scholarly journals An integrated measurement approach for the determination of the aerodynamic loads and structural motion for unsteady airfoils

2021 ◽  
Vol 103 ◽  
pp. 103293
Author(s):  
C. Mertens ◽  
A. Sciacchitano ◽  
B.W. van Oudheusden ◽  
J. Sodja
Keyword(s):  
Aerodynamic Loads ◽  
Structural Motion ◽  
Measurement Approach

Application of pressure sensitive paint for determination of aerodynamic loads and moments on propeller blade

2006 ◽  
Author(s):  
V. P. Kulesh ◽  
V. E. Mosharov ◽  
A. A. Orlov ◽  
S. P. Ostroukhov ◽  
V. N. Radchenko
Keyword(s):  
Pressure Sensitive Paint ◽  
Propeller Blade ◽  
Aerodynamic Loads ◽  
Pressure Sensitive

Rapid Determination of Analytical Aerosol Size Characteristics

1986 ◽  
Vol 40 (8) ◽  
pp. 1166-1169 ◽  
Author(s):  
R. K. Skogerboe ◽  
S. J. Freeland ◽  
K. G. Kronholm
Keyword(s):  
Atomic Absorption ◽  
Rapid Determination ◽  
Cascade Impactor ◽  
Size Measurement ◽  
Absorption System ◽  
Droplet Sizes ◽  
Measurement Biases ◽  
The Masses ◽  
Measurement Approach

A method in which a cascade impactor is interfaced directly to an atomic absorption system to allow measurements of the masses of analyte associated with various droplet sizes is described. Data are presented which indicate that this measurement approach conveniently provides results equivalent to those obtained by the indirect protocol used by others [see M. S. Cresser and R. F. Browner, Spectrochim, Acta 35B, 73 (1980)] when a filter is used to collect the analyte transported through the impactor. In addition to saving analysis time while providing reliable results, the method is shown to prevent positive size measurement biases due to failure to collect aerosol not trapped by an impactor.

Aerodynamic Loads on a Darrieus Rotor Blade

1983 ◽  
Vol 105 (1) ◽  
pp. 53-58 ◽  
Author(s):  
R. E. Wilson ◽  
P. B. S. Lissaman ◽  
M. James ◽  
W. R. McKie
Keyword(s):  
Rotor Blade ◽  
Accurate Determination ◽  
Vortex Sheet ◽  
Numerical Results ◽  
Speed Ratio ◽  
Aerodynamic Loads ◽  
Tip Speed Ratio ◽  
Circle Plane ◽  
Darrieus Rotor

A free-vortex analysis of a Darrieus rotor blade in nonsteady motion has been developed. The method uses the circle theorem to map a moving airfoil into the circle plane. The wake is modeled using point vortices. Nascent vortex strength and position are determined from the Kutta condition so that the nascent vortex has the same strength as a vortex sheet of uniform strength. The force on the airfoil is determined by two methods, integration of the pressure over the plate and from the impulse of the wake vortices. Both methods yield the same numerical results. A comparison with an analytical solution for a plunging airfoil gives excellent agreement. Results are shown for a one-bladed Darrieus Rotor at a tip speed ratio of three and two chord sizes. The numerical results indicate that the forces and moment on a Darrieus Rotor blade may be adequately approximated by quasisteady relationships although accurate determination of the local velocity and circulation are still required.

scholarly journals ANALISA PENGUKURAN BEBAN MODAL RISIKO OPERASIONAL METODE BASIC INDICATOR APPROACH (BIA) DAN ADVANCE MEASUREMENT APPROACH (AMA) DI BANK EFG

2020 ◽  
Vol 21 (1) ◽  
pp. 14-20
Author(s):  
Edian Fahmy
Keyword(s):  
Value At Risk ◽  
Goodness Of Fit ◽  
Geometric Distribution ◽  
Operational Risk ◽  
Risk Capital ◽  
Loss Distribution ◽  
Indicator Approach ◽  
External Events ◽  
Measurement Approach

This study aims to compare the magnitude of operational risk losses between the Basic Indicator Approach (BIA) method, and the loss distribution model in the Advanced Measurement Approach (AMA) approach so as to provide a more realistic picture for banks to determine the operational risk capital burden that must be provided based on the causes Operational risks are as follows Internal Process, Human and External Events. Measurement of operational risk capital burden by the AMA method is the determination of frequency of loss distribution, determination of severity of loss distribution, testing with goodness of fit test, then compilation of aggregated loss distribution, calculation of Operational Value at Risk (OpVar), testing the model with back testing and comparison of capital adequacy from the results of the calculation of the Basic Indicator Approach (BIA) and the Advance Measurement Approach (AMA). The results of research based on the BIA require an operational risk capital cost of Rp.291,652,000,000. The results of the research on the AMA approach use the frequency of loss distribution parameter for the internal causes of the process with a Geometric distribution of 0.17561, while for the human cause of 0.08511, for the cause of external events amounting to 0.83721. Determination of Frequency of Loss Distribution using Goodness of Fit for internal processes, people and external events. The results of the Operational Value at Risk (OpVar) with a geometric distribution pattern, then the maximum loss that can arise due to human factors is Rp.24,114,480,096, -, for internal process factors of Rp.6,010,929,367, whereas for external causes for Rp. 2,161,092,909. In total operational risk capital needs through the AMA method of Rp. 32,286,502,372.

scholarly journals Medidas de riesgo para riesgo operacional con un modelo de perdida agregada de Poisson-Lindley

2010 ◽  
pp. 1
Author(s):  
Agustín Hernández Bastida ◽  
Pilar Fernández Sánchez
Keyword(s):  
Risk Measures ◽  
Predictive Distribution ◽  
Loss Distribution ◽  
Gamma Distributions ◽  
Loss Distribution Approach ◽  
Aggregate Loss ◽  
Aggregate Loss Distribution ◽  
High Level ◽  
Measurement Approach

En este trabajo se considera la determinación de medidas de riesgo en riesgo operacional, es decir, la determinación de cuantiles de alto orden. Se considera la aproximación basada en la distribución de la pérdida dentro de la aproximación avanzada. Se calculan, y se comparan entre si, las medidas de riesgo a partir de la distribución de la pérdida agregada y a partir de la distribución predictiva considerando como funciones estructura para los perfiles de riesgo las distribuciones Triangular y Gamma.<br /><br />This paper considers the determination of the risk measures in Operational Risk, i.e. the determination of a high level quantile. The Loss Distribution Approach in the Advanced Measurement Approach is adopted. The risk measures, obtained from the aggregate loss distribution and from the predictive distribution are determined and compared, using the Triangular and Gamma distributions as structure functions of the risk profiles.<br />

Calculation of aircraft’s aerodynamic loads using flight data records

2020 ◽  
Vol 130 ◽  
pp. 7-17
Author(s):  
Bartosz Dalba ◽  
Jerzy Manerowski
Keyword(s):  
Computer Software ◽  
Point Of View ◽  
Flight Mechanics ◽  
Key Factors ◽  
Mathematical Methods ◽  
Flight Data ◽  
Aerodynamic Loads ◽  
Engine Thrust ◽  
And Control

From the point of view of assessing the aircraft in the field of flight mechanics interesting are loads acting on it. The ability to plan and then coordinate the use of engine thrust and control surfaces to make appropriate changes to aircraft’s thrust, drag, lift and weight are key factors in assessing its performance. The balance between these forces must always be controlled during the flight, and better the understanding of them (these forces) and how to control them, the greater the pilot’s skill in operating the aircraft. The article presents a method of determining these loads using records from the on-board flight data recorder. Aerodynamic loads acting on the aircraft during take-off were determined in the article based on mathematical methods and experimental flight mechanics equations. The key element of this work is computer software, developed based on equations mentioned above, which allows to calculate the loads. The use of appropriate flight mechanics equations allowed to obtain results in the form of aerodynamic loads – lift, drag and friction – acting on the aircraft during take-off. Work results can be used together with a computer program in operational practice. The results were obtained based on parameters from the flight data recorder. The equations and methodology presented in the article have enabled the development of a computer tool that allows calculation of aerodynamic loads and determination of aircraft’s characteristics.

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