A Design Procedure to Modify the Trailing Edge Upper Surface Pressure Gradient of a Given Aerofoil. G.U. Aero Report 8408

Summary: Little is known about the detailed flow on the upper surface of aerofoils, prone to trailing edge separation, during the process of dynamic stall. The present report describes a method whereby the pressure gradient on the trailing edge upper surface of a given aerofoil may be modified to either enhance or reduce such separations, for a given section, whilst retaining the leading edge pressure distribution

A Design Procedure to Modify the Trailing Edge Upper Surface Pressure Gradient of a Given Aerofoil. G.U. Aero Report 8408

Summary: Little is known about the detailed flow on the upper surface of aerofoils, prone to trailing edge separation, during the process of dynamic stall. The present report describes a method whereby the pressure gradient on the trailing edge upper surface of a given aerofoil may be modified to either enhance or reduce such separations, for a given section, whilst retaining the leading edge pressure distribution

An Investigation into the Three-Dimensional Stall Development on a Modified NACA 23012 Aerofoil. G.U. Aero Report 8414

No abstract available

Collected Data for Tests on a NACA 23012A Aerofoil

Herein is presented the collected data for tests in which a NACA 23012A aerofoil was subjected to a variety of displacements in pitch about the quarter-chord location at low Reynolds numbers

Collected Data for Tests on a NACA 23012A Aerofoil

Herein is presented the collected data for tests in which a NACA 23012A aerofoil was subjected to a variety of displacements in pitch about the quarter-chord location at low Reynolds numbers

A view on the internal consistency of linear source identification for I.C. engine exhaust noise prediction

[EN] Considerable efforts have been devoted to the development of predictive models that, from a certain set of data related to an engine, and making use of an adequate representation of the effect of the silencing elements, provide an estimate of the exhaust noise emitted. Such models should allow for the consideration of the engine and its interaction with the exhaust system. This is properly achieved by gas-dynamic models, which are becoming the standard, but linear models solved in the frequency domain and representing the engine as a linear time-invariant source may still play a role in exhaust system design, as the engine is treated as a black box. Such a representation is very attractive for engine manufacturers, since it gives the possibility to provide data on the engine without any possibility to trace back to its real characteristics. In order to provide additional criteria for the suitability of the application of a linear time-invariant representation to an engine exhaust, in this paper a multi-load method has been used to extract source characteristics from gas-dynamic simulation results. The details of the method, in which the resulting over-determined system is solved by fitting the values of the source parameters in a least-squares sense, are described, and different approaches are used in order to check the internal consistency of the source representation: the identification of pressure and velocity sources, and the application of the least-squares criterion to the modulus or to the real and imaginary parts separately. In particular, eight different determinations of the source impedance are obtained and, considering the application of the formalism to an engine exhaust, the differences observed provide a suitable criterion for the evaluation of the suitability of the representation and of the particular set of loads chosen.Macian Martinez, V.; Torregrosa Huguet, AJ.; Broatch, A.; Niven, P.; Amphlett, S. (2013). A view on the internal consistency of linear source identification for I.C. engine exhaust noise prediction. Mathematical and Computer Modelling. 57(7-8):1867-1875. doi:10.1016/j.mcm.2011.12.018S18671875577-

Real-world Outcomes of Sequential Androgen-receptor Targeting Therapies with or Without Interposed Life-prolonging Drugs in Metastatic Castration-resistant Prostate Cancer

_Background:_ Cross resistance between androgen-receptor targeting therapies(ARTs) (abiraterone acetate plus prednisone [ABI + P] or enzalutamide [ENZ]) fortreatment of metastatic castration-resistant prostate cancer (mCRPC) may affectresponses to second ART (ART2). _Objective:_ To establish treatment duration and prostate-specific antigen (PSA)response of ART2 in real-world mCRPC patients treated with or without otherlife-prolonging drugs (LPDs; ie, docetaxel, cabazitaxel, or radium-223) betweenART1 and ART2. _Design, setting, and participants:_ Castration-resistant prostate cancer patients,diagnosed between 2010 and 2016 were retrospectively registered in Castra-tion-resistant Prostate Cancer Registry (CAPRI). Patients treated with both ARTswere clustered into two subgroups: ART1 > ART2 or ART1 > LPD > ART2

Multicenter Comparison of Molecular Tumor Boards in The Netherlands: Definition, Composition, Methods, and Targeted Therapy Recommendations

Background: Molecular tumor boards (MTBs) provide rational, genomics-driven, patient-tailored treatment recommendations. Worldwide, MTBs differ in terms of scope, composition, methods, and recommendations. This study aimed to assess differences in methods and agreement in treatment recommendations among MTBs from tertiary cancer referral centers in The Netherlands. Materials and Methods: MTBs from all tertiary cancer referral centers in The Netherlands were invited to participate. A survey assessing scope, value, logistics, composition, decision-making method, reporting, and registration of the MTBs was completed through on-site interviews with members from each MTB. Targeted therapy recommendations were compared using 10 anonymized cases. Participating MTBs were asked to provide a treatment recommendation in accordance with their own methods. Agreement was based on which molecular alteration(s) was considered actionable with the next line of targeted therapy. Results: Interviews with 24 members of eight MTBs revealed that all participating MTBs focused on rare or complex mutational cancer profiles, operated independently of cancer type–specific multidisciplinary teams, and consisted of at least (thoracic and/or medical) oncologists, pathologists, and clinical scientists in molecular pathology. Differences were the types of cancer discussed and the methods used to achieve a recommendation. Nevertheless, agreement among MTB recommendations, based on identified actionable molecular alteration(s), was high for the 10 evaluated cases (86%). Conclusion: MTBs associated with tertiary cancer referral centers in The Netherlands are similar in setup and reach a high agreement in recommendations for rare or complex mutational cancer profiles. We propose a “Dutch MTB model” for an optimal, collaborative, and nationally aligned MTB workflow. Implications for Practice: Interpretation of genomic analyses for optimal choice of target therapy for patients with cancer is becoming increasingly complex. A molecular tumor board (MTB) supports oncologists in rationalizing therapy options. However, there is no consensus on the most optimal setup for an MTB, which can affect the quality of recommendations. This study reveals that the eight MTBs associated with tertiary cancer referral centers in The Netherlands are similar in setup and reach a high agreement in recommendations for rare or complex mutational profiles. The Dutch MTB model is based on a collaborative and nationally aligned workflow with interinstitutional collaboration and data sharing

An Investigation into the Three-Dimensional Stall Development on a Modified NACA 23012 Aerofoil. G.U. Aero Report 8414

No abstract available

Reattachment Studies of an Oscillating Airfoil Dynamic Stall Flow Field

The reattaching flow over an oscillating airfoil executing large amplitude sinusoidal motion around a mean angle of attack of 10 degrees has been studied using the techniques of stroboscopic schlieren, two component laser Doppler velocimetry and point diffraction interferometry, for a free stream Mach number of 0.3 and a reduced frequency of 0.05. The results show that the dynamically stalled flow reattaches in a process that begins when the airfoil is very close to the static stall angle on its downward stroke and progresses over the airfoil through a large range of angles of attack as the airfoil angle decreases to about 6 degrees. The airfoil suction peak shows a dramatic rise as the static stall angle is approached and the velocity profiles develop such that the flow near the surface is accelerated. The process completes through the disappearance of a separation bubble that forms over the airfoil.Army Research Office grant (MIPR-ARO-132-90) to the Naval Postgraduate SchoolAFOSR (MIPR-91-0007)NAVAIRArmy Research Office grant (MIPR-ARO-132-90) to the Naval Postgraduate SchoolAFOSR (MIPR-91-0007)NAVAI