The Aeronautical Journal, Volume 74Royal Aeronautical Society, 1970 - Aeronautics |
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Page 27
... Method , the stiffness matrix is formed and the unknown displacements are found for the given loading conditions . In the Matrix Force Method , the flexibility matrix is formed and the internal forces are the unknowns to be determined ...
... Method , the stiffness matrix is formed and the unknown displacements are found for the given loading conditions . In the Matrix Force Method , the flexibility matrix is formed and the internal forces are the unknowns to be determined ...
Page 28
... method must fulfil two requirements which are , of course , closely linked . First , it must be able to make use of the simple arithmetic operations the computer is capable of , and secondly , the method must lend itself to a systematic ...
... method must fulfil two requirements which are , of course , closely linked . First , it must be able to make use of the simple arithmetic operations the computer is capable of , and secondly , the method must lend itself to a systematic ...
Page 379
... method of decision making needs to be stated . The best solution indicated by such a method is only the one which appears best on the assumptions made and at the time that the initial decision is to be taken . The fact that an event is ...
... method of decision making needs to be stated . The best solution indicated by such a method is only the one which appears best on the assumptions made and at the time that the initial decision is to be taken . The fact that an event is ...
Contents
S G Hooker THE ENGINE SCENE | 13 |
Edwards ENGINE DEVELOPMENT IN AN OPERATORS MARKET | 52 |
The Effect of Static Deflection on the Harmonic Resonance of a System with | 59 |
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Aero aerodynamic aerofoil aeroplane AESOP AFRAeS Air Transport aircraft airlines altitude analysis angle autoland Aviation blade boundary layer British cell CEng Chairman coefficient Committee compressor cost cruise design curve drag drag coefficient effect elements engine equations equipment ESRO Figure flight flow fluid flying FRAeS frequency function heat transfer helicopter hovercraft ICAO increase intake Lecture lift lift coefficient loading Mach number measured ment method NASA TN noise nozzle obtained Olympus ONERA operating optimisation organisation parameters performance pilot plate potential flow pressure problem programme propulsion prototype ratio Report Reynolds number rotor Royal Aeronautical Society shock tube shock wave shown in Fig shows simulated slot solution speed static stress structure supersonic surface take-off technical techniques temperature thrust tion Trident turbine velocity vortex VTOL weight wind tunnel wing