An aerodynamic investigation was performed to assess the effectiveness of combined boundary layer suction and trailing edge blowing at reducing the blade profile losses and the wake momentum deficit of a cascade of tandem IGV's operating at realistic flow conditions. Two trailing edge blowing designs were tested: metal-angle blowing, which oriented the blowing jets very near to the blade exit angle, and deviation-angle blowing, which oriented the blowing jets at a significant deviation angle from the blade exit angle. Both blowing designs used the same boundary layer suction arrangement. 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 and 55 degrees, respectively. Tests performed with no flow control showed significant suction surface flow separation that generated large wakes with high losses and large momentum deficits. The application of boundary layer suction reduced the baseline pressure loss coefficient and wake momentum thickness by 22%. A suction mass flow of 0.4% of the passage flow was used to obtain these results. The addition of metal-angle blowing with the suction resulted in total reductions of 48% and 38% for the pressure loss coefficient and wake momentum thickness. A blowing mass flow of 3.1% of the passage flow was used in addition to 0.4% suction mass flow to obtain these results. The application of the deviation-angle blowing was detrimental to the aerodynamics of the IGV, as both the pressure loss coefficient and wake momentum thickness increased slightly over their suction-only values. This was attributed to a manufacturing defect which distorted the flow of the blowing jet. The results of the deviation-angle blowing experiments were not considered representative of the design intent and reinforced the importance of the hole design for creating a proper blowing jet. While low speed tests of this cascade showed results and trends very similar to those of previous research, the application of flow control proved to be less effective at higher speeds due to the generation of significantly larger wakes. / Master of Science

No description available.

A combined wing and propeller model is presented as a low-cost approach to preliminary modeling of slipstream effects on a finite wing. The wing aerodynamic model employs a numerical lifting-line method utilizing the 3D vortex lifting law along with known 2D airfoil data to predict the lift distribution across a wing for a prescribed upstream flowfield. The propeller/slipstream model uses blade element theory combined with momentum conservation equations. This model is expected to be of significant importance in the design of tail-sitter vertical take-off and landing (VTOL) aircraft, where the propeller slipstream is the primary source of air flow past the wings in some flight conditions. The algorithm is presented, and results compared with published experimental data.

No description available.

A Laser Inertial Fusion Energy (LIFE) target’s flight through a low Reynolds number and high Mach number regime was analyzed with computational fluid dynamics software. This regime consisted of xenon gas at 1,050 K and approximately 6,670 Pa. Simulations with similar flow conditions were performed over a sphere and compared with experimental data and published correlations for validation purposes. Transient considerations of the developing flow around the target were explored. Simulations of the target at different velocities were used to determine correlations for the drag coefficient and Nusselt number as functions of the Reynolds number. Simulations with different target angles of attack were used to determine the aerodynamic coefficients of drag, lift, Magnus moment, and overturning moment as well as target stability. The drag force, lift force, and overturning moment changed minimally with spin. Above an angle of attack of 15°, the overturning moment would be destabilizing. At angles of attack less than 15°, the overturning moment would tend to decrease the target’s angle of attack, indicating the lack of a need for spin for stability at these small angles. This stabilizing moment would cause the target to move in a mildly damped oscillation about the axis parallel to the free-stream velocity vector through the target’s center of gravity.

A parametric study was performed to observe and quantify the effect of varying turbulence intensities on separation and performance in a compressor cascade at low Reynolds numbers. Tests were performed at 25° and 37.5° stagger angle, negative and positive angles of incidence up until the point of full stall, Reynolds numbers from 6 x 104 to 12.5 x 104, and turbulence intensities from approximately 0.7% – 8%. Additionally, oil flow techniques were combined with static tap data to visualize the boundary layer characteristics at various test conditions. The overall performance of the cascade was presented and evaluated through mass-averaged total pressure loss coefficients. The results of the study showed that the best efficiency (lowest pressure loss coefficient) was determined by separation characteristics for any angle of attack. While adding turbulence generally delayed separation, in some cases, adding turbulence to a separated airfoil resulted in decreased performance. Very similar separation characteristics were observed for the full range of Reynolds numbers and stagger, with the higher stagger setting giving slightly better performance. It was shown that a large percentage of total pressure losses can be recovered by applying the appropriate turbulence intensity at any angle of attack, which is relevant to possibilities for active control of such flows. / Master of Science

An innovative experimental facility was developed for testing flush-mounted, diffusing serpentine inlets intended for use on blended-wing-body aircraft. The static ground test facility was able to simulate the boundary layer profile expected to be ingested by inlets mounted on the aft sections of these aircraft. It generated Mach numbers ranging from 0.19 to 0.4 and boundary layer thicknesses between 36% and 45%. The circumferential distortions at the aerodynamic interface plane of the serpentine inlet were also calculated, and ranged between 0.0042 for the lowest Mach number, to 0.0098 for the highest Mach number. Reynolds numbers for the tests ranged between 1.2 million and 2.4 million depending on engine speed and Mach number. The results of the experiment were compared to a previous NASA report, and showed close agreement in distortion patterns and pressure losses at a Mach number of 0.25. / Master of Science

The aim of this work is to study the in-vitro aerodynamic performance of a new inhaled theophylline formulation prepared by supercritical fluids technique. For the analysis of the output from the in-vitro tests (and further in-vivo tests) a new, fast, sensitive high performance liquid chromatographic (HPLC) method was developed and validated for the determination of theophylline and other related derivatives in aqueous and urine samples using new packing materials (monolithic columns). These columns achieve efficient separation under lower backpressure and shorter time comparing to other traditionally or newly introduced C18 columns. Solution enhanced dispersion by supercritical fluid (SEDS) process has been applied for the production of anhydrous theophylline as pure crystals in the range 2-5 ¿m to be used as new inhaled dry powder formulation for asthma. Fifteen theophylline samples have been prepared under different experimental conditions. The drug produced by this method has been subject to a number of solid-phase analytical procedures designed to establish the crystal structure [X-ray powder diffraction (XRPD)], the structure and conformation [(FTIR), Fourier-transform Raman spectroscopy (FT-Raman)], and the morphology and particle size [scanning electron microscope (SEM)]. While, thermal gravimetric analysis (TGA), and differential scanning calorimetry (DSC) have been used to monitor any phase transition or polymorphic changes after processing. All these analytical techniques gave a satisfactory indication of the solid-state chemistry of the processed particles and assess the development of new inhalation product. The performance of inhaled SEDS theophylline with or without a carrier was evaluated using the developed HPLC method. Three samples having different particle sizes were selected out of the prepared powders by SEDS technique to be tested. The dose sampling unit and the Anderson Cascade Impactor were used to determine the in-vitro emitted dose and the deposition profiles of SEDS samples, respectively. The effect of different inhalation flows was studied using two different flows 28.3, and 60 L min-1 with 4 L inhalation volume. Different DPI devices were investigated in this study; Easyhaler® and Spinhaler®. The particle size has an important effect on the aerodynamic behaviour and deposition profile of inhaled drug, the smaller the particles the greater the total lung deposition. The presence of a carrier improves the respirable fraction for all the tested formulations. / Egyptian Ministry of Higher Education

Currently available dry powder inhalers (DPIs) for drug delivery to the lungs require turbulent energy to generate and disperse aerosol particles in the respirable range ¿5¿m during inhalation. The patient's inspiratory effort together with the resistance inside the device creates this energy. Different inhalers provide varying degrees of resistance to inhalation flow and require different inhalation techniques for the generation and delivery of drug fine particles in respirable size range to the lungs. The aim of this research programme was to identify the influence of inhalation flow, inhalation volume and the number of inhalations per dose on the ex-vivo dose emission and the in-vitro aerodynamic dose emission characteristics of the salbutamol Accuhaler®, Easyhaler®, and Clickhaler® and the terbutaline Turbuhaler® DPIs. A high-performance liquid chromatography method for the assay of salbutamol sulphate and terbutaline sulphate in aqueous samples was modified and accordingly validated. In-vitro dose emission of the four different DPIs was measured using the pharmacopoeia method with modifications to simulate varying inhalation flows within patient and between patients. The ranges of the total emitted dose (% nominal dose) at the inhalation flow range of 10 - 60 Lmin-1, following one and two inhalations per metered dose for 2L and 4L inhaled volumes were as follows: the Accuhaler (52.64- 85.11; 61.88-85.11 and 59.23-85.11; 62.81-85.11); the Easyhaler (68.35-91.99; 79.94-91.99 and 73.83-92.51; 80.40-92.51); the Clickhaler (46.55-96.49; 51.12-96.49 and 51.18-101.39; 59.71-101.39) as well as the Turbuhaler (46.08-88.13; 51.95-88.13 and 48.05-89.22; 48.64-89.22). The results highlight that the four inhalers have flow-dependent dose emission property to a varying degree using 2L and 4 L inhaled volumes. There was no significant difference in the total emitted dose between a 2L inhaled volume and a 4L inhaled volume at each inhalation flow. Furthermore, the total emitted dose from the Easyhaler®, Clickhaler®, and Turbuhaler® was significantly (p¿0.001) greater with two inhalations than one inhalation per metered dose across the range of inhalation flow (10 ¿ 60) Lmin-1. This effect was only observed at inhalation flow less than 30 Lmin-1 with the Accuhaler®. Overall there is a significant difference in the total emitted dose. The ex-vivo dose emission of the four different DPIs has been determined using the In- Check Dial device to train twelve non-smoking healthy adult volunteers to inhale at slow (30 Lmin-1) and fast (60 L min-1) inhalation flows through the device with its dial set corresponding to each inhaler. Subsequently each volunteer inhaled at the trained inhalation flows through each active inhaler. The local ethics committee approval was obtained prior to the study and all volunteers gave signed informed consent. The results obtained demonstrate that the studied inhalers have flow-dependent dose emission, thereby enhancing confidence in the use of the In-Check Dial® to identify a patient¿s inhalation flows through a variety of DPIs. Also the total emitted dose determined by ex-vivo methodology was significantly (p¿0.05) greater with two inhalations than one inhalation per metered dose. The results of the in-vitro aerodynamic dose emission characteristics highlight that the fine particle dose (FPD) from the four studied inhalers is flow dependent. Also the minimum inhalation flow to generate the (FPD) with the appropriate characteristics for lung deposition has been identified to be 20 L min-1 for the Accuhaler®, Easyhaler® and Clickhaler®, while that for the Turbuhaler® is about 30 L min-1. Also the inhalation volume above 2L and the number of inhalations for each dose have respectively no significant (p¿0.05) influence on the FPD emitted from the four studied inhalers. The results support the present instructions to patients using these inhalers to inhale once for each dose as fast as they can.

This study provides, for the first time, an ex vivo comparative evaluation of formulations of budesonide with crystallised β-form mannitol, commercial DPI grade mannitol and lactose. The lactose-budesonide was the marketed Easyhaler® 200 g formulation. Ex vivo assessment of deposition using the Easyhaler® multi-dose high resistance inhaler with reservoir was compared with the RS01® single dose capsule low resistance inhaler at two different inhalation rates. Aerodynamic characteristics, flow and surface energies were investigated together with in vitro and ex vivo assessment of drug deposition. Dose emission was greater for all formulations with higher inhalation flow, indicating greater detachment of drug from carrier, and greater with the Easyhaler®, highlighting the importance of correct device for formulation. Emission was lowest at both inhalation rates for crystallised mannitol due to poor flowability associated with elongated particle shape which resulted in interception deposition. Surface energies were also implicated; closely matched polar surface energy of carrier and drug may be an important inhibiting factor. The promising aerodynamic characteristics of crystallised mannitol with the RS01® inhaler and lactose-budesonide from in vitro assessment were not supported by ex vivo results, highlighting the need for careful selection of device.