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.
Clay Dillow’s “To Catch a Bombmaker” was published by Popular Science in October 2015. This article educated the reader about the FBI’s Terrorist Explosive Device Analytical Center— a key aspect in the fight against terrorism. Dillow focused on ethos and logos to strengthen the validation of his claim concerning the importance of the TEDAC and was successful in persuading the reader to believe in its significance as well. He used expert quotes from FBI agents to give the article credibility; In addition, he presented statistical data in a clear and concise manner and gave many factual cases in which the TEDAC facilitated the government in their pursuit of terrorist and bomb makers. As proven by Dillow in “How to Catch a Bombmaker,” the Terrorist
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
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.
By studying these shadows scientists pinpointed the exact detonation point of the bomb. The second atomic bomb was dropped just three days later on Nagasaki, Japan. 1/3 of the city was destroyed and 66,000 people were reported killed or injured. A memorial now marks the spot where the bomb exploded.
Citations: "Hiroshima." Encyclopaedia Britannica. Encyclopaedia Britannica Online Academic Edition. Encyclopædia Britannica Inc., 2014. Web. 14 Mar. 2014. .
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.
Note: The tail arm is considered 65% of the fuselage length. Usually, the tail arm is approximated by considering 65%-75% of the fuselage [1].
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.
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 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.
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.
Basic weight volume relationships are used to develop the equation for the ZAV line. Recall that:
12. Twisting the wings to raise or lower the leading edges can also affect the boomerang's performance.
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.