Interactive Aerospace Engineering and DesignMcGraw-Hill, 2002 - 356 страници 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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Страница 73
... given alti- tude h . 2. Calculate the lift coefficient C , for a given velocity v , by recalling the def- inition of dynamic pressure q = 1 / 2p ̧v2 : CL = 2W Pov2s 3. Calculate the drag coefficient from the drag polar for the aircraft ...
... given alti- tude h . 2. Calculate the lift coefficient C , for a given velocity v , by recalling the def- inition of dynamic pressure q = 1 / 2p ̧v2 : CL = 2W Pov2s 3. Calculate the drag coefficient from the drag polar for the aircraft ...
Страница 132
... [ given in Equation ( 6.16 ) ] . The equation for the exit velocity was developed in Section 6.3.6 , " Nozzles , " and depends on the thermodynamic properties of total temper- ature in the nozzle and the nozzle pressure ratio ( NPR ) [ given ...
... [ given in Equation ( 6.16 ) ] . The equation for the exit velocity was developed in Section 6.3.6 , " Nozzles , " and depends on the thermodynamic properties of total temper- ature in the nozzle and the nozzle pressure ratio ( NPR ) [ given ...
Страница 133
... given by Equation ( 6.11 ) and Equation ( 6.12 ) for M < 1 and M > 1 , respectively . The conditions at the compressor stage depend on inlet per- formance and freestream conditions . Temperature is given by To = Tso where the total ...
... given by Equation ( 6.11 ) and Equation ( 6.12 ) for M < 1 and M > 1 , respectively . The conditions at the compressor stage depend on inlet per- formance and freestream conditions . Temperature is given by To = Tso where the total ...
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A Brief History of Flight | 1 |
Introduction to Engineering | 20 |
Aerodynamics | 36 |
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