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<![CDATA[PEMBERDAYAAN PENGRAJIN PRODUK APEM DI DESA KADUBUNGBANG-CIMANUK-PANDEGLANG ]]>
<![CDATA[Akhmad Nidhomuz Zaman]]>;
<![CDATA[Santika Sari]]>;
<![CDATA[Fitri Wahyuni]]>;
<![CDATA[Noverdo Saputra]]>
<![CDATA[ Jurnal Abdi Masyarakat Vol. 4 No. 1 (2020): Jurnal Abdi Masyarakat November 2020 ]]>
Publisher : <![CDATA[Universitas Kadiri ]]>
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DOI: 10.30737/jaim.v4i1.1349
<![CDATA[ABSTRACTThe development of the industrial center area is one of the efforts to build a local economythat aims to construct commodity-based production of the village that is owned by the localcommunity. Community Service (PKM) is carried out in Kadubungbang-PandeglangVillage. PKM is done to assist in the empowerment of typical Pandeglang culinary businessin the home industry "Apem Bohay Barokah". The current problem is not yet maximized inapem marketing (in terms of packaging and sales that are still sold around the village).Marketing is assisted on the packaging side with contemporary packaging designs andmaking posters to be better known and known to the general public. PKM was accepted byApem Bohay Pandeglang's business. Marketing is not only done in terms of packagingproducts and banners but also assisted in terms of digitizing one of them with the androidapplication. It is hoped that this empowerment can be better known by the Pandeglangcommunity as well as expanding and establishing sustainable partnerships.Keywords: home industry, culinary, marketing, empowerment.ABSTRAKPembangunan kawasan sentra industri merupakan salah satu upaya untuk membangunperekonomian lokal yang bertujuan membangun produksi berbasis komoditas unggulanDesa yang dimiliki oleh masyarakat setempat. Pelaksanaan kegiatan Pengabdian KepadaMasyarakat (PKM) dilakukan di Desa Kadubungbang-Pandeglang. PKM yang dilakukanadalah membantu dalam pemberdayaan usaha kuliner khas pandeglang pada home industri“Apem Bohay Barokahâ€. Permasalahan saat ini adalah belum maksimal pada pemasaranapem (dari sisi pengemasan dan penjualan yang masih di jual disekitar Desa). Pemasaran dibantu pada sisi pengemasan dengan desain pengemasan yang kekinian serta membuat posteruntuk lebih dikenal dan diketahui khalayak umum. PKM diterima pihak usaha Apem BohayPandeglang. Pemasaran tidak hanya dilakukan dari sisi pengemasan produk dan spanduktetapi juga dibantu dari sisi digitalisasi salah satunya dengan aplikasi android. Diharapkanpemberdayaan ini bisa lebih di kenal masyarakat Pandeglang serta meluas dan terjalinkemitraan yang bekelanjutan.Kata kunci: home industri, kuliner, pemasaran, pemberdayaan]]>
<![CDATA[Influence of Slat Size Variation as Passive Flow Control Instruments on NACA 4415 Airfoil Toward Aerodynamic Performance ]]>
<![CDATA[James Julian]]>;
<![CDATA[Rizki Aldi Anggara]]>;
<![CDATA[Fitri Wahyuni]]>
<![CDATA[ International Journal of Marine Engineering Innovation and Research Vol 8, No 2 (2023) ]]>
Publisher : <![CDATA[Institut Teknologi Sepuluh Nopember ]]>
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DOI: 10.12962/j25481479.v8i2.16427
<![CDATA[Airfoil is a fundamental geometry in designing various aerodynamic objects. Passive flow control installation is essential in determining the airfoil's aerodynamic performance. The influence of variations in slat size as a passive flow control instrument is analyzed using the CFD method with a Reynold number of Re= 10^6. NACA 6641 airfoil was used as the slat geometry with size variations of 10%c and 16%c. Based on the computational results, variations in slat size have a substantial influence on the aerodynamic efficiency of the airfoil. Variations in slat size additional Cl ability to reach 20.6043% and 13.1917%, respectively. In addition, a 16%c slat can delay a stall until it reaches AoA ≥ 19°. Meanwhile, a 10%c slat can delay a stall until it reaches AoA ≥ 17°. However, variations in slat size also affect the resulting drag force. Slat measuring 16%c can addition Cd up to 50.9252%. Meanwhile, 10% c slat additional Cd up to 21.8389%. Based on the resulting lift-to-drag ratio curve, a 10%c slat has the lowest lift-to-drag ratio compared to a 16%c slat. However, a 10%c slat has the highest level of stability when compared to a 16%c slat installation and without a slat installation. ]]>
<![CDATA[Leading Edge Modification of NACA 0015 and NACA 4415 Inspired by Beluga Whale ]]>
<![CDATA[James Julian]]>;
<![CDATA[Waridho Iskandar]]>;
<![CDATA[Fitri Wahyuni]]>
<![CDATA[ International Journal of Marine Engineering Innovation and Research Vol 8, No 2 (2023) ]]>
Publisher : <![CDATA[Institut Teknologi Sepuluh Nopember ]]>
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DOI: 10.12962/j25481479.v8i2.16432
<![CDATA[This research modifies the leading-edge structure of NACA 0015 and NACA 4415 to resemble the nose of a beluga whale. The focus of this modification is to improve the airfoil's aerodynamic performance and investigate the changing fluid flow patterns. Numerical equation used is RANS combined with the k-ε turbulence model. Mesh independence test shows that mesh with 200 elements is the best mesh. Validation results reveal that CFD data can follow the trend of experimental data, especially on the AoA before the stall. There was a significant increase in Cl from NACA 0015 and NACA 4415 at AoA>9°. On the other hand, the modification also had a positive effect by lowering the Cd value. The modification also provides an advantage by increasing the maximum Cl/Cd value. Furthermore, the separation point data shows that the modification can delay the separation of the fluid flow in the airfoil. Modifications can cause an increase in pressure on the lower side and a decrease in pressure on the upper side. Through velocity contours and streamlines, the modifications can reduce the recirculation area. Overall, modifying the leading edge has positive impacts on the NACA 0015 and NACA 4415 airfoils.]]>
<![CDATA[Aerodynamic Performance Improvement on NACA 4415 Airfoil by Using Cavity ]]>
<![CDATA[James Julian]]>;
<![CDATA[Waridho Iskandar]]>;
<![CDATA[Fitri Wahyuni]]>;
<![CDATA[Nely Toding Bunga]]>
<![CDATA[ Jurnal Asiimetrik: Jurnal Ilmiah Rekayasa dan Inovasi Volume 5 Nomor 1 Tahun 2023 ]]>
Publisher : <![CDATA[Fakultas Teknik Universitas Pancasila ]]>
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DOI: 10.35814/asiimetrik.v5i1.4259
<![CDATA[This study uses a numerical method to analyze the cavity's use on the airfoil's trailing edge and the aerodynamic effects it generates. The type of airfoil used is NACA 4415. The variations in the Reynolds number examined in this study are 2×105 and 3×105. The governing equation is the Reynolds Averaged Navier-Stokes paired with the k-ε turbulence model. This study concludes that the cavity can increase Cl in the airfoil but cannot delay the stall. The increase in Cd is also a negative effect of using a cavity in the airfoil. The cavity can increase Cl by increasing the pressure on the lower side near the trailing edge. Meanwhile, the cavity increases Cd because it creates a separation of the fluid flow, forming a vortex when viewed in a streamlined form of fluid flow.]]>
<![CDATA[The The Effect of Micro Geometry with Various Forms as Passive Flow Control in NACA 4415 ]]>
<![CDATA[James Julian]]>;
<![CDATA[Rizki Aldi Anggara]]>;
<![CDATA[Fitri Wahyuni]]>;
<![CDATA[Nely Toding Bunga]]>
<![CDATA[ Jurnal Asiimetrik: Jurnal Ilmiah Rekayasa dan Inovasi Volume 5 Nomor 2 Tahun 2023 ]]>
Publisher : <![CDATA[Fakultas Teknik Universitas Pancasila ]]>
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DOI: 10.35814/asiimetrik.v5i2.4678
<![CDATA[This study investigates the effect of variations in the micro geometry with various forms as passive flow control devices on the aerodynamic capability of the airfoil. Micro-cylinder, micro-slat, and micro-cube are installed close to the leading edge of the NACA 4415 airfoil as a micro geometric variation of passive flow control devices with a predetermined diameter of 3% c located at coordinates x= 0% c and y= 8 %c of the leading edge of the airfoil. The Reynolds number used in this study is Re = with AoA variations from 0°-30°. This study's results show a decrease in Cl of 12% with a micro-cylinder, 26% with a micro-slat, and 28% with a micro-cube. In addition, the Cd produced by using the variation of the device micro geometry has increased significantly. Thus, the final result is a lift-to-drag ratio of more petite than the without micro. In the streamlined contour shown when the airfoil is at a high angle of attack, the use of micro geometric variations of passive flow control devices can have an effect that causes reduced recirculation that occurs in the airfoil. However, the impact of these devices is not optimal, resulting in a reduction in the aerodynamic capability of the NACA 4415 airfoil.]]>
<![CDATA[Analysis of the Use of Bio Flap on NACA 4415 with Numerical Methods ]]>
<![CDATA[James Julian]]>;
<![CDATA[Saphira Anggraita Siswanto]]>;
<![CDATA[Fitri Wahyuni]]>;
<![CDATA[Nely Toding Bunga]]>
<![CDATA[ Jurnal Asiimetrik: Jurnal Ilmiah Rekayasa dan Inovasi Volume 5 Nomor 2 Tahun 2023 ]]>
Publisher : <![CDATA[Fakultas Teknik Universitas Pancasila ]]>
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DOI: 10.35814/asiimetrik.v5i2.4768
<![CDATA[This study was conducted using the Computational Fluid Dynamics (CFD) method using the Reynolds Averaged Navier Stokes (RANS) approach. The type of airfoil used in this study is the asymmetry NACA 4415 airfoil type. In this paper, computational tests were carried out on the airfoil with the addition of bionic flaps on its trailing edge. This study's update tests three variations of the Reynolds number: Re = 106, Re = 5 × 105, and Re = 3 × 105. The airfoil test was carried out at AoA 0°–25°. The addition of bionic flaps causes a decrease in lift performance at low AoA, but at high AoA, it can increase lift performance on airfoils. In addition, adding a bionic flap on the airfoil can delay the occurrence of a stall. At AoA 10°–13°, the Cd of the three variations of the Reynolds number experiences an increase in performance. Then, from this computational test, the resulting Coefficient moment (Cm) is a pitch down because the torque is below zero.]]>
<![CDATA[ANALYSIS OF AERODYNAMIC PERFORMANCE OF EROSION AIRFOIL WITH REYNOLDS NUMBER VARIATIONS ]]>
<![CDATA[James Julian]]>;
<![CDATA[Waridho Iskandar]]>;
<![CDATA[Fitri Wahyuni]]>
<![CDATA[ Jurnal Ilmiah Teknologi dan Rekayasa Vol 28, No 2 (2023) ]]>
Publisher : <![CDATA[Universitas Gunadarma ]]>
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DOI: 10.35760/tr.2023.v28i2.8299
<![CDATA[Erosion on airfoil was investigated using computational methods to investigate changes in the performance of the airfoil. NACA 0015 used in this study has a chord length of 1 m, which is then used as a parameter in calculating the Reynolds number. The computational process is carried out with domain C with dimensions that have been arranged in such a way as to avoid the influence of the boundary on the computational results obtained in this study. The governing equation for this study is RANS which the standard k-ω turbulence model supports. Erosion has a considerable influence on changes in the aerodynamic performance of the airfoil. Erosion can significantly reduce the Cl value of the airfoil, especially at high AoA. Erosion of the airfoil results in an increase in the value of Cd. The increase in Cl value can be explained by visualizing the pressure contour around the airfoil. The pressure contour shows a decrease in pressure in the lower but an increase in the upper. The velocity and streamline contours can explain the cause of the increase in Cd, which is very clearly caused by the separation in the erosion area and on the upper surface of the airfoil.]]>
<![CDATA[HYDRODYNAMICS ANALYSIS OF JANUS SPHERE AT VARIATIONS OF THE REYNOLDS NUMBER ]]>
<![CDATA[James Julian]]>;
<![CDATA[Waridho Iskandar]]>;
<![CDATA[Fitri Wahyuni]]>
<![CDATA[ Jurnal Teknologi Vol 15, No 2 (2023): Jurnal Teknologi ]]>
Publisher : <![CDATA[Fakultas Teknik Universitas Muhammadiyah Jakarta ]]>
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DOI: 10.24853/jurtek.15.2.315-324
<![CDATA[The hydrodynamics of the homogeneous and Janus spheres were compared computationally at various Reynolds number variations. The Janus sphere is divided into two parts: slippery, which is set as a free-slip wall, and sticky, which is arranged as a free-slip wall. The equation used is the RANS equation for laminar fluid flow. Research focuses more on hydrodynamic forces and visualization of fluid flow by using velocity contours and streamlines. The domains of computational processes are arranged in a rectangular shape. The Richardson Extrapolation method verifies the mesh and gives the result that the meh variation is within the convergence range. Mesh with 105 elements is used for further computation because it only gives the lowest error of 0.129%. Meanwhile, the validation results show that the computational process can follow the experimental results at 0°≤θ≤80°. The Janus sphere is hydrodynamically better than the homogeneous sphere, where the Cl produced is larger and the Cd produced is smaller. The Janus sphere can prevent separation at a Reynolds number of 20 and reduce the recirculation area at a Reynolds number of 50.]]>
<![CDATA[Design and Performance Testing of a 3D Printed Mini DC Powered Pump for Microbubble Generator ]]>
<![CDATA[Tulus Hidayat Yusanto]]>;
<![CDATA[James Julian]]>;
<![CDATA[Fitri Wahyuni]]>;
<![CDATA[Adi Winarta]]>;
<![CDATA[I Wayan M. Managi Marlon Managi]]>
<![CDATA[ International Journal of Marine Engineering Innovation and Research Vol 8, No 4 (2023) ]]>
Publisher : <![CDATA[Institut Teknologi Sepuluh Nopember ]]>
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DOI: 10.12962/j25481479.v8i4.18826
<![CDATA[Centrifugal pumps are the most commonly utilized in industries, agriculture, and households. In the microbubble generator, the centrifugal pump is driven by a DC motor for efficiency. This research was conducted to determine the optimal centrifugal pump design for microbubble generators using 3D-printed PLA material. The pump drive uses a brushless DC motor. With impeller dimensions r1=16mm, r2=26mm, β1=46.8, β2=62.8, and number of blades = 8, the resulting head is 2m at a constant operational current of 3A and a flowrate of 0 L/m. The same operational current input yields a maximum flow rate of 14 L/min with a head of 0.5 m. Maximum head exists when there is no liquid on the outlet side. At current ≥ 6.5A, there is a deviation from the previously formed trend. The input power of 58W is generated when the maximum flow rate is 25L/m. Maximum efficiency can be achieved as the input current increases to ≤6.5A and 18L/m. At conditions ≥6.5A, efficiency decreases drastically as the input current increases. This centrifugal pump design can work optimally at a constant input current of 6.5A with an input power 58W for the microbubble generator.]]>
<![CDATA[The Influence of Mounting Angle on Gurney Flap on The Aerodynamics Performance of NACA 0015 Using CFD Method ]]>
<![CDATA[Mirza Fauzan Lukiano]]>;
<![CDATA[James Julian]]>;
<![CDATA[Fitri Wahyuni]]>;
<![CDATA[Waridho Iskandar]]>
<![CDATA[ International Journal of Marine Engineering Innovation and Research Vol 8, No 4 (2023) ]]>
Publisher : <![CDATA[Institut Teknologi Sepuluh Nopember ]]>
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DOI: 10.12962/j25481479.v8i4.18891
<![CDATA[Improving the airfoil aerodynamics is quite an essential aspect of the aviation industry. One method for improving airfoil aerodynamics involves applying passive flow control techniques. The effect of using the gurney flap as passive flow control was explored through the CFD approach with the RANS control equation and incorporating k-epsilon as a turbulence model. The airfoil model utilized in this study was the NACA 0015 airfoil operating at a Reynolds number of 1×106. This study explored three different mounting angles of the gurney flap, namely 45°, 60°, and 90°. The outcomes show that adding the gurney flap has positive results in increasing the lift and drag of the NACA 0015. An airfoil with a mounting angle flap of 45° has an average percentage increase in Cl of 23%, followed by a mounting angle flap of 60°, which is 28%, and a percentage Cl of 45% for a mounting angle flap of 90°. Meanwhile, Gurney flaps with a mounting angle of 45° can increase Cd by an average percentage of 3%, while mounting angle flap at 60° increases the Cd percentage by 4% and 5% for a mounting angle of 90°. Moreover, fluid flow visualization with pressure and velocity contours was given at AoA 10º to determine its effect on increasing lift and drag on the NACA 0015 airfoil.]]>
