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
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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 : Aeronautics
Languages : en
Pages : 58
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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
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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: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 520
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1136
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Book Description
Author: William D. Deveikis
Publisher:
ISBN:
Category : Alloys
Languages : en
Pages : 584
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Book Description
Elevated-temperature compressive-strength test results from room temperature to 600 degrees F and creep test results from 350 degrees F to 500 degrees F are presented for V-groove edge-supported plates of 7075-T6 aluminum alloy. The test data are compared with calculations obtained from procedures for estimating maximum strength from material stress-strain curves and creep-failure stresses from isochronous stress-strain curves. The strength and creep results from this investigation are also compared with similar results from 2024-T3 aluminum-alloy plates.
Author: Gloria R. Champine
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 134
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Book Description
Author: Albert J. Evans
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 326
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1208
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Book Description
Author: John A. Kelly
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 706
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Book Description
A previous report, NACA TN 3007, gave force and moment data for the NACA 64A010 airfoil section equipped alternately with a flap and a slat at the leading edge, and with a split flap and a double-slotted flap at the trailing edge. The present report presents the chordwise distributions of pressure measured concurrently with the force and moment data of NACA 3007. The pressure data for the leading-edge flap and slat have been converted into coefficients of normal force, chord force, and moment based on the geometry of the leading-edge device.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 500
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Book Description
