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ساغر جعفری

ساغر جعفری(۱۹۱۳ء۲۰۰۲ء) کا اصل نام محمد حسین جعفری ہے۔ آپ سیالکوٹ میں پیدا ہوئے۔ ساغر جعفری ایک پختہ گو شاعر تھے۔ ان کا کلام’’ادبِ لطیف‘‘،’’ساقی‘‘،’’رومان‘‘ اور دیگر ملکی سطح کے رسائل و جرائد میں چھپتا رہا۔ساغر جعفری رومانوی تحریک سے وابستہ رہے۔ (۶۵۹) انھوں نے غزل ،نظم،گیت ،قطعہ ،نعت ،منقتبت،مرثیہ ،سلام،ماہیہ ،اور ہائیکو میں طبع آزمائی کی۔ آپ اقبال کی قومی و ملی شاعری سے بہت متاثر تھے۔ قومیت و وطنیت کے حوالے سے اقبال کا رنگ ساغر جعفری کی شاعری میں واضح طورپر نظر آتا ہے۔

’’بہارو نگار‘‘ ساغر جعفری کا پہلا مجموعہ کلام ہے۔ جس کا پہلا ایڈیشن ۱۹۹۵ء میں شائع ہوا۔ اس مجموعے کے صفحات دو سو چوبیس ہیں۔ا س کا پیش لفظ ڈاکٹر وحید قریشی اور تعارف احمد ندیم قاسمی نے لکھا ہے۔ اس مجموعے میں غزلیں ،ہائیکو اور ماہیے شامل ہیں۔ دوسرا شعری مجموعہ ’’برگِ گل‘‘ کے نام سے ۱۹۹۵ء میں شائع ہوا۔ اس مجموعے کے صفحات کی تعداد ایک سو چھہتر ہے۔ اس میں ان کی نظمیں ،غزلیں اور گیت شامل ہیں۔ برگِ گل میں مشاہیر پاکستان بالخصوص قائد اعظم اور اقبال کی خدمات پر انھیں خراجِ عقیدت پیش کیا گیا ہے۔ ان کے علاوہ میرانیس اور مرزا دبیر کے فکری و فنی اثرات کا اظہار بھی ہے۔ اس کتاب کا دیباچہ ڈاکٹر وزیر آغا اور تعارف ظہیر کا شمیری نے لکھا ہے۔

ساغر جعفری کا تیسرا شعری مجموعہ ’’دائرے‘‘ ہے۔ جو ۱۹۹۶ء میں شائع ہوا۔ اس کے صفحات کی تعداد ایک سو چوراسی ہے۔ اس مجموعے میں غزلیں اور قطعات شامل ہیں۔ اس کتاب کا مقدمہ ڈاکٹر انور سدید نے لکھا ہے۔ اس کے قطعات کا بڑا موضوع اخلاقی ،معاشرتی اور سماجی مسائل ہیں۔

’’جامِ مودت‘‘ ساغر کا چوتھا شعری مجموعہ ہے جو ۱۹۹۷ء میں شائع ہوا۔ اس کا فلیپ علامہ...

Multivariate Analysis of Rotifers Community from Safari Zoo Lake Lahore, Pakistan

Rotifers are zooplanktons that react more sharply to the environmental changes. Objective: To better understand the community composition of rotifers in Safari Zoo Lake, Lahore, PakistanMethods: wecollected 16 water samples on monthly basis, dividing lake into four major sites: northern, southern, eastern, and western sites. Each of these was further subdivided into four locations, for a total of 16 sampling sites. A total 23 rotifer species were recorded from the lake with Brachionus calyciflorus having maximum abundance. A species abundance curve was plotted between months and number of species of rotifers indicating their lowest and highest abundance through the study period. Results: A Cluster Analysis yielded three main groups of closely related species including species like Brachionus quadridentatus, Synchaeta stylata and Brachionus calyciflorusetc. We used a Principal Component Analysis (I and II) to study variation in the rotifer community on a seasonal basis and among sampling sites. A biplot of Principal Component Analysis (PCA I) reflected the relationship of rotifers with the months. Some of the species showed a positive positive relationship, while others showed negative one. PCA II was plotted between months and physico-chemical parameters showing their negative and positive relations. Conclusions: We conclude that a lesser replacement of fresh water, increased density of waterfowl, reptilia and solid waste left overduring boating has resulted in eutrophication of lake leading to overall low diversity of rotifers observed

Improved Technique for the Calculation of Heat Transfer in a Thrust Chamber

Advancements in rocket propulsion have been the key factor for the scientific progress especially in space exploration and communication. The continued quest to achieve higher propulsion velocities at low cost still provides the room to the scientists and engineers to work on the development in the design of thrust chamber of a rocket engine. Given the high manufacturing and operational cost of rocket engines, precise knowledge of the chamber dynamics, propellants flow and feed system, heat transfer and structural integrity are important. During operations the thrust chamber experiences high temperatures and pressures, thus a reliable design requires adequate knowledge of the flow and combustion physics inside the chamber. A number of ways have been employed by the researchers to optimize heat transfer and performance of the engine. Generally regenerative cooling along with film cooling are used for safe operation.For small LPREs with small mass flow rates of the coolant, safety of the chamber wall becomes challenging job. Structural integrity can be attained by specific heat transfer rate and efficient combustion will give better performance. Numerical estimation of heat transfer using commercial software may be help for design and mounting instrumentation for experimentation at proper place. However one requires an integrated design tool for designing a thrust chamber with optimal performance ensuring adequate thrust, structural integrity and efficient cooling. For optimization of such a thrust chamber, couple fluid-structure-heat transfer analysis is often complicated and requires huge computational resources using commercial software. The combustion chemistry is often approximated through one dimensional theory. Generally experimental/empirical correlations are used for heat transfer rate calculations or one has to rely on expensive testing to validate structural design and safe operation. However the high cost involved with experimentation and manufacturing of even a small chamber, an integrated tool for optimal design of thrust chamber can be helpful. The optimized geometry can be numerically simulated for confirmation before leading to actual use. The integrated design tool can help in obtaining optimal thrust under given dimensional and flow constrains with adequate heat transfer rates ensuring low design cost. The major aim of this research work was to develop an in-house integrated software tool for the design and optimization of the coolant channel configuration of thrust chamber of a rocket engine. However, the study also includes the experimentation and CFD study for the validation of the tool developed. The developed integrated tool includes seven modules providing optimal performance parameters for a given thrust chamber design. The modules include combustion chemistry, flow dynamics, heat transfer and optimal cooling channels design for a given thrust chamber shape. Here the results obtained from the integrated tool have been verified using own computational fluid dynamics results and experimental data as well as the published results available in the literature. Amongst the important parameters, heat transfer rate within the thrust chamber is key design parameter. Here focus is on the prediction of heat transfer rates and surface temperatures of both coolant and thrust chamber. Thus results for the heat transfer rates and heat transfer coefficients are compared with published results, numerical simulations and experimental data. Further calculations for the optimized coolant geometry have been carried out based on the heat transfer, flow rate and pressure drop across the coolant channel. The results indicate that the predicted geometry offers safe operation of the thrust chamber. The integrated tool developed in this study is intelligent enough to optimize a number of coolant channel flow configurations with different coolants and fuels within a short time.
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