| 出版: | Ann Arbor, Mich. : J. W. Edwards, In. |
| 附註: | "This book was originally begun as a joint undertaking with Mr. Wyckoff, and its plan and much of the material were outlined jointly."--Pref. |
| 出版: | Ann Arbor, Mich. : J.W. Edwards |
| 出版: | New Haven, London, G. Cumberledge : Yale university press; Oxford university press |
| 附註: | Preface, by K. M. Bowman.--Scope and method of the study, by E. M. Jellinek.--pt. I. Alcohol addiction and its treatment, by K. M. Bowman and E. M. Jellinek. Alcoholic mental disorders, by K. M. Bowman and E. M. Jellinek. Bibliography for part I (p. [152]-169).--pt. II. Vitamin deficiencies in chronic alcoholism, by Norman Jolliffe. Alcoholic encephalopathies and nutrition, by Norman Jolliffe, Herman Wortis and M. H. Stein. Marchiafava's disease, by Giorgio Lolli. Cirrhosis of the liver, by Norman Jolliffe and E. M. Jellinek. Bibliography for part II (p. [310]-324) |
| 出版: | [Princeton, N.J. : The University |
| 附註: | Running title: Fresh-water angling, the contemplative man's sport. Title from cover. Bibliography: p. 21-24 |
| 出版: | Washington, D.C. : U. S. Govt. print. off. |
| 出版: | Washington : U.S. Govt. Print. Off. |
| 出版: | Washington : U. S. Govt. print. off. |
| 出版: | [Washington] National Marine Fisheries Service; [for sale by the Supt. of Docs., U.S. Govt. Print. Off.] : |
| ISBN: | 0010-2989 |
| 附註: | Vols. for 1946-June 1965 issued by the United States Fish and Wildlife Service; July 1965-Aug./Sept. 1970 by the Bureau of Commercial Fisheries; 1970-May/June 1972 by the National Marine Fisheries Service |
| 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 October 1944."FU "Originally issued March 1946 as Advance Restricted Report L5H11a."FU "Report no. L-99."FU Includes bibliographic references (p. 16). Summary: Stability and control characteristics determined from tests in the Langley 19-foot pressure tunnel of a 0.2375-scale model of the Douglas XA-26 airplane are compared with those measured in flight tests of a Douglas A-26B airplane. Agreement regarding static longitudinal stability as indicated by the elevator-fixed neutral points and by the variation of elevator deflection in both straight and turning flight was found to be good except at speeds approaching the stall. At these low speeds the airplane possessed noticeably improved stability, which was attributed to pronounced stalling at the root of the producion wing. The pronounced root stalling did not occur on the smooth, well-faired model wing. Elevator tab effectiveness determined from model tests agreed well with flight-test tab effectiveness, but control-force variations with speed and acceleration were not in good agreement. Although some discrepancy was introduced by the absence of a seal on the model elevator and by small differences in the determination of elevator deflections, correlation in control-force characteristics was also influenced by the effects of fabric distortion at high speeds and by small construction dissimilarities such as differences in trailing-edge angle. Except for the wave-off condition, in which the tunnel results indicated rudder-force reversal at a higher speed than the flight tests, agreement in both rudder-fixed and rudder-free static directional stability was good. Model and airplane indications of stick-fixed and stick-free dihedral effect were also in good agreement, although some differences in geometric dihedral may have existed because of wing bending in flight. 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 1946."FU "Originally issued February 1946 Advance Restricted Report L6A05b."FU "Report no. L-154."FU Summary: The horizontal and vertical components of the induced velocity in front of an inclined propeller in a horizontal stream were obtained by a magnetic-analogy method. The problem was formulated in terms of the linear theory of the acceleration potential of an incompressible nonviscous fluid. The propeller was assumed to be an actuator disk. The horizontal component of the induced velocity was found by a numerical calculation. Numerical calculation of the vertical component, however, was not practicable; therefore the vertical component was obtained from electrical measurements by use of the analogy between the acceleration potential of an incompressible nonviscous fluid and the potential of a magnetic field. An alternative formulation of the problem in terms of the trailing-vortex sheet is shown to be equivalent to the acceleration-potential formulation if the thrust coefficient is assumed so small that the slipstream is not deflected and undergoes no contraction. From the results presented, induced velocities of greater accuracy are shown to be obtainable from a modification of the vortex theory based on the assumption of a constant finite down-wash angle of the slipstream. 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 "Originally issued August 1944 as Advance Confidential Report L4H15."FU Includes bibliographic references (p. 10). Summary: The first data obtained in the United States under the controlled testing conditions necessary for establishing relationships among the numerous parameters involved when a float having both horizontal and vertical velocity contact a water surface are presented. The data were obtained at the NACA impact basin. The report is confined to a presentation of the relationship between resultant velocity and impact normal acceleration for various float weights when all other parameters are constant. Analysis of the experimental results indicated that the maximum impact normal acceleration was proportional to the square of the resultant velocity, that increases in float weight resulted in decreases in the maximum impact normal acceleration, and that an increase in the flight-path angle caused increased impact normal acceleration. 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 "Originally issued January 1946 as Advance Confidential Report L5G31a."FU "Report no. L-76."FU Includes bibliographic references (p. 11). Summary: An investigation has been conducted in the Langley rectangular high-speed tunnel to determine the effect of compressibility on the pressure distribution for a modified NACA 65,3-019 airfoil having a 0.20-chord flap. The investigation was made for an angle-of-attack range extending from -2À to 12À at flap deflections from 0À to -12À. Test data were obtained for Mach numbers from 0.28 to approximately 0.74. The results show that the effectiveness of the trailing-edge-type control surface rapidly decreased and approached zero as the Mach number increased above critical value. 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 April 1946."FU "Originally issued April 1946 as Advance Restricted Report L6C13."FU "Report no. L-213."FU Includes bibliographic references (p. 41). Summary: The flow inclination induced outside cold and hot propulsive jets by the turbulent spreading has been derived. Certain simplifying assumptions were employed and the region near the orifice was not treated. The effect of jet temperature on the flow inclination was found to be small when the thrust coefficient is used as the criterion for similitude. The deflection of a jet due to angle of attack has been derived and found to be appreciable but small for normal flight conditions with small normal accelerations. The average jet-induced downwash over a tail plane has been obtained in terms of the geometry of the jet-tail configuration. These results have been applied to the estimation of the effect of the jets on the static longitudinal stability and trim of jet-propelled airplanes. 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 "Originally issued March 1946 as Advance Confidential Report L6A22."FU "Report no. L-119."FU Summary: Approximate formulas for the computation of the momentum thicknesses of turbulent boundary layers on two-dimensional bodies, on bodies of revolution at zero angle of attack, and on the inner surfaces of round channels all in compressible flow are given in the form of integrals that can be conveniently computed. The formulas involve the assumptions that the momentum thickness may be computed by use of a boundary-layer velocity profile which is fixed and that skin-friction formulas for flat plates may be used in the computation of boundary-layer thicknesses in flow with pressure gradients. The effect of density changes on the ration of the displacement thickness to the momentum thickness of the boundary layer is taken into account. Use is made of the experimental finding that the skin-friction coefficient for turbulent flow is independent of Mach number. The computations indicated that the effect of density changes on the momentum thickness in flows with pressure gradients is small for subsonic flows. 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 January 1946."FU "Originally issued January 1946 as Advance Restricted Report L5J02."FU "Report no. L-54."FU Includes bibliographic references (p. 15). Summary: The effects of negative dihedral on lateral stability and control characteristics at high lift coefficients have been determined by flight tests of a model in the Langley free-flight tunnel. The geometric dihedral angle of the model wing was varied from 0À to -20À and the vertical-tail area, from 0 to 35 percent of the wing area. The model was flown with various combinations of dihedral angle and vertical-tail area at lift coefficients of 1.0, 1.4, and 1.8. As the effective dihedral was decreased from 0À to -15À, the model became increasingly difficult to fly. With an effective dihedral of -15À the flying characteristics were considered to be dangerous because, when there was only a slight lag in the application of corrective control following a disturbance, the unstable moments resulting from spiral instability became sufficiently large to overpower the moments of the controls so that return to straight flight was impossible. Inasmuch as full-scale airplanes because of their greater size will diverge at a slower rate than free-flight models, the amount of negative effective dihedral that would constitute a dangerous condition is expected to be greater for full-scale airplanes. Also available in electronic format.FU |
| 出版: | [Washington] : U.S. Navy dept., Office of research and inventions |
| 附註: | "Prepared by A.N. Lowan ... and P.M. Morse [and others]" Reproduced from type-written copy. cover-title |
| 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 February 1946 as Restricted Bulletin L5K21a."FU "Report no. L-68."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 varying resultant velocities with the model at 12À trim. The model had a 22 1/2À angle of dead rise and a total weight of 1100 pounds. 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 "Originally issued February 1946 as Restricted Bulletin L5K21."FU "Report no. L-69."FU Includes bibliographic references (p. 6). Summary: Tests were made in the Langley impact basin to determine the relationship between impact normal acceleration and flight-path angle for seaplanes landing in smooth water. The tests were made at both high and low forward speeds and at trims of 6À and 9À. The model had 22 1/2À angle of dead rise and a gross wieght of 1100 pounds. Also available in electronic format.FU |
| 出版: | Seattle, Wash. : Superior publishing company |
| 出版: | Washington : U.S.G.P.O. |
| 附註: | Includes bibliographical references. "From Fishery bulletin of the Fish and Wildlife Service, volume 50". |
| 出版: | Washington : U. S. Govt. print. off. |
| 附註: | v.1.On H. Res. 38.--v.2.On H. Res. 38.--v.3.On H. Res 36.--v.4.On H. Res1032, 2814, 2856, 4690.--v.5.On H.J. Res. 396, 401 |
| 出版: | [Sacramento] : State of California, Dept. of Natural Resources, Division of Fish and Game, Bureau of Marine Fisheries |