Harness open educational resources in higher education : progress, issues and challenges

Technology proliferation, has transformed higher education to a student controlled centered-based teaching and learning environment. The change of attitude towards the students by the institutions has shifted students' learning environment into a more active role as collaborators. This degree of openness through creating and developing of Open Educational Resource (OER) material can be more productive than the traditional learning environment, but main barriers related to copyright law should be addressed. Furthermore, research on comparative effectiveness is required to streamline and optimize the process, in addition to incorporating support of OER creation and development recognition into university policies

Intellectual property development reciprocation on distance learning education: a review of the law & policies, challenges and recommendations

Distance learning education via computer enabled technologies had created nontraditional off-site learners where better student engagement shifted towards organized content leadership to facilitate courseware delivery. The new teaching model caused concerns with regards to course material ownership and intellectual property rights (IPR), which prompted new legislations and policies to be put in place. University policies, while acknowledging ownership should be maintained by faculty, have a higher number of exemptions tailored for collection of a certain percentage of royalties. This reinforced faculty concerns of infringement of academic freedom of expression. Studies demonstrated raising awareness of IPR among faculty and students should be exercised

Using Socrative to enhance in-class student engagement and collaboration

Learning and teaching experiment was designed to incorporate SRS-Student Response System to measure and assess student engagement in higher education for level 5 engineering students. The SRS system was based on getting an immediate student feedback to short quizzes lasting 10 to 15 minutes using Socrative software. The structure of the questions was a blend of true/false, multiple choice and short answer questions. The experiment was conducted through semester 2 of yearlong engineering module. The outcome of the experiment was analyzed quantitatively based on student performance and qualitatively through student questionnaire. The results indicate that using student paced assessments method using Socrative enhanced student’s performance. The results showed that 53% of the students improved their performance while 23% neither improved nor underperformed. Qualitative data showed students felt improvement in their learning experience. Overall results indicate positive impact using this technology in teaching and learning for engineering modules in higher educatio

Theoretical prediction of critical pyrolysate mass fluxes of a material to mitigate spacecraft or planetary habitat fire

Future deep space exploration and plans for planetary settlements prompted researchers to address variety of challenging engineering problems. One problem is developing materials that can mitigate an event of interplanetary spacecraft fire. A numerical simulation of piloted ignition delay time of solid fuel material for PMMA sample, subjected to various incident radiant heat fluxes and airflows was developed based on thermo-chemical solid phase model. The model incorporates, conduction, convection, surface re-radiation and radiation surface absorption heat transfer modes and solid phase chemical degradation described by first order Arrhenius law chemistry. The predicted surface temperature rise adequately captured the measured surface temperatures for forced air flow velocities induced by buoyancy relevant to normal gravity environments. Based on the measured onset temperature of ignition the critical pyrolysate, fuel vapour mass flow rate was deduced in normal gravity conditions. The critical fuel vapour mass flow rate relevant to interplanetary environment was extrapolated based on normal gravity data. The results highlights the urgent need for space policy makers and stake holders to provide more funding directed towards design and fabrication of ground based facilities simulating planetary environments in order to enhance and leverage future planetary habitat designs with capabilities of mitigation on board events of fires

MELUKIS DENGAN TEKNIK CAMPURAN LILIN DAN CAT AIR DALAM PEMBELAJARAN SISWA KELAS V SDN JATIROWO 1 KEC.DAWARBLANDONG KAB.MOJOKERTO

ABSTRAK Pelaksanaan pembelajaran SBK di kelas V SDN Jatirowo 1, materi seni budaya dan keterampilan (SBK) untuk materi melukis/ menggambar, seorang guru hanya memerintahkan siswanya tanpa memberikan teori atau contoh secara rinci. Media yang biasanya siswa menggunakan buku gambar dan pensil. Sehingga siswa kurang ada minat untuk belajar melukis/ menggambar. Peneliti ingin mengenalkan melukis dengan teknik campuran lilin dan cat air, dengan tujuan agar siswa tertarik dan berminat untuk belajar menggambar. Berdasarkan latar belakang tersebut, masalah yang diangkat adalah : 1) Bagaimana proses yang dilakukan dalam pembelajaran melukis dengan teknik campuran lilin dan cat air siswa kelas V SDN Jatirowo 1? , 2) Bagaimanakah hasil yang diperoleh dalam pembelajaran melukis dengan teknik campuran lilin dan cat air siswa kelas V SDN Jatirowo 1?, 3) Bagaimanakah tanggapan guru dan siswa kelas V SDN Jatirowo 1 terhadap pembelajaran melukis dengan teknik campuran lilin dan cat air? Penelitian ini bertujuan untuk mendeskripsikan proses, hasil dan tanggapan yang diperoleh dalam melukis menggunakan teknik campuran lilin dan cat air dalam pembelajaran siswa kelas V SDN Jatirowo 1 Kec.Dawarblandong, Kab.Mojokerto. Penelitian ini menggunakan jenis penelitian deskriptif kualitatif, tidak menyajikan angka – angka yang di analisis secara statistik melainkan berupa uraian deskriptif dari hasil yang di laksanakan, tetapi memungkinkan memakai angka dalam uji validitas. Sumber data utama diperoleh dari proses pembelajaran yang dilakukan di ruang kelas V SDN Jatirowo 1 dengan menggunakan instrumen pengamatan. kegiatan analisis digunakan untuk membandingkan data domain yang berisi tentang melukis dengan teknik campuran lilin dan cat air dengan hasil wawancara dan pembagian angket kuesioner. Data-data tersebut kemudian dibandingkan untuk mendapatkan kontras antar keduanya sebagai analisis komponensial. Melalui komponensial tersebut kemudian menjadi hasil dari validitas data. Hasil penelitian melukis dengan teknik campuran lilin dan cat air dari 17 siswa, hampir seluruhnya telah dapat memahami dan mempraktikan materi melukis menggunakan lilin dan cat air. Berdasarkan hasil penelitian tersebut dapat diambil simpulan bahwa menggunakan lilin dan cat air dalam melukis, dapat menambah wawasan dan memberikan pengalaman baru bagi siswa. Selain itu tanggapan dari guru dan siswa tentang pelaksanaan melukis dengan teknik campuran lilin dan cat air bisa menumbuhkan semangat dalam melukis/ menggambar. Kata Kunci: Lilin dan Cat Air, Teknik Melukis, Pembelajaran   ABSTRACT SBK implementation in class V SDN Jatirowo 1, art and culture material (SBK) for painting / drawing material, a teacher only ordered his students without giving theory or detailed example. Media that students usually only know the media from the drawing book and pencil. So that students have less interest to learn painting / drawing. Researchers want to introduce a painting with a mixture of wax and watercolors, with the aim that students interested and interested to learn to draw. Based on this background, the issues raised are: 1) How is the process done in learning to paint with a mixture of wax and watercolor technique of grade V SDN Jatirowo 1? , 2) How did the results obtained in learning to paint with a mixture of wax and watercolor technique of class V student SDN Jatirowo 1 ?, 3) How do teachers and students responded in grade V SDN Jatirowo 1 to painting learning with mixed wax and watercolor technique? This study aims to describe the process, results and responses obtained in painting using a mixture of wax and watercolor techniques in the learning of class V SDN Jatirowo 1 Kec.Dawarblandong, Kab.Mojokerto. This research uses descriptive qualitative research type, does not present figures that are statistically analyzed but descriptive descriptive of the results that are carried out, but allows using numbers in the validity test. The main data source is obtained from the learning process conducted in classroom V SDN Jatirowo 1 by using the observation instrument. activity analysis is used to compare domain data that contains about painting with mixed technique of wax and watercolor with result of interview and questionnaire questionnaire. The data are then compared to obtain the contrast between the two as a component analysis. Through the component then becomes the result of data validity. The results of painting test with a mixture of wax and watercolor techniques from 17 students, almost entirely have been able to understand and practice painting materials using wax and watercolors. Based on the results of this study can be concluded that using wax and watercolor in painting, can add insight and provide new experiences for students. In addition, responses from teachers and students about the execution of painting with a mixture of wax and watercolors can foster the spirit in painting / drawing. Keywords: Candle and Watercolor, Painting Technique, Learnin

Aerodynamic flow characteristics of utilizing delta wing configurations in supersonic and subsonic flight regimes

Computational fluid dynamic tests are performed on delta wing models at different heights and speeds in order to achieve lift and drag coefficient values. Primarily, testing was done at supersonic speeds to reveal the advantages of these wing configurations at supersonic flight regimes at a cruise speed and altitude. The low speed characteristics are also examined, important for take-off and landing regimes where the distinctive vortices become prominent. Throughout the two flight conditions tested, a simple delta wing model (with a straight swept wing) is compared to a delta wing model that exhibited a ‘LERX’ (leading edge root extension). Provided literature describes how the performance of delta wings can be improved through this inclusion. Results obtained from the tests show that the model with the LERX has a small, but significant, performance improvement over the simple delta model, in respect to the maximum achievable lift coefficient and maximum stall angle. Lift to drag ratio is not improved however, due to the large vortices creating pressure drag. Generally, the delta wing models produce relatively small amounts of drag, and slightly less lower lift, when at low angles of attack. This is primarily due to the geometry of the models that have thin leading edges and also low thickness to chord ratios

Numerical investigation for the enhancement of the aerodynamic characteristics of an aerofoil by using a gurney flap

Numerical investigation was carried out to determine the effect of a Gurney Flap on NACA 0012 aerofoil performance with emphasis on Unmanned Air Vehicles applications. The study examined different configurations of Gurney Flaps at high Reynolds number of 3.6×105 in order to determinethe optimal configuration. The Gurney flap was tested at different heights, locations and mounting angles. Compared to the clean aerofoil, the study found that adding the Gurney Flap increased the maximum lift coefficient by19%, 22%, 28%, 40% and 45% for the Gurney Flap height of 1%C, 1.5%C, 2%C, 3%C and 4%C respectively, C represents the chord of the aerofoil. However, it was also found that increasing the height of the gurney beyond 2%C leads to a decrease in the overall performance of the aerofoil due to the significant increase in drag penalty. Thus, the optimal height of the Gurney flap for the NACA 0012 aerofoil was found to be 2%C as it improves the overall performance of the aerofoil by 21%. As for the location, it was found that the lifting-enhanced effect of the gurney flap decreases as it is shifted towards the leading edge. Thus the optimal location of the Gurney Flap mounting was found to be at the trailing edge or at distances smaller than 10%C. The Gurney flap was also tested at different mounting angles of -45, 90 and +45 degrees and it was found that the Gurney flap at +45 mounting angle leads to the optimal performance of the aerofoil

Flow control through vortex shedding interaction of one cylinder downstream of another

This study investigates the vortices produced between two 2d cylinders, and the relationship between the structures of the vortices produced at both cylinders when one is placed in the wake flow of another. CFD simulations using ANSYS Fluent were used to determine the coefficients of lift and drag, as well as the frequency of vortex shedding and size of vortices at three separate Reynolds numbers of 16000, 32000 and 65000 in different arrangements. Each arrangement of cylinders was compared against controls, which consisted of a single cylinder to determine the alteration of forces produced. Two trip wires at 7 different angles of 40, 45, 50, 55, 60, 65, and 70 degrees were then investigated at a Reynolds number of 65000 which was compared to the smooth cylinder control forces and frequency of vortex shedding. The most optimum angle of trip wires was then combined with linear cylinder arrangements also at a Reynolds number of 65000 for comparison with only the upstream cylinder utilizing the trip wires

Design, development and testing of shape shifting wing model

The design and development of morphing (shape shifting) aircraft wings—an innovative technology that has the potential to increase the aerodynamic efficiency and reduce noise signatures of aircrafts—was carried out. This research was focused on reducing lift-induced drag at the flaps of the aerofoil and to improve the design to achieve the optimum aerodynamic efficiency. Simulation revealed a 10.8% coefficient of lift increase for the initial morphing wing and 15.4% for the optimized morphing wing as compared to conventional wing design. At angles of attack of 0, 5, 10 and 15 degrees, the optimized wing has an increase in lift-to-drag ratio of 18.3%, 10.5%, 10.6% and 4% respectively when compared with the conventional wing. Simulations also showed that there is a significant improvement on pressure distribution over the lower surface of the morphing wing aerofoil. The increase in flow smoothness and reduction in vortex size reduced pressure drag along the trailing edge of the wing as a result an increase in pressure on the lower surface was experienced. A morphing wing reduced the size of the vortices and therefore the noise levels measured were reduced by up to 50%

Computational fluid dynamics investigation into flow behavior and acoustic mechanisms at the trailing edge of an airfoil

Airfoil self-noise or trailing edge noise and shear noise was investigated computationally for a NACA0012 airfoil section, focusing on noise mechanisms at the trailing edge to identify and understand sources of noise production using ANSYS Fluent. A two-dimensional computational fluid dynamics simulation has been performed for 0°, 8° and 16° airfoil angle of attack capturing surface pressure contours, contours of turbulent intensity, contours of surface acoustic power level, vorticity magnitude levels across the airfoil profile, and x and y directional self and shear noise sources across the airfoil profile. The results, indicate that pressure gradients at the upper surface do increase as the angle of attack increase which is a measure of vortices near the surface of the trailing edge associated with turbulence cease as the boundary layer begins to separate. Comparison of the turbulent intensity contours with surface acoustic power level contours demonstrated direct correlation between the energy contributed by turbulent structures (i.e. vortices), and the level of noise measured at the surface, and within the boundary layer of the airfoil. As angle of attack is increased both x and y sources have the same trends, however, y sources (perpendicular to the free-stream flow) appear to have a bigger impact as angle of attack is increased. Furthermore, as the angle of attack increased, shear noise contributes less and less energy further downstream of the airfoil, and becomes dominated by noise energy from vortical structures within turbulence. The two-dimensional computational fluid dynamics simulation revealed pressure, turbulent intensity and surface acoustic power contours, that further corroborated the previously tested noise observations phenomena at the trailing edge of the airfoil