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Indra Lohani
Indra Lohani (17 April 1968 – 16 January 2009) was a prominent Nepalese Lawyer, political talk-show host, and news reporter mostly known for his television political talk-show Bahas aired on Nepal Television and later on Kantipur Television as Kantipur Bahas.

Early Years
Lohani was born in Lakhanpur-8, Rangapur Village of Jhapa district, Nepal to father Sharada Prashad Lohani and mother Harimaya Lohani. He was Sharada Prashad and Harimaya's second child, among his five siblings. Known to be an average student, he attended a government school for his secondary education before going to the capital city Kathmandu to join college at Nepal Law Campus with major in Law. He later attended National College of Banglore in Banglore, India to receive his LLM degree.

Career
Soon after returning Nepal from Banglore he started his legal firm Legal Research Associates in Kathmandu, at the same time attending Nepal Law Campus for further studies. His career as a television personality started when he started doing a political talk-show named Bahas in the national television of Nepal. With his strict nature and the habit of straight forward questioning, he soon attracted significant attention from the viewers who would eagerly wait for him to provoke critical issues, especially while interviewing politicians, in his talk-shows. During the period of Monarchy, before 2006 revolutions, his show in the government-controlled Nepal Television started getting heavily censored due to his strict behavior when it came up to political interviews. This led him to quit the show at Nepal Television, but soon starting the show in a privately-controlled television, Kantipur Television, under the name Kantipur Bahas. The show still remained a favorite to its audiences and attracted even more attention after the peoples' revolution of 2006 when people had renewed interests in the country's changing politics.

Personal Life
Lohani was married to Sushma Dubedi in 24th of April 1999. The couple has two daughters, Samragi and Subhangi.

Death
Lohani's demise occurred due to a cardiac arrest while speeding his vehicle, around 8 pm in the evening of 16th January 2009. His funeral was attended by thousands of people at the Pashupati Temple Cremation Area.

Shcramjet
A Shock-Induced Ramjet Engine (abbreviated as Shcramjet; also called Oblique Detonation Wave Engine (ODWE), or simply referred to as Shock-Ramjet Engine) is a new concept in airbreathing ramjet engines, proposed to be used for hypersonic, as well as, single-stage-to-orbit (SSTO) propulsion applications. From the overall design point of view, the shcramjet engine is similar to a scramjet engine; however, unlike the diffusive mode of combustion in scramjet engine, a shcramjet engine combustion takes place across a very thin region of standing oblique shock and/or detonation waves stabilized over a wedge, blunt body etc. Since combustion in a shcramjet engine is confined to very short region across the igniting wave, the combustor length in a shcramjet can be significantly shorter than the scramjet that requires a lengthy combustor for complete fuel-air mixing and combustion. Hence, compared to scramjet, the shcramjet has a reduced overall weight (which directly leads to substantial reduction in overall vehicle weight of a hypersonic waverider design) and higher efficiency. Also, the shcramjet is believed to have a better overall propulsive performance than the scramjet at higher Mach numbers, especially above Mach 12. These potantial advantages of shcramjet has recently attracted substantial efforts into their research all around the world.

Basic Principles
The shcramjet engine geometry is extremely simple and closely similar to scramjet, the only major difference being the combustor design. The engine includes a supersonic inlet followed by a combustion chamber and a nozzle, respectively. The design principle for a shcramjet inlet is similar to a scramjet, in which the whole nose structure of waverider vehicle is used as inlet. Combustion in a shcramjet can occur in two different modes, shock-induced combustion or detonation combustion, depending on the strength of inducing shock at any Mach number. If ignition occurs far enough downstream that the ensuing combustion process does not influence the preceeding shock, the combustion is said to be shock-induced. However, for extremely fast reactions, ignition occurs close to the preceeding shock wave and the combustion process couples with the shock wave and forms a detonation wave. Therefore detonation wave ramjet, or oblique detonation wave engine, is only a particular case of shcramjet. Though shock and detonation waves are related to high total pressure loss during combustion, the theoretical total pressure loss associated with shcramjet combustor approaches that of the scramjet engine at increasing Mach numbers. This fact,together with simpler engine geometry with concomitant increase in component efficiencies, result in possible superior predicted performance of the shcramjet compared to scramjet at flight Mach numbers beyond 12.