Theory and Procedure for Determining Loads and Motions in Chine-immersed Hydrodynamic Impacts of Prismatic Bodies
Theory and Procedure for Determining Loads and Motions in Chine-immersed Hydrodynamic Impacts of Prismatic Bodies

Author: Emanuel Schnitzer

Publisher:

Published: 1952

Total Pages: 58

ISBN-13:

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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.

Theory and Procedure for Determining Loads and Motions in Chine-immersed Hydrodynamic Impacts of Prismatic Bodies
Theory and Procedure for Determining Loads and Motions in Chine-immersed Hydrodynamic Impacts of Prismatic Bodies

Author: Emanuel Schnitzer

Publisher:

Published: 1952

Total Pages: 740

ISBN-13:

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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.

NASA Memorandum
NASA Memorandum

Author: United States. National Aeronautics and Space Administration

Publisher:

Published: 1959

Total Pages: 520

ISBN-13:

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Investigation of the Compressive Strength and Creep of 7075-T6 Aluminum-alloy Plates at Elevated Temperatures
Investigation of the Compressive Strength and Creep of 7075-T6 Aluminum-alloy Plates at Elevated Temperatures

Author: William D. Deveikis

Publisher:

Published: 1957

Total Pages: 584

ISBN-13:

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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.

Aerodynamic Loads on a Leading-edge Flap and a Leading-edge Slat on the NACA 64A010 Airfoil Section
Aerodynamic Loads on a Leading-edge Flap and a Leading-edge Slat on the NACA 64A010 Airfoil Section

Author: John A. Kelly

Publisher:

Published: 1954

Total Pages: 706

ISBN-13:

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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.