Response distortion on personality tests in applicants: Comparing high-stakes to low-stakes medical settings

Preprint and supplementary material to accompany Anglim, J., Bozic, S., Little, J., Lievens, F. (2017). Response Distortion on Personality Tests in Applicants: Comparing High-Stakes to Low-Stakes Medical Settings. Advances in Health Science Education. http://dx.doi.org/10.1007/s10459-017-9796-8 1. item level characteristics for the NEO-PI3 (i.e., mean, standard deviation, percentages for each response option, loading on first factor). See Excel file. 2. Supplementary analyse

Racial differences in systemic sclerosis disease presentation: a European Scleroderma Trials and Research group study

Objectives. Racial factors play a significant role in SSc. We evaluated differences in SSc presentations between white patients (WP), Asian patients (AP) and black patients (BP) and analysed the effects of geographical locations.Methods. SSc characteristics of patients from the EUSTAR cohort were cross-sectionally compared across racial groups using survival and multiple logistic regression analyses.Results. The study included 9162 WP, 341 AP and 181 BP. AP developed the first non-RP feature faster than WP but slower than BP. AP were less frequently anti-centromere (ACA; odds ratio (OR) = 0.4, P < 0.001) and more frequently anti-topoisomerase-I autoantibodies (ATA) positive (OR = 1.2, P = 0.068), while BP were less likely to be ACA and ATA positive than were WP [OR(ACA) = 0.3, P < 0.001; OR(ATA) = 0.5, P = 0.020]. AP had less often (OR = 0.7, P = 0.06) and BP more often (OR = 2.7, P < 0.001) diffuse skin involvement than had WP.AP and BP were more likely to have pulmonary hypertension [OR(AP) = 2.6, P < 0.001; OR(BP) = 2.7, P = 0.03 vs WP] and a reduced forced vital capacity [OR(AP) = 2.5, P < 0.001; OR(BP) = 2.4, P < 0.004] than were WP. AP more often had an impaired diffusing capacity of the lung than had BP and WP [OR(AP vs BP) = 1.9, P = 0.038; OR(AP vs WP) = 2.4, P < 0.001]. After RP onset, AP and BP had a higher hazard to die than had WP [hazard ratio (HR) (AP) = 1.6, P = 0.011; HR(BP) = 2.1, P < 0.001].Conclusion. Compared with WP, and mostly independent of geographical location, AP have a faster and earlier disease onset with high prevalences of ATA, pulmonary hypertension and forced vital capacity impairment and higher mortality. BP had the fastest disease onset, a high prevalence of diffuse skin involvement and nominally the highest mortality

THE LAST ACHIEVEMENTS IN THE DEVELOPMENT OF A ROCKET GRADE HYDROGEN PEROXIDE CATALYST CHAMBER WITH FLOW CAPACITY OF 1 KG/S

Worldwide, the hybrid rocket propulsion technology gained in importance recently. A new innovative hybrid rocket engine concept is developed at the German Aerospace Center (DLR) within the program “AHRES”. This rocket engine is based on hydroxyl-terminated polybutadiene with metallic additives as solid fuel and rocket grade hydrogen peroxide (high test peroxide: HTP) as liquid oxidiser. Instead of a conventional ignition system, a catalyst chamber with a silver mesh catalyst is designed, to decompose the HTP to steam and oxygen at high temperatures up to 615 °C. The newly modified catalyst chamber is able to decompose up to 1.3 kg/s of 87,5% HTP. Used as a monopropellant thruster, this equals an average thrust of 1600 N. The catalyst chamber consists of the catalyst itself, a mount for the catalyst material, a retainer, an injector manifold and a casing. Furthermore, a pressure sensor, a mass flow sensor and a thermocouple can be attached to measure the properties of the decomposition products. With the described catalyst chamber a number of tests under steady conditions are carried out using 87.5 %wt hydrogen peroxide with different flow rates and constant amount of catalyst material. The chamber is mounted on a test-bed, which comprises attachment, peroxide storage, feed system, valves, data acquisition and control. By determination of the decomposition temperature the integrity of decomposition is verified and compared to theoretical prediction. The catalyst chamber is designed using the self-developed software tool SHAKIRA. A short description of the tool features is given. The applied kinetic law which determines catalytic decomposition of HTP within the catalytic chamber is also given and commented. Several calculations are carried out to determine the appropriate geometry for complete decomposition with a minimum of catalyst material. The experimental results show good agreement with the results generated by the design tool. The developed catalyst chamber provides a simple, reliable ignition system for hybrid rocket propulsion systems based on hydrogen peroxide as oxidiser. The system is capable for multiple re-ignitions without the need to meet an optimal ignition point. Such a system behaves like a hypergolic engine in terms of ignition, but no hazardous substances are required. The developed hardware and software can be used to design full scale monopropellant thrusters based on HTP and catalyst chambers for hybrid rocket engines. Both concepts are under considerations within DLR

Numerical Simulation of the Flow and Combustion inside the Reaction Chamber of the AHRES Hybrid Rocket Engine

Within the AHRES program of DLR, the Institute of Aero-dynamics and Flow Technology is developing a software tool for the design of hybrid rocket engines. Therefore, the Department Spacecraft is operating a lab-scale hybrid rocket engine for ground tests with high test peroxide (87.5 wt.%) as liquid oxidizer and hydroxyl-terminated polybutadiene with aluminum additives as solid fuel. With-in this study, the AHRES hybrid rocket engine is computed through numerical simulations of the flow and the combustion process inside the reaction chamber. Namely, three characteristic points in burning time are determined within 2D axial symmetric steady-state simula-tions. These simulations are carried out applying the DLR TAU-Code with the implemented reaction models for chemical equilibrium and non-equilibrium conditions

CFD Simulation of Chemical Non‐Equilibrium Reacting Flow within the AHRES Hybrid Rocket Engine

Within this study, the flow and the combustion process inside the reaction chamber of the AHRES engine is discussed based on several 2D and 3D steady-state simulations carried out with the DLR flow solver TAU. The computed engine is a lab-scale hybrid rocket engine for ground tests, operated by the DLR - Institute of Aerodynamics and Flow Technology in the project ATEK. It is propelled with hydrogen peroxide as oxidizer and HTPB with different additives as fuel. A first comparison of numerical simulation and ground test results is realized and shows good agreements with globally measured values

Numerical Simulation of the Flow and Combustion inside the Reaction Chamber of the AHRES Hybrid Rocket Engine

Within the AHRES program of DLR, the Institute of Aero-dynamics and Flow Technology is developing a software tool for the design of hybrid rocket engines. Therefore, the Department Spacecraft is operating a lab-scale hybrid rocket engine for ground tests with high test peroxide (87.5 wt.%) as liquid oxidizer and hydroxyl-terminated polybutadiene with aluminum additives as solid fuel. With-in this study, the AHRES hybrid rocket engine is computed through numerical simulations of the flow and the combustion process inside the reaction chamber. Namely, three characteristic points in burning time are determined within 2D axial symmetric steady-state simula-tions. These simulations are carried out applying the DLR TAU-Code with the implemented reaction models for chemical equilibrium and non-equilibrium conditions