H. Bomb Nose The normal coefficient for the bomb nose has been taken as[2] Where CNN is the normal coefficient for the nose, σ, the cone semi-vertex angle is given by Where lN is the length of the bomb nose. The derivative, (CNα)N is given by[2] The center of pressure of the nose is given as[2] Where P is the pressure coefficient given by,[2] To facilitate the calculation of the pressure coefficient P, the ogive semi-vertex angle is given by,[2] I. Bomb Body The calculations for bomb body are,[3] The value of the center of pressure for the body alone is given by, Where, CNB is the normal coefficient for the body, (CNα)B is the derivative of the normal coefficient, lB is the body lenght and XACB is the body center of …show more content…
Boattail The calculations for the boattail are,[4] Where (CNα)BT is the normal derivative for the boattail, Abt and dbt are the area of cross section and the diameter of the boattail section. Aref and dref are the area of cross section and diameter of the reference area. For small angles of attack, The value of center of pressure for the Boattail is given as,[5] K. Center of Pressure for the Bomb Body The center of pressure of the entire bomb body is calculated from firure 2 as Thus, the value of center of pressure for the bomb body has been calculated for various boattail lengths and angles of attack. L. Tail Area Sizing As the nose provides the maximum lift for the body alone, the tails must be sized to provide static stability. The tail contribution to pitching moment stability, provided by the tail normal force effectiveness (CNα)T(ST/SRef) times its moment arm to the center of gravity must balance the contributions to pitching moment from the nose and body. The equation to be followed for the purpose of tail area sizing at a particular angle of attack is given as[3] Where ST is the optimum tail area required to balance the …show more content…
the top five tails with the least difference with the optimum tail area for neutral stability. The values of cone half angle (θ) and fin sweep angle (δ) were then adjusted to obtain the best result. The differences from the actual tail dimensions are vast. This means that the center of pressure of the bomb will be behind the center of gravity, which is desirable. To maximise the static margin, the best five tails were chosen based on maximum sweep angle δ based on subsonic leading edge to avoid drag divergence. Of these possible designs, the ones of 6, 7 and 8 degree boattail angles were chosen for further analysis. This was done to obviate the problems of too long a bomb (5°) and the possible problems of flow separation due to too short a boattail (9 and
I am reading Bomb by Steve Sheinkin. At the beginning of the book, Oppenheimer, who is the main chemical scientist in the novel, sees the effects of the Great Depression on his pupils when they cannot buy chemistry textbooks. During Oppenheimer’s time as a professor, the Nazis discovered the splitting of the uranium atom. When Albert Einstein found out that about the discovery the Nazis did, he informs President Roosevelt about how the Nazis plan to develop atomic weapons. Harry Gold who is a Communist spy, starts to work with the KGB. And starts to steal ideas and projects from the American Uranium Committee.
...Modelling: Rigging Patterns - The Carracks and Caravels." Jan's Sites: Navigation. N.p., 8 Mar. 2012. Web. 24 Nov. 2013.
The Split Hopkinson Pressure Bar is named after Bertram Hopkinson [2], who in 1914 acquired a technique to evaluate the pressures created by dynamic events such as the blast caused by a rifle bullet or the explosion of explosives. In this placement, a long cylindrical bar of steel is suspended horizontally by four equal threads so that it can dangle in the vertical plane parallel to it. A short piece of rod of the same diameter is obtained against the long bar by magnetic attraction created by a solenoid. A rifle bullet is forced out or gun cotton is detonated near the close of the long bar. This creates a pressure wave which goes from the long bar in the short piece of rod. On passing the loose end of the short rod the pressure wave is reflected back as a tensile wave; when the magnitude of the tensile wave exceeds that of the pressure wave at the butted end of the short rod, the inability of the short rod to hold up the tension along the joint produces separation and it flies away. The little rod is caught in a box suspended in
8 Galum, John, Joshua Shakon and Tan Mau Wu. “National Missile Defense – A CS91 Final Project.” < http://www.cs.swarthmore.edu/~eroberts/cs91/projects/national-missile-defense/index.html>
Hutchinson and Garcia's model calculates the ground reaction force along with other necessary factors such as the length of limbs and stance to determine the amount of muscle mass that would be needed to maintain equilibrium.
The weapon was designed to lock onto the loudest noise after a run of 400m from its launch. This often proved to be the U-boat itself and standard issue-orders were to dive immediately to depth of 60m after launch from a bow tube while a stern shot was to be followed by a complete silence in the boat. Two U-boats were almost certainly lost when hit by one of their own T5 torpedoes, U-972 in Dec 1943 and U-377 in Jan 1944.
Citations: "Hiroshima." Encyclopaedia Britannica. Encyclopaedia Britannica Online Academic Edition. Encyclopædia Britannica Inc., 2014. Web. 14 Mar. 2014. .
[2] “Wing and Tail Design”- Page Aircraft Design: A System Engineering Approach by Mohammad H Sadraey- Wiley Aerospace Series
For takeoff and landing, hinged wing panels are extended at right angles to the fuselage in order to utilize the advantages of long-span and high-aspect ratio. For high speed and maneuvering in flight, the panels are swung rearward to make (with the tail surfaces) a delta configuration. The normal location for stabilizers, fins, rudders, and elevators is well behind the wing, mounted on the tapered tail section of the fuselage.
When Jesus called His disciples, His invitation was simple. He invited them to follow Him. The same is true today. In Matthew 28, Jesus gave His last charge to His disciples, and the charge was simple. He called his followers to go and make disciples. Much effort has been placed by Christians to fulfill this charge, commonly referred to as the Great Commission. Jesus chose to fulfill the implementation of the New Covenant through 12 men who He called, appointed, and commissioned, and he only had a few short years to prepare them for the task (Willson, 1990). His methods were unconventional and were revolutionary for that time. His disciples were to be trained extensively by Jesus, living with Him for three years prior to His ascension. He taught about servant leadership and its meaning for both the leader and follower Matt. 20:25-28). From the beginning, Jesus put in place a careful plan, and an examination of His actions in the Gospels showed that Jesus left behind the pattern to be replicated. His methods, which included the incorporation of three different levels of discipleship, included His interaction with Peter, His closest three (Peter, James, and John), and finally the group of 12. This paper identified and analyzed the three levels of discipleship Jesus modeled, these discipleship methods were then measured against modern leadership theories, and Jesus’s level of involvement and interaction with his disciples were critiqued in light of these modern theories in an effort to determine the effectiveness of this approach.
Basic weight volume relationships are used to develop the equation for the ZAV line. Recall that:
The law of partial pressures equation was used to find the pressure of CO2. is the vapor pressure of water that we found to be 0.0245 atm.3 is the total pressure of the combined gases which was measured to be 2.54 atm. When manipulating the equation, the pressure of CO2 was 2.5155 atm. Below shows this calculation.
A ramjet intake design analysis. Supersonic and hypersonic flights often make use of a ramjet engine during the cruise phase of the flight. The design of the intake affects important variables of the ramjet engine, namely Mach number distribution, formation of shocks and pressure distribution. Analysis of a normal intake design provides lower than optimal pressure to the combustion chamber. A geometric dimension modification on the intake, i.e. lengthening of the nosecone significantly improves the resultant pressure in the combustion chamber. Flow speed or the Mach number in the combustion chamber is also reduced. Over lengthening the nosecone could require infeasible initial flow speed; very high Mach number.
We are putting CA and IS values in Space Matrix on the X axis and CA values can range from 0 to -6 and IS Values can range from 0 to 6. FS and ES Dimensions are drawn on the Y Axis and ES values can be between 0 and -6 and FS values can take 0 to 6.
Where, W is the weight loss in g, ‘ρ’is the density of the mild steel specimen in gcm˗3, ‘A’ is the area of specimen in cm2 and t is the time of exposure in h.