Theory and Procedure for Determining Loads and Motions in Chine-immersed Hydrodynamic Impacts of Prismatic Bodies PDF Download
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Author: Emanuel Schnitzer Publisher: ISBN: Category : Aeronautics Languages : en Pages : 58
Book Description
A theoretical method is derived for computing the motions and hydrodynamic loads during water landings of prismatic bodies involving appreciable immersion of the chines. A simplified method of computation covering flat-plate and V-bottom bodies with beam-loading coefficients greater than unity is given as a separate section. Comparisons of theory with experiment are presented as plots of impact lift coefficient and maximum draft-beam ratio against flight-path angle and as time histories of loads and motions. Fair agreement is found to exist for chine-immersed landings for angles of dead rise of 0 degrees and 30 degrees, beam-loading coefficients from 1 to 36.5, flight-path angles from 2 to 90 degrees, and trims from 6 to 45 degrees.
Author: Emanuel Schnitzer Publisher: ISBN: Category : Impact Languages : en Pages : 740
Book Description
A theoretical method is derived for computing the motions and hydrodynamic loads during water landings of prismatic bodies involving appreciable immersion of the chines. A simplified method of computation covering flat-plate and V-bottom bodies with beam-loading coefficients greater than unity is given as a separate section. Comparisons of theory with experiment are presented as plots of impact lift coefficient and maximum draft-beam ratio against flight-path angle and as time histories of loads and motions. Fair agreement is found to exist for chine-immersed landings for angles of dead rise of 0 degrees and 30 degrees, beam-loading coefficients from 1 to 36.5, flight-path angles from 2 to 90 degrees, and trims from 6 to 45 degrees.
Author: Robert J. Tapscott Publisher: ISBN: Category : Charts, diagrams, etc Languages : en Pages : 692
Book Description
Theoretically derived charts showing steady-state and first- and second-harmonic flapping coefficients are presented for helicopter rotors having hinged rectangular blades with a linear twist of 0, -8, and -16 degrees. The charts, showing the rotor flapping coefficients for combinations of inflow ratio and blade pitch angle, are presented for tip-speed ratios ranging from 0.05 to 0.50.
Author: George E. Glawe Publisher: ISBN: Category : Combustion gases Languages : en Pages : 820
Book Description
A Nusselt-Reynolds number relation for cylindrical thermocouple wires in crossflow was obtained from the experimental determination of time constants. Tests were conducted in exhaust gas over a temperature range of 2000 to 3400 R, a Mach number range of 0.3 to 0.8, and a static-pressure range from 2/3 to 1-1/3 atmospheres, yielding a Reynolds number range of 450 to 3000. The correlation obtained is Nu=(0.428 plus or minus 0.003) times the square root of Re with average deviations of a single observation of 8.5 percent. This relation is the same as one previously reported for room-temperature conditions.
Author: Emanuel Schnitzer
Author: Emanuel Schnitzer
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: Robert J. Tapscott
Author: George E. Glawe
Author: United States. Ship Structure Committee
Author: United States. National Aeronautics and Space Administration
Author: Gloria R. Champine
Author: United States. National Advisory Committee for Aeronautics