مولانا احتشام الحسن کاندہلوی
افسوس ہے ہمارے عزیز اور فاضل دوست مولانااحتشام الحسن کاندہلوی بھی گزشتہ نومبر میں شدید علالت کے بعد انتقال کرگئے۔مولانا کاندہلہ کے رئیسوں میں شمار ہوتے تھے لیکن ان کا مشغلہ تبلیغی کتابوں کی تصنیف وتالیف اور مطالعہ کے سوا کچھ نہ تھا۔شب وروز اسی میں بسر ہوتے تھے اور گفتگو کاموضوع بھی بس یہی ایک بات ہوتی تھی۔تبلیغی جماعت کے طریق کارسے ان کو اختلاف تھا۔وہ کہا کرتے تھے کہ تبلیغ تو نام ہی اسلام کوغیر مسلموں تک پہنچانے کا ہے۔ مرض الوفات میں مبتلاہونے سے ایک ماہ قبل علی گڑھ آئے اور ایک ہفتہ کے قریب قیام کیا۔ان دنوں میں ان سے کئی مرتبہ ملاقات ہوئی اورہرملاقات میں وہ اپنے اس محبوب موضوع پرتقریر کرتے رہے ہیں۔میں حسب عادت خاموش سنتا رہا اور بولا کچھ نہیں۔مرض الوفات میں انھوں نے بڑی سخت تکلیف اٹھائی لیکن صبر ورضا کادامن ہاتھ سے نہیں چھوڑا۔ بڑے خلیق اورعابد وزاہد بزرگ تھے۔اﷲ تعالیٰ ابرار وصلحا کامقام عطا فرمائے آمین۔ [جنوری ۱۹۷۲ء]
In the contemporary era of conspiracy theories and practices through media prejudice, focused scholarship and policy oriented publication, Islam in general and Muslims in specific are being tinted as anti-peace and social prosperity entities. Quran as the primary source of Islamic jurisprudence provides principals for every aspect of society including polity one. This study focuses on basic Quranic injections regarding politics and their role in developing peace in contemporary society. The compatibility of Islam and democracy is one of the hottest debates among researchers of political science are also to be focusedon the study. Applyinghermeneuticsmethod and analyzing thought of key Muslim political thinkers and interpreters, this paper concludes that Quranic injections of polity and state are a vibrant source of developing peace and prosperity in historical perspective and same applicable in contemporary society, but hegemony forces feeling fear of Islamic resurgence state that Islam and democracy are incompatible and these Quranic sources are being used for creating panic in the present world.
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.