Interactive Aerospace Engineering and DesignMcGraw-Hill, 2002 - 356 pages This text contains an integrated bound-in CD-ROM, and has a strong emphasis on design. Its active visual approach and inclusion of space-orientated engineering make it an interesting examination of the aerospace engineering field. |
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Page 127
... temperature are related , and the energy equation determines the temperature change . The energy output of the burner stage is desired . Since fuel is added in the burner domain , we account for the added mass of the fuel by using a ...
... temperature are related , and the energy equation determines the temperature change . The energy output of the burner stage is desired . Since fuel is added in the burner domain , we account for the added mass of the fuel by using a ...
Page 168
... temperature of the body is determined as follows : Pemitted = Pabsorbed [ 8.1 ] By definition , the power absorbed from the Sun by a spherical body at a dis- tance d from the Sun is given by Pabsorbed ( a ) = ( P = ) ( πr2 ) 4πd2 ...
... temperature of the body is determined as follows : Pemitted = Pabsorbed [ 8.1 ] By definition , the power absorbed from the Sun by a spherical body at a dis- tance d from the Sun is given by Pabsorbed ( a ) = ( P = ) ( πr2 ) 4πd2 ...
Page 228
... temperature simplifies to T = Ga Δεσ 0.25 = 0.035 . Using Using the values in Table 10.3 for aluminum , we have a = 0.38 and ε these values in the temperature equation , we get a steady - state temperature of 505 K ( 232 ° C ) , which ...
... temperature simplifies to T = Ga Δεσ 0.25 = 0.035 . Using Using the values in Table 10.3 for aluminum , we have a = 0.38 and ε these values in the temperature equation , we get a steady - state temperature of 505 K ( 232 ° C ) , which ...
Table des matières
A Brief History of Flight | 1 |
Chapter | 4 |
Introduction to Engineering | 20 |
Droits d'auteur | |
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Expressions et termes fréquents
aerodynamic aircraft airfoil airplane altitude angle of attack antenna Apollo astronauts atmosphere axis balloon body Boeing burner calculate camber CD-ROM chapter coefficient coefficient of lift components compressor crew member debris Decavitator drag drawing efficiency elliptical energy Equation equilibrium example Figure flight force freestream fuel gravity human human spaceflight inlet International Space Station jet engine joint launch lift load factor low Earth orbit LTA vehicle lunar maneuver mass flow materials maximum microgravity mission motion NASA nozzle object operational orbital mechanics oxygen particles payload performance plane planetary pressure problem produced propeller propulsion radiation ratio rocket satellite semimajor axis simulation Skylab solar space environment Space Shuttle space station spacecraft spaceflight specific speed stability static structural surface temperature thermal thrust truss turbine turbofan turbojet United vector velocity wing