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Figure 2.20. Three variations on the bathtub theme, spanning the range from greatly simplified to a more physically realistic model based on Torricelli's Law.

Thrust (sl): 267.000 kN (60,023 lbf). Thrust (sl): 27,227 kgf. Engine: 885 kg (1,951 lb). Chamber Pressure: 15.90 bar. Propellant Formulation: Lox/Alcohol-75%. Thrust to Weight Ratio: 35.3672316384181. Oxidizer to Fuel Ratio: 1.28. Country: Russia. Launch Vehicles: R-1. Propellants: Lox/Alcohol. Stages: R-1 stage. Agency: Glushko bureau. Bibliography: 225, 287, 317, 321, 323, 342, 394. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z © 1997-2019 Mark Wade - Contact © / Conditions for Use

German salaries and conditions were good - the chief of the German team receiving the second highest salary after the Soviet designer-in-chief. The RD-100 was built in 1946 at a former Ilyushin aviation plant that had been moved to Tashkent in World War 2 (now the Energomash factory). There was no equipment so everything had to be started from scratch. By mid-1947 the first RD-100 was ready. In May 1948 the first RD-100 test took place at Khimki itself, with the spectators watching from 1 km away. There are still tests at the same location but thrust levels are now 800 metric tons force. The R-1 rocket with the RD-100 engine entered service in 1950. Thrust (sl): 267.000 kN (60,023 lbf). Thrust (sl): 27,227 kgf. Engine: 885 kg (1,951 lb). Chamber Pressure: 15.90 bar. Propellant Formulation: Lox/Alcohol-75%. Thrust to Weight Ratio: 35.3672316384181. Oxidizer to Fuel Ratio: 1.28. Country: Russia. Launch Vehicles: R-1. Propellants: Lox/Alcohol. Stages: R-1 stage. Agency: Glushko bureau. Bibliography: 225, 287, 317, 321, 323, 342, 394. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z © 1997-2019 Mark Wade - Contact © / Conditions for Use

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Figure 2.22. Comparison of the three versions of the bathtub model ranging from a realistic to a highly simplified model. Note that the intermediate model shows virtually the same behavior as the more realistic model.

Country: Russia. Launch Vehicles: R-1. Propellants: Lox/Alcohol. Stages: R-1 stage. Agency: Glushko bureau. Bibliography: 225, 287, 317, 321, 323, 342, 394. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z © 1997-2019 Mark Wade - Contact © / Conditions for Use

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These three models thus cover a range of possibilities but even the most sophisticated one ignores things like friction and water viscosity and density that certainly operate in the real world. In most cases, these additional factors are minor in comparison with the ones represented in the model, so they do not present a serious shortcoming of the model.

From the results, it is clear that the simplest model does a poor job of representing the real behavior of this system; it drops off at a constant rate and does not achieve a steady state except in the special case where the inflow is set equal to the outflow. This simple system does not have any negative feedback associated with it either. So, this is a good example of a model that is too simple. Next, let's assume that our most complex model, based on Torricelli's Law is a nearly perfect model in that it can accurately reproduce the results of a real system (it would be a good exercise to test this hypothesis). The question then is whether our second model, the intermediate one, is simple enough and yet not too simple. from the results, it is clear that this model is nearly indistinguishable from the most realistic model. It is similar to the best model in the reservoir changes rapidly at first and then very slowly approaches its steady state value - it follows an exponential curve in other words. It also contains negative feedback, so it responds to changes the same way that the best model does. Because of these similarities in behavior, this second model represents a reasonable simplification. It is qualitatively acceptable, but not necessarily quantitatively acceptable (though in this case, the numbers are certainly acceptable). It is simple enough and yet not too simple. RETURN TO MAIN PAGE

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Einstein's quote that "a model should be as simple as possible and yet no simpler" makes a good sound bite, but it does not give us too much guidance in figuring out what is simple enough and what is too simple. This is clearly an important concept and we will examine three versions of the familiar water tub model to illustrate varying levels of simplicity.

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These three models are shown in Figure 2.20. The first is the simplest, consisting of a reservoir with an inflow and outflow that are both defined as constants - they are unaffected by the amount of water in the tub. The second model is the one we experimented with in the earlier part of this chapter; the inflow is a constant and the outflow is a function of the amount of water in the tub. The third model is the most complex and the most realistic.

Figure 2.21. Diagram illustrating Torricelli's Law, used to calculate the velocity and flow rate, or discharge, from a drain at the bottom of a tub of water.

Date: 1946-50. Number: 184 . Thrust: 304.00 kN (68,341 lbf). Unfuelled mass: 885 kg (1,951 lb). Specific impulse: 237 s. Specific impulse sea level: 203 s. Burn time: 65 s. Height: 3.70 m (12.10 ft). Diameter: 1.65 m (5.41 ft). German salaries and conditions were good - the chief of the German team receiving the second highest salary after the Soviet designer-in-chief. The RD-100 was built in 1946 at a former Ilyushin aviation plant that had been moved to Tashkent in World War 2 (now the Energomash factory). There was no equipment so everything had to be started from scratch. By mid-1947 the first RD-100 was ready. In May 1948 the first RD-100 test took place at Khimki itself, with the spectators watching from 1 km away. There are still tests at the same location but thrust levels are now 800 metric tons force. The R-1 rocket with the RD-100 engine entered service in 1950. Thrust (sl): 267.000 kN (60,023 lbf). Thrust (sl): 27,227 kgf. Engine: 885 kg (1,951 lb). Chamber Pressure: 15.90 bar. Propellant Formulation: Lox/Alcohol-75%. Thrust to Weight Ratio: 35.3672316384181. Oxidizer to Fuel Ratio: 1.28. Country: Russia. Launch Vehicles: R-1. Propellants: Lox/Alcohol. Stages: R-1 stage. Agency: Glushko bureau. Bibliography: 225, 287, 317, 321, 323, 342, 394. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z © 1997-2019 Mark Wade - Contact © / Conditions for Use

where v is velocity, g is gravity, and h is height. This velocity has units of m/sec and when multiplied by the area of the drain opening, gives an outflow in m3/sec. The details of this calculation are shown in Figure 2.21, in which our bathtub is replaced with a simple cylinder.

Figure 2.22 shows the results of running these three models. I set the two more complex models up so that they have the same initial amounts and the same steady state amounts to provide a better comparison. As you might have guessed, this was not possible for the simplest model.

It turns out that an Italian named Torricelli has examined the dynamics of this water tub system (this is the same person who invented the barometer) and after a good deal of experimentation, he came up with a general relationship that is called Torricelli's Law. This law says that the velocity of water flowing out of a drain is equal to the square root of two times gravity times the height of the water:

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