| 出版: | Langley Field, VA : Langley Memorial Aeronautical Laboratory |
| 附註: | "NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were previously held under a security status but are now unclassified. Some of these reports were not technically edited. All have been reproduced without change in order to expedite general distribution."FU "Originally issued July 1945 as Restricted Bulletin L5F15."FU "Report no. L-70."FU Includes bibliographic references (p. 10). Summary: An application of a modified hydrodynamic impact theory is presented. Plots are given from which the maximum load, the time to reach maximum load, and the variation of load with time may be obtained for a prismatic float of 22 1/2À angle of dead rise for different combinations of flight-path angle, trim, weight, velocity, and fluid density. The curves cover the range of trim, flight-path angle, and weight-velocity relationship for conventional airplanes. Test data obtained in the Langley impact basin are presented and are used to establish the validity of the theoretical curves. Also available in electronic format.FU |
| 出版: | Langley Field, VA : Langley Memorial Aeronautical Laboratory |
| 附註: | "NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were previously held under a security status but are now unclassified. Some of these reports were not technically edited. All have been reproduced without change in order to expedite general distribution."FU "Report date February 1945."FU "Originally issued February 1945 as Restricted Bulletin L5A24."FU "Report no. L-211."FU Includes bibliographic references (p. 5). Summary: Tests were made in the Langley impact basin to determine the relationship between impact normal acceleration and flight-path angle for seaplanes landing on smooth water. The tests were made at both high and low forward speeds with the model at 3À trim. The model had a dead-rise angle of 22 1/2À and, with the drop linkage, weighed 1100 pounds. Also available in electronic format.FU |
| 出版: | San Francisco : Camera craft publishing company |
| 出版: | Langley Field, VA : Langley Memorial Aeronautical Laboratory |
| 附註: | "NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were previously held under a security status but are now unclassified. Some of these reports were not technically edited. All have been reproduced without change in order to expedite general distribution."FU "Originally issued April 1945 as Restricted Bulletin L5C30."FU "Report no. L-77."FU Includes bibliographic references (p. 6). Summary: The effects of compressibility and angle of yaw on the pressure measured by a round-nose and a flat-nose total-pressure tube have been investigated. The tests were conducted in the Langley rectangular high-speed tunnel at Mach numbers from 0.3 to 0.9 for angles of yaw from 0À to 180À. The results indicated that no error was incurred in the measurement of total pressure by either tube for angles of yaw from 0À to 10À in the Mach number range investigated. At constant Mach numbers, the round-nose tube had a linear variation of total-pressure error with angle of yaw at angles ranging from 50À to 70À. This characteristic is desirable in yaw heads of the Y-type. The flat-nose tube had a nonlinear variation of total-pressure error with angle of yaw in this range. Also available in electronic format.FU |
| 出版: | Washington : |
| 附註: | Includes bibliographies. |
| 出版: | Washington : U.S. Govt. print. off. |
| 出版: | Washington : Anglo-American Caribbean commission |
| 出版: | [Washington, D.C.] : Military Intelligence Division, Office, Chief of Engineers, U.S. Army |