Legalization Of Legalization For Recreational Marijuana

It has been called Maryjane, Pot, Reefer, Ganga, Green and many other names, but this little plant seems to be causing a big controversy in recent decades. Can Marijuana really help us or is it a problem in the making? This question may seem simple, but in reality, it is more complex of an issue than we think. The opposing sides of legalization for recreational marijuana are so varied with many points of view to consider. Only a few of those views will be addressed in this article with simplified information to speak plainly on the subject. Bringing notice to the areas of the criminal justice system, economic revenue and wider medicinal availability versus the many public health concerns for adults and adolescents. Legalization for recreational marijuana seems to be the battle of a new age. Let us look at where legalization has made its mark so far. â€Å"In November 2012, Colorado and Washington State withdrew from the battle against marijuana. Voters in each state approved ballot initiatives legalizing possession of marijuana and authorizing state regulation of marijuana production and commercial sale. In 2014, Alaska, Oregon, and the District of Columbia followed suit† (Adler, 505). This is where it begins, a few liberal states become trailblazers for the marijuana revolution, giving others the hopeful possibility that their state’s participation is likely in the near future. Marijuana use is still illegal according to federal laws. It is only under state law that some haveShow MoreRelatedThe Legalization Of Recreational Marijuana1645 Words   |  7 PagesThe legalization of recreational marijuana has recently been a widely debated topic, especially since medical marijuana was legalized in several states. Critics say that cannabis is a Class I drug that has both negative health effects and behavior effects. However, there is minimal evidence to support these claims, and none of the benefits of marijuana are taken into consideration when the arguments are made. The possession and use of recreational marijuana should be legalized in the United StatesRead MoreThe Legalization Of Recreational Marijuana1535 Words   |  7 Pagesthis may be†¦ it is the truth. This truth allows otherwise big ticket discussions to go un-talked about. One such issue is that of the legalization of recreational marijuana. Many just assume that the reason that this â€Å"harm less substance† isn’t legalized is due to stuffy old politicians stuck in their ways or some other trivial reason. The truth of the matter is, marijuana is dangerous. It’s just as much a harmful drug as cocaine and meth are, and thus should be treated as a harmful drug. It blows meRead MoreThe Legalization Of Recreational Marijuana1975 Words   |  8 PagesName: Course: Date: Federal Legalization of Recreational Marijuana Marijuana is a very controversial drug that spurs a lot of debate as to whether it should be legalized for recreational purposes or not. Most of the states already have legalized marijuana for medical purposes although the federal government prohibits any use of it. Proponents and opponents to this debate each try to argue their side and to show why recreational marijuana should be or should not be legalized but no consensus hasRead MoreThe Legalization Of Recreational Marijuana1577 Words   |  7 PagesThe 2016 elections and the subsequent legalization of recreational marijuana in California, Nevada, and Massachusetts show how constantly evolving attitudes regarding marijuana and regulations pertaining to marijuana practices are. Corresponding with constantly changing attitudes regarding marijuana, users are finding more novel ways to make the most of their plant products. Butane-extracts or butane hash-oil (BHO) products are potent marijuana concentrates (Bell, Slim, Flaten, Wikto r, Monte, 2015)Read MoreLegalization Of Marijuana For Recreational Use1071 Words   |  5 PagesAjin Jose Professor Sheila Gordon Drugs, Society Human Behavior 12 April 2017 Legalization of marijuana for recreational use in Canada The Federal Government promises to legalize marijuana in Canada. But it should be revised in accounting to those pot legalization strategies and results gained in other parts of the World. I do not agree with the fact that Marijuana should be legalised for recreational purposes in Canada because there are short term and long term effects which affect both the individualRead MoreThe Legalization Of Marijuana For Recreational Purposes1344 Words   |  6 PagesThis is a paper pertaining to the legalization of marijuana for recreational purposes. This is a concept that states has been considering and debating in their jurisdictions. First, this paper will explain why supporters of the legislation I researched believe marijuana should be legalized. Secondly, this paper will analyze the public policy issues associated with the legalization of marijuana for the legislation I selected, paying particular attention to newness and implementation of the legislationRead MoreThe Legalization Of Marijuana For Recreational Use Essay1463 Words   |  6 PagesCurrently in America, eight states have approved the legalization of Marijuana for recreational use, and eighteen other states have approved forms of medical uses of the drug. This means that there are a total of forty-two states that have not approved the drug for recreational use, and have criminal laws against it. One of these states happens to be the state of Ohio. Recently, the counties within Ohio have voted for the legalization of both recreational and medical use, ending with a result of only passingRead MoreLegalization Of Medical And Recreational Use Of Marijuana1385 Words   |  6 PagesThe legalization of marijuana has been a very controversial topic that has everyone asking each other, is it really worth it? For many, the thought of legalizing a drug, which the government has classified as a Schedule 1 drug is, mind boggling to them. I am going to prove that the pros about the legalization of medical and recreational use of marijuana are greatly outweighing the cons. I will show with statistical evidence that legalization is beneficial in many ways such as generating higher stateRead MoreThe Legalization Of Recreational And Medical Use Of Marijuana1237 Words   |  5 PagesThe legalization of recreational and medical use of marijuana is still a controversial social issue faced by the United States. Although marijuana was seen as a dangerous drug back in the 1900’s, research has revealed the truth about marijuana, making the drug less frightening towards Americans. Now in the year 2015, marijuana is generally more accepted by Americans and many more see marijuana in a positive manner. Although marijuana does have some negative side effects, the side effects are notRead MoreLegalization Of Marijuana And The United States For Recreational Use1287 Words   |  6 Pagesregular users of marijuana, this paper will argue that marijuana should remain illegal in the United States fo r recreational use. Arguments for the legalization of marijuana and arguments against the legalization of the drug will be discussed throughout the paper. It will address the biological effects of the drug on the human body, the current laws in place and the effects it has on children, adolescents and adults. The National Institute on Drug Abuse, (NIH), refers to marijuana as the â€Å"dried leaves

The Terrorist’s Extradition Loophole Essay - 1064 Words

The Terrorist’s Extradition Loophole Most extradition treaties between states call for an exemption for crimes that are political in nature. The political offense exemption was originally created to allow states to protect those that another state may wish to prosecute for crimes that are politically committed against that government. R. Stuart Phillips, a Judge Advocate in the United States Army, distinguishes between â€Å"pure† political offenses and â€Å"relative† political offenses. â€Å"Pure† political offenses are directed specifically against the state and do not directly affect civilians. They also do not contain acts that would normally be considered a common crime. This can include efforts to overthrow the government, treason, and†¦show more content†¦Should the person be extradited to stand trial as a terrorist? The answer to the final question is ultimately left up to the individual state. That state may have ulterior motives for using the political offense exemption as an ex cuse for not extraditing the individual in question. This exemption gives some governments the excuse they need to protect terrorists, whether or not that is their actual intention. It also gives the terrorist legal recourse to avoid extradition for the crimes that were committed. If nothing else, this exemption allows the terrorist to stall the process of justice while awaiting a ruling on whether the terrorist act should be considered a â€Å"political offense.† The United Nations has condemned all forms of terrorism, but what exactly that means is still up for debate. Most states would probably be willing to extradite a â€Å"terrorist,† but not quite as willing to extradite a â€Å"freedom fighter.† The first step that is necessary to close this loophole is defining the concept of terrorism itself. The current usage of the term â€Å"terrorism† is politically contrived. The former U.S. Judge to the International Court of Justice, Richard Baxter, has shown the problem with the definition of terrorism: â€Å"[W]e have cause to regret that a legal concept of terrorism was ever inflicted upon us. The term is imprecise; it is ambiguous; and above all, it serves no operative legal purpose†

Pressure Management on a Supercritical Airfoil Free Essays

Pressure Management on a supercritical aerofoil in transonic flow Abstract-At transonic speeds an aerofoil will have flow accelerate onwards from the leading edge to sonic speeds and produce a shockwave over the surface of its body. One factor that determines the shockwave location is the flow speed. However, the shape of an aerofoil also has an influence. We will write a custom essay sample on Pressure Management on a Supercritical Airfoil or any similar topic only for you Order Now The experiment conducted compared Mach flow over a supercritical aerofoil (flattened upper surface) and a naca0012 aerofoil (symmetrical). Despite discrepancies, the experiment confirmed the aerodynamic performance of a supercritical aerofoil being superior to a conventional aerofoil. A comparison of the graphical distributions demonstrates the more even pressure distribution on a supercritical aerofoil and a longer delay in shockwave formation. All of which, reflects the theory. Table of Contents Introduction3 Apparatus3 Induction Wind Tunnel with Transonic Test Section3 Mercury Manometer4 Procedure4 Theory and Equations5 Results6 Discussion10 Theory of Transonic Flight10 Relating the Theory to the Experiment11 Effectiveness of Supercritical aerofoils†¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦Ã¢â‚¬ ¦ 11 Limitations and Improvements12 Appendix13 References14 Introduction For any object travelling through a fluid such as air, a pressure distribution over all of its surface exists which helps generate the necessary lift. Lift is an aerodynamic force which is perpendicular to the direction of the aerofoil. Transonic speeds result in the formation of shockwaves over the top surface of the aerofoil. This is due to accelerated flow over the surface region. We say this region is approximately between 0. 8-0. . Since the flow must accelerate and then will lose velocity following the shockwave the aerofoil will have a subsonic and sonic region. For the majority of commercial airlines this is not a desired region to cruise at given the instantaneous pressure distri bution which passengers would otherwise experience. Particularly, the formation of shock induced boundary layer separation. Supercritical aerofoils are more efficient designed for higher Mach speeds and drag reduction. They are distinct from conventional aerofoils by their flattened upper surface and asymmetrical design. The main advantage of this type of aerofoil is the development of shockwaves further away then traditional aerofoils and thus greatly reducing the shock induced boundary layer separation. In order to truly understand the effectiveness of a supercritical aerofoil an experiment gathering supercritical aerofoil performance and raw data of a naca0012 aerofoil will be extensively analysed and compared. Following the calculation and procedureit will be assessed whether a supercritical aerofoil is more effective. Apparatus A wind tunnel with a transonic test section was used in this experiment to study transonic flow around an aerofoil. The test section consists of liners which, after the initial contraction, are nominally parallel apart from a slight divergence to compensate for growth of the boundary layers on the wall. In order to reduce interference and blockage at transonic speeds, the top and bottom liners are ventilated by longitudinal slots backed by plenum chambers. The working section has a height and width of 178mm and 89mm respectively. The stagnation pressure, p0? in the tunnel is close to atmospheric pressure, and therefore it can be taken to be equal to the settling-chamber pressure as the errors are only small. To minimise the disturbance due to the model itself, the reference stagnation pressure, p? , is taken from a pressure tapping in the floor of the working-section, well upstream of the model. The nominal ‘free-stream’ Mach number, M? , in the tunnel can be calculated from the ratio p? /p0?. The Mach number in the tunnel can be controlled by varying the pressure of the injected air, pj. The maximum Mach number that the tunnel can achieve is about 0. 8 Mercury Manometer A multi-tube manometer with mercury was used to measure the pressure at stagnation, the aerofoil tappings and atmosphere. The manometer is equipped with a locking mechanism which allows the mercury levels to be ‘frozen’ so that readings can be taken once the flow has been stopped. Also, the angle of the manometer can be adjusted. For this experiment, it was set to 45 degrees (Motellebi, F. ,2012). Procedure Before conducting the experiment, the barometric pressure, Pat, was recorded, in inches of mercury and the atmospheric temperature, in degrees Celsius, was also recorded. For a range of  values of Pj from 10 – 110 lb/in2, in intervals of 20lb/in2, Pj was then recorded along with the manometer readings corresponding to stagnation pressure (I0? ), the reference static pressure (I? ), airfoil pressure tappings (In, n=1 to 8 and 3a) and the atmospheric pressure (Iat), all in inches of mercury (Motellebi, F. ,2012). Results- Raw data in appendix x/c Figure 1b Cp against x/c at M= 0. 85 Figure 1a -Cp against x/c at M=0. 85 The experimental data was converted to absolute pressure values using Equation x ( units are inches of mercury). For a given value of the pressure injector (Pinjector) we can find the value of the Mach number using Equation y. Also Equation Z calculates Cp( or pressure coefficents) which reflect the measurements of the surface of the aerofoil. These results are displayed in figure x. This was done for both the supercritical aerofoil and the NACCA 0012 aerofoil. What follows is a comparison and analysis of the data. ( Figure 2b Cp against x/c at Mach speed 0. 8 Figure 2a -Cp against x/c at Mach speed 0. 81 x/c x/c Figure 3b- -Cp against x/c at Mach speed 0. 72 Figure 3a –Cp against x/c at Mach speed 0. 3 Figure 4b –Cp against x/c at Mach speed 0. 61 Figure 4a –Cp against x/c at Mach speed 0. 61 Figure 5a- -Cp against x/c at Mach speed 0. 45 Figure 5b- -Cp against x/c at Mach speed 0. 44 Note that for both supercritical and naca0012 aerofoils the supercritical cases ( where M is equal to 0. 77, 0. 83 and 0. 840) the approximate value of x/c % where the shock occurs over the a erofoil is shown in red line. For the point below where Cp and the Cpcritical and hence the drop in Cp is greatest gives the location of where the shockwave occurs on the surface of the aerofoil. Cp and Cp* vs M? naca0012 aerofoil) Cp and Cp* vs M? (supercritical aerofoil) It is worth noting that for both the supercritical and Naca0012 aerofoil the results are somewhat similar. That is the critical Mach numbers for both are around 0. 72. Therefore the Minimum Mach number for a local shockwaves on both the supercritical and conventional aerofoil can be assumed to be the same. It is worth noting that Mach number 0. 41 for the supercritical aerofoil does not produce a shockwave, whereas the Naca0012 aerofoil does. Mach number| Supercritical Aerofoil Approx position of shock| naca0012 Approx position of shock| 0. 5| -| -| 0. 61| -| -| 0. 72-0. 73| -| 0. 25x/c%| 0. 85-0. 86| 0. 70x/c%| 0. 40x/c%| Basic transonic theory An aerofoil or any object for that matter travelling through a medium (air) at low Mach numbers ( typically between 0. 30-0. 40) has flow is subsonic and can be considered incompressible. This means that any change in pressure or density is significant. The speed of sound (a) is dependent on the altitude of the aerofoil/object and the Mach number M is the ratio of velocity: M=va , a=? RT ?is a specific heat ratio, T is thel absolute temperature and R is the gas constant. The combination of these two equations above leads to: M=v? RT Sound is essentially a series of consecutive weak pressure waves emitted from a given source. These waves travel at the local speed of sound. If we assume the aerofoil is travelling towards the source, the source can notice the disturbances beforehand giving enough time for flow to adjust around the object. When the source begins to approach near the speed of sound, pressure waves move closer together in front of the object, therefore inadequate information from the source/disturbance is propagated upstream and the flow will not be able to react in time. The pressure waves merge together to produce a shockwave in front of the object. The flow encountering the shockwave will experience changes in temperature, static pressure and gas density as well as a lower Mach number. The transonic region is special because although flight speed is below sonic speed as the information is propagated upstream on the surface of the aerofoil the flow accelerated to the speed of sound. Thus forming a shockwave over the aerofoil. The position of this shockwave depends on the initial entry speed to the aerofoil. Therefore what we have in the transonic region is an aerofoil which has sonic speeds early upstream and subsonic speed towards the end of the aerofoil or downstream. This means it is complicated to accurately analyse transonic flow over an aerofoil as a different set of equations must be used on the leading edge, upper surface and trailing edge. The critical upstream Mach number is the minimum value of a given Mach number for which a shockwave will be produced on the surface of an aerofoil. In other words, supersonic flow. Below this threshold a shockwave will not appear. Drag or the aerodynamic force in the transonic region again depends on the speed of the object travelling. At subsonic speeds the main component of drag are Skin friction, pressure drag and lift induced drag. At sonic speeds (approaching or exceeding) there is the addition of wave drag. The drag increases dramatically, and as a result a higher thrust is needed to sustain acceleration. Also, at this point the shockwave will interact with the boundary layer, thus causing it to separate upstream of the shock. Figure 6Demonstration of transonic flight-(Scott, J. , 2000) The aerofoils The two aerofoils Naca0012 and Supercritical aerofoil are different in design and purpose. The Naca0012 is a basic symmetrical aerofoil used primarily for rudder and elevator movements. Aerodynamic performance is not taken into consideration and is thus reflected by the simple aerodynamic design. It is worth noting that there are better aerofoils. The Supercritical aerofoil is a performance aerofoil designed for higher Mach speeds and drag reduction. They are distinct from conventional aerofoils by their flattened upper surface and asymmetrical design. The main advantage of this type of aerofoil is the development of shockwaves further away then traditional aerofoils and thus greatly reducing the shock induced boundary layer separation. Relating the Theory to the Experiment The critical Mach number for both the supercritical aerofoil and NACA0012 aerofoil was found to be in the region of 0,72. There is a difference to the nearest 10th but for all intents and purposes we can assume they are the same. This indicates that the minimum Mach number for a shockwave to be produced on the surface of the aerofoils is equal and not influenced via the shape. The pressure distributions of the supercritical aerofoil ( especially at Higher Mach) in comparison to the Naca0012 are more evenly distributed. The experiment confirms the theory that the supercritical aerofoil in comparison ro a conventional aerofoil generates more lift due to an even distribution of pressure over the upper surface. (http://en. wikipedia. org/wiki/Supercritical_airfoil) Effectiveness of Supercritical aerofoils. At a Mach number of 0. 45 both aerofoils do not display a shockwave. This is evident from the fact the Cp and Cp* graphs do not intersect at all. We already know this because the critical Mach number is 0. 72 for both. This indicates that either a shockwave was not produced (unlikely), or that the shockwave was produced beyond the trailing edge This means we cannot assess the effectiveness of the supercritical aerofoil at Mach speeds 0,45 and 0. 61. The supercritical Mach numbers show varying results. When the experiment took place at Mach ) 0. 72-0. 3 ( the critical Mach number) the supercritical aerofoil did not produce a shockwave ( Cp and Cp* do not intersect) whereas the naca0012 aerofoil did. The lack of a shockwave formation indicates either the critical Mach number for the supercritical aerofoil is higher then the conventional aerofoil experimental accuracy is lacking. At the supercritical mach numbers ( 0. 81-0. 86) in both the naca0012 aerofoil and the supercritical aerofoi l Cp and Cp* intersect. The large drop in pressure coefficient is evidence of the formation of a shockwave. However, the pressure drop in the supercritical aerofoil is occurring at a pressure tapping further downstream. This confirms the theory that a shockwave is produced further downstream in a supercritical aerofoil This seems to confirm the theory that a supercritical aerofoils design does allow for development of shockwaves further away then traditional aerofoils and thus greater reduction in the shock induced boundary layer separation. In regards to the amount of drag (aerodynamic force) acting on the aerofoils it is worth noting that the pressure distribution at 0. 5 Mach for the supercritical aerofoil is more evenly distributed and ‘flatter’ then the naca0012 aerofoil. There is no indication of a large instantaneous increase in drag taking over. This would therefore confirm the theory that a supercritical aerofoil is effective in greatly reducing the shock induced boundary layer separation. Notes for limitations The experiment is a success since results obtained confir m the capabilities of supercritical aerofoils and their advantages over conventional aerofoils. However, there are a few discrepancies which regarding experimental error and the different aerofoils. First of all the mach numbers tested at 0. 72 and 0. 73 created an inaccurate experiment. Normally, this would not be a problem. However, since the critical mach numbers for both aerofoil’s were in the vicinity of 0. 72 it was expected this was the minimum threshold for a shockwave to be produced over the aerofoil. A shockwave was not produced for the supercritical aerofoil despite the critical mach number value. Therefore, we can conclude that at this speed there are too many inaccuracies to understand what is really going on. We also did not really see a difference in performance at subsonic flow. Granted, the supercritical aerofoil was primarily designed for supercritical mach speed. No useful information was obtained from here. The fact the pressure tappings have different coordinates means that each aerofoil is showing the pressure distribution at a different set of coordinates. This of course, is not as accurate if the aerofoils had the same pressure tappings. For instance, the naca0012 has a pressure tapping at 6. 5% of the aerofoil section and the last ends 75% the rest is unaccounted for. Since the supercritical aerofoil has different pressure tappings it means both aerofoils have different areas which are unaccounted for. This means it is not certain whether or not the graphs are a reliable source of information, yet alone to compare. A digital meter should also be connected that displays the pressure in the two tappings so the aerofoil can be appropriately adjusted to bring it to zero incidence. This digital meter can also be used to display the value of the mercury levels for other pressure tappings, reducing any human errors. In order to increase the accuracy of the pressure distribution over the aerofoil surface, more pressure tappings can be made on the aerofoil. These will improve the pressure coefficient graphs by allowing more points to be plotted, in turn, yielding better information for the position of the shockwave in the supercritical cases and also the critical Mach number for a shock to occur. References 1) http://www. southampton. ac. uk/~jps7/Aircraft%20Design%20Resources/aerodynamics/supercritical%20aerofoils. pdf 2) http://www. nasa. gov/centers/dryden/pdf/89232main_TF-2004-13-DFRC. pdf 3) How to cite Pressure Management on a Supercritical Airfoil, Essay examples

Define Public Relations free essay sample

When I think of public relations I also think of promotions, advertisement, and media. Public Relations also Is the front end person when It comes to anything about the product. Press, Inquiries, and Information about the product itself are given by the public relations department. According to Edward Barneys, Public Relations is a management function which tabulates public attitudes, defines the policies, procedures and interest of an organization followed by executing a program of action to earn public understanding and acceptance (Cole, 2007).Edward Barneys was known to be the first person to define public relations but room a psychological perspective. Sigmund Freud Is also his uncle so we can see where his Influence Is from. According to the Public Relations Society of America, Public relations helps our complex, pluralistic society to reach decisions and function more effectively by contributing to mutual understanding among groups and institutions. It serves to bring private and public policies into harmony (APRS, 2007). We will write a custom essay sample on Define Public Relations or any similar topic specifically for you Do Not WasteYour Time HIRE WRITER Only 13.90 / page Among the many institutions of our society, public relations serve as a connection for institutions to develop relationships with several deferent audiences to sell their product or service. Another definition of public relations Is the efforts to establish and malting a companys Image with the public (Investigators. Com, 2007). Although there are many different types of definitions the main word I picked up is public. Through research I found, the word public not only means the audience but also key steak holders within an organization.There are many organizations, business, and institutions that all need public relations in order to remain successful in business. In closing, public relations must work together with good marketing , research, and communication In order to satisfy the needs and wants of the organization including the customers, employees, suppliers, and society. In the long run, public relations will ensure the satisfaction and success of meeting the needs of the organization itself.