om de fundamentala sätten på vilket luftflödekan skapas.När informationssökningen var färdig, genererades ett stort antal olika koncept. Konceptetsom författarna ansåg ha mest potential, var en propeller med en ny metod för passivkontroll av gränsskiktet. Konceptet har ett luftintag nära rotationscentrum. Efter att luftenhar kommit in i detta luftintag, leds den genom interna kanaler och accelereras radiellt utåtpå grund av centrifugalkraften. Luften sprutas sedan ut genom en slits nära framkantenpropellerbladets lågtryckssida. Denna ström av luft färdas över propellerbladet och sugsin genom en slits nära vingens bakkant. Därefter sprutas luften ut genom ett utlopp närapropellerbladets spets.Tanken är att den beskrivna metoden ska fördröja eller förhindra avlösning. Detta skullepotentiellt möjliggöra högre lyftkraft vid lägre rotationshastigheter, vilket därigenom potentielltsänker bullernivåerna. Förenklade modeller av det valda konceptet har utvecklats ochanalyserats med hjälp av CFD (Computational Fluid Dynamics) och jämförts med simuleringarav en referensmodell utan gränsskiktskontroll. Resultaten indikerar att flödet ikonceptmodellen strömmar genom kanalerna och över propellerbladet som det var tänkt.Lyftkraften och effektiviteten ökade med 4.3 % respektive 1.9 %, jämfört med referensmodellen,vid samma rotationshastighet. Den möjliga minskningen av rotationshastigheten pågrund av ökningen i lyftkraft resulterar i en minskning av bullernivån med 0.9 dB. Detbör noteras att resultaten från simuleringarna bör ses med försiktighet och att ytterligarearbete måste göras innan några definitiva slutsatser kan dras beträffande potentiella prestandaökningarav konceptet jämfört med en konventionell propeller. / As the use of small UAVs (Unmanned Aerial Vehicles) keeps increasing, the noise emittedfrom their propulsion systems have become an increasing issue. This report is the resultof a master thesis project with the aim of developing a propulsion method with low noiseemissions for small UAVs.The project started with a background study, where the aim was to find informationabout sources of noise in current systems and information about the fundamental ways inwhich air flow can be created.When the background study was finished, a large number of different concepts were generated.The concept that the authors considered having the most potential, was a propellerwith a new method for passive circulation control. The concept has an air intake close tothe rotational center. After air has entered this inlet it is led through internal channels andis accelerated radially outwards due to centrifugal forces. The air is then ejected through aslot close to the leading edge on the low pressure side on the propeller blade. This stream ofair travels over the propeller blade and is the sucked in through a slot close to the trailingedge. After this, the air is ejected through an outlet close to the propeller blades tip.The idea is that the method described should delay or prevent boundary layer separation.This would potentially allow for higher thrust at lower rotational speeds, thus potentiallylowering the noise emissions. Simplified models of the chosen concept have been developedand analyzed using CFD (Computational Fluid Dynamics) and compared to simulations ofa baseline model with no circulation control. The results indicate that the fluid flow in theconcept model flows through the channels and over the propeller blade, as intended. Thethrust and efficiency were increased by 4.3 % and 1.9 % respectively, compared to the baselinemodel, at the same rotational speed. The possible reduction of the rotational speed due tothe increase in thrust, results in a reduction of the noise level by 0.9 dB. It should be notedthat the results from the simulations should be viewed with caution and the that furtherwork needs to be done before any clear conclusions can be drawn regarding the potentialperformance increase of the concept compared to a conventional propeller.

With the advantage of modern high speed computers, there has been an increased interest in the use of first-principles based computational approaches for the aerodynamic modeling of horizontal axis wind turbine (HAWT). Since these approaches are based on the laws of conservation (mass, momentum, and energy), they can capture much of the physics in great detail. The ability to accurately predict the airloads and power output can greatly aid the designers in tailoring the aerodynamic and aeroelastic features of the configuration. First-principles based analyses are also valuable for developing active means (e.g., circulation control), and passive means (e.g., Gurney flaps) of reducing unsteady blade loads, mitigating stall, and for efficient capture of wind energy leading to more electrical power generation. In this present study, the aerodynamic performance of a wind turbine rotor equipped with circulation enhancement technology (trailing edge blowing or Gurney flaps) is investigated using a three-dimensional unsteady viscous flow analysis. The National Renewable Energy Laboratory (NREL) Phase VI horizontal axis wind turbine is chosen as the baseline configuration. Prior to its use in exploring these concepts, the flow solver is validated with the experimental data for the baseline case under yawed flow conditions. Results presented include radial distribution of normal and tangential forces, shaft torque, root flap moment, surface pressure distributions at selected radial locations, and power output. Results show that good agreement has been for a range of wind speeds and yaw angles, where the flow is attached. At high wind speeds, however, where the flow is fully separated, it was found that the fundamental assumptions behind this present methodology breaks down for the baseline turbulence model (Spalart-Allmaras model), giving less accurate results. With the implementation of advanced turbulence model, Spalart-Allmaras Detached Eddy Simulation (SA-DES), the accuracy of the results at high wind speeds are improved. Results of circulation enhancement concepts show that, at low wind speed (attached flow) conditions, a Coanda jet at the trailing edge of the rotor blade is effective at increasing circulation resulting in an increase of lift and the chordwise thrust force. This leads to an increased amount of net power generation compared to the baseline configuration for moderate blowing coefficients. The effects of jet slot height and pulsed jet are also investigated in this study. A passive Gurney flap was found to increase the bound circulation and produce increased power in a manner similar to the Coanda jet. At high wind speed where the flow is separated, both the Coanda jet and Gurney flap become ineffective. Results of leading edge blowing indicate that a leading edge blowing jet is found to be beneficial in increasing power generation at high wind speeds. The effect of Gurney flap angle is also studied. Gurney flap angle has significant influence in power generation. Higher power output is obtained at higher flap angles.