| 出版: | New York : The Macmillan company |
| 附註: | "Useful books": p. 102 "First printing." |
| 出版: | Washington : U.S. Govt. print. off. |
| 附註: | Includes hearings held Jan. 21, 24-25, 1944 Theodore G. Bilbo, chairman of subcommittee. |
| 出版: | [Washington : U.S. Govt. Print. Off.] |
| 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 May 1944."FU "Originally issued May 1944 as Memorandum Report."FU "Report no. L-112."FU Includes bibliographic references (p. 9). Summary: A method is presented for predicting the amplitude and frequency, under certain simplifying conditions, of the hunting oscillations of an automatically controlled aircraft with lag in the control system or in the response of the aircraft to the controls. If the steering device is actuated by a simple right-left type of signal, the series of alternating fixed-amplitude signals occurring during the hunting may ordinarily be represented by a square wave. Formulas are given expressing the response to such a variation of signal in terms of the response to a unit signal. A more complex type of hunting, which may involve cyclic repetition of signals of varying duration, has not been treated and requires further analysis. Several examples of application of the method are included and the results discussed. Also available in electronic format.FU |
| 出版: | Yonkers, N. Y. : The Arlington chemical company |
| 附註: | Includes bibliographical references. |
| 出版: | New York : Reinhold Publishing Corporation |
| 附註: | Bibliography at end of each chapter. |
| 出版: | Detroit : Wayne University Press |
| 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 November 1944 as Advance Restricted Report L4I21."FU Includes bibliographic references (p. 25-26). Summary: A number of samples of flight acceleration data taken by the National Advisory Committee for Aeronautics under a variety of operating conditions were evaluated to determine the total frequencies and the frequency distribution of atmospheric gusts. The samples include 1748 hours of operation by several airplanes of the domestic airlines of the United States, a Martin M-130 airplane of the Pacific Division of Pan American Airways System, and the Boeing B-15 airplane of the Army Air Forces. These data are supplemented by V-G records, so that more than 9,000,000 miles of operation are represented. Samples taken on an Aeronca C-2 airplane at low altitude in the turbulent air of the earth's boundary layer are compared with similar samples taken on the Lockheed XC-35 airplane at high altitude within cumulus-congestus and cumulo-nimbus clouds. Similar data of German origin have been reanalyzed and included for comparison. Also available in electronic format.FU |
| 出版: | [Washington, D.C.] : U.S. Dept. of the Interior, Bureau of Mines |
| 出版: | Los Angeles : University of Southern California Press |
| 出版: | Tallahassee : Published for the Florida Geological survey |
| 附註: | "Prepared by the United States Geological survey in cooperation with the Florida Geological survey, Dade County, and the cities of Miami, Miami Beach, and Coral Gables." At head of title: State of Florida. Dept. of conservation. Florida Geological survey. S. E. Rice, supervisor of conservation. Herman Gunter, director, Geological survey. "References": p.113-115 |
| 出版: | Urbana, Illinois : |
| 附註: | At head of title: State of Illinois, Dwight H. Green, Governor. Dept. of Registration and Education, Frank G. Thompson, Director. Division of the State Geological Survey, M.M. Leighton, Chief, Urbana. Bibliography: p. 26-28 |
| 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 1944."FU "Originally issued April 1944 as Advance Restricted Report L4D18."FU "Report no. L-28."FU Includes bibliographic references (p. 23). Summary: A theoretical investigation has been made of the oscillations performed by suspended bodies of the type commonly used for trailing airspeed heads ans similar towed devices. The primary purpose of the investigation was to design an instrument that will remain stable as it is drawn up to a support underneath an airplane without attention on the part of the pilot. Flight tests of a model airspeed head were made to supplement the theoretical study. Unstable oscillations of the body at short cable lengths were predicted by the theory, but the rate of increase of amplitude of these oscillations was very small. In flight tests, more violent types of instability were believed to be caused by unsteady or nonuniform air flow in the region where the cable was lowered from the airplane. No practical method was found to provide large damping of the oscillations at short cable lengths, but the degree of stability present in a suitably designed suspended body was shown to be satisfactory if the body was lowered into a uniform air stream. 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 July 1944 as Advance Restricted Report L4G31."FU "Report no. L-203."FU Includes bibliographic references (p. 8). Summary: An instrument for warning the pilot of the approach of the airplane to critical speed conditions has been developed at the Langley Memorial Aeronautical Laboratory. The device closes a contact that completes the electrical circuit of a suitable warning indicator when a predetermined limiting Mach number is approached. The operation of the instrument is based on the relation between Mach number and the ratio of impact pressure to total pressure. These pressures are obtained from the pitot-static installation on the airplane. The accuracy of the device, exclusive of errors due to the pitot-static installation, is «1 percent. 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 May 1944."FU "Originally issued May 1944 as Restricted Bulletin L4E31."FU "Report no. L-100."FU Includes bibliographic references (p. 6). Summary: Ground tests were conducted in a specially constructed cockpit rig to determine the maximum rates of control-stick (elevator) motion and the corresponding maximum stick forces that could be exerted, as based on results obtained with a number of pilots. The measurements indicate that the maximum rate of push on the control stick is greater than the maximum rate of pull; that the maximum rate of either push or pull is less when a mental restriction is imposed upon the pilot; and that the maximum rates at which the pilot thought he would apply elevator control forces in flight are considerably less than the rates at which he could apply these forces with the same stick stiffness. Also available in electronic format.FU |
| 出版: | New York : E.P. Dutton |
| 附註: | The author's experiences as a ferry pilot from 1941 to 1943 Map on lining-papers |
| 出版: | New York : Columbia university press |
| 附註: | Bibliography: p. [235]-240 |
| 出版: | [Washington : |
| 出版: | Washington, D.C. : [U. S. Govt. Print. Off |
| 附註: | "Prepared at the request of the Bureau of yards and docks, U. S. Navy, by Dr. J. H. Kraemer of the Supply and resources service, Office of economic programs, Foreign economic administration."--Foreword. |
| 出版: | Washington, D.C. : [U.S. govt. print. off. |
| 附註: | "Prepared at the request of the Bureau of yards and docks, U.S. Navy, by the Supply and resources service, Foreign economic administration."--Foreword. |
| 出版: | Harrisburg : Commonwealth of Pennsylvania, Dept. of Public Instruction |
| 附註: | Half-title: Vocational training for war production workers. |
| 出版: | Newport News, Va. : Joint employee-management war production drive committee, Newport News shipbuilding and dry dock co. |
| 出版: | [New Orleans : Higgins industries, inc. |
| 附註: | "Second edition." "Based upon lectures to students in previous classes of the Higgins boat operators and marine engine maintenance school, as well as technical articles by the author previously published in the American journal, 'Motor boating'."--Pref. |
| 出版: | Berkeley, Cal. : Agricultural Experiment Station |
| 出版: | New York and London : McGraw-Hill book company, inc. |
| 附註: | "Originally ... in ... two mimeographed pamphlets, containing approximately 900 questions, and answers."--Pref. |
| 出版: | [Washington, D.C.] : U.S. Dept. of the Interior, Bureau of Mines |
| 出版: | [LaConner, Wash. : Puget Sound steel co.] |
| 附註: | "First edition, April, 1943. Second edition (revised), March, 1944." At head of title: New revised edition. |
| 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 October 1944 as Restricted Bulletin L4I07."FU "Report no. L-96."FU Includes bibliographic references (p. 14). Summary: Because large airplanes of the transport and bomber categories have been reported to have spun inadvertently, the available information on the subject has been reviewed. Results of model tests, as well as reports of full-scale-airplane spins, were considered. It is concluded that large airplanes should not be intentionally spun because these aircraft are not designed for the loads and speeds that may be encountered in the spin and recovery. If a large airplane is stalled, wither inadvertently or for familiarization purposes, the pilot should apply sufficient down elevator to relieve the stall at the very first sign of stalling. The throttles should be closed if the airplane has started to roll off into a turn and the nose has dropped appreciably. Even after the airplane has rolled off on a wing, the pilot can regain control by promptly moving the stick forward and then using all three controls to return t level 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 June 1944."FU "Originally issued June 1944 as Advance Restricted Report L4F02."FU "Report no. L-55."FU Includes bibliographic references (p. 10). Summary: The effects of static margin and rotational damping in pitch on the longitudinal stability characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rotational damping in pitch was varied over a wide range by using horizontal tails that varied in area from 0 to 24 percent of the wing area. A range of static margins from 2 to 16 percent of the mean aerodynamic chord was covered in the tests. For each test condition the model was flown and the longitudinal steadiness characteristics were noted. It was found in the investigation that longitudinal steadiness was affected to a much greater extent by changes in static margin than by changes in rotational damping. The best longitudinal steadiness was noted at large values of static margin. For all values of rotational damping, the steadiness of the model decreased as the static margin was reduced. The model was especially unsteady at low values of static margin (0.03 or less). Reduction in rotational damping had little effect on longitudinal steadiness, except that with low values of static margin (0.03 or less) the longitudinal divergences were sometimes more violent with the tailless (low rotational damping) condition. 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 1944."FU "Originally issued January 1944 as Advance Restricted Report 4A22."FU "Report no. L-457."FU Includes bibliographic references (p. 31-32). Summary: The existence of energy dissipations in gas dynamics, which must be attributed to a lag in the vibrational heat capacity of the gas, has been established both theoretically and experimentally. The flow about a very small impact tube is discussed. It is shown that total-head defects due to heat-capacity lag during and after the compression of the gas at the nose of an impact tube are to be anticipated. Experiments quantitatively verifying these anticipations in carbon dioxide are discussed. A general theory of the dissipations in a more general flow problem is developed and applied to some special cases. It is pointed out that energy dissipations due to this effect are to be anticipated in turbines. Dissipations of this kind might also introduce errors in cases in which the flow of one gas is used in an attempt to simulate the flow of another gas. Unfortunately, the relaxation times of most of the gases of engineering importance have not been studied. A new method of measuring the relaxation time of gases is introduced in which the total-head defects observed with a specially shaped impact tube are compared with theoretical considerations. A parameter is thus evaluated in which the only unknown quantity is the relaxation time of the gas. This method has been applied to carbon dioxide and has given consistent results for two impact tubes at a variety of gas velocities. 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 1944 as Advance Restricted Report 4B23."FU Includes bibliographic references (p. 12). Summary: In order to determine jet-boundary corrections to cowling-flap-outlet pressures, corrections to the velocities near a cowling-flap tip have been studied by an electrical-analogy method. The presence of the low-energy air leaving the flap opening was taken into account by so shaping the nacelle model that its outer surface represented the stream surface leaving the flap tip. Copper was found unsatisfactory for use as electrode material. Good accuracy was obtained with chromium-plated copper for tank electrodes and platinum wire for the solution contacts. An 8-percent velocity correction was found for a typical nacelle in the LMAL 16-foot high-speed tunnel, corresponding to a correction of about 0.25 times free-stream dynamic pressure at the flap outlet. The results agreed approximately with the corrections calculated by Lamb's method for an equivalent source-sink ovoid. Also available in electronic format.FU |
| 出版: | Langley Field, VA : Langley Memorial Aeronautical Laboratory |
| 附註: | "Report date August 10, 1944."FU "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 October 1944 as Restricted Bulletin L4H10."FU Includes bibliographic references (p. 5). Summary: Local-instability tests of 24S-T aluminum-alloy formed Z- and channel-section columns were made in order to determine a length of test specimen that would avoid the increased strength associated with short lengths and also permit the occurrence of a convenient buckling pattern. The effect of column length on the critical compressive stress, on the average stress at maximum load, and on the number of half-waves of the buckling pattern is shown. A buckling pattern of three half-waves is indicated as desirable for test purposes. A curve is presented from which may be determined the lengths of Z- or channel-section columns that give a buckling pattern of three half-waves. When the strength for local instability is very high, a reduction in the length indicated by the curve may be necessary to prevent column failure. In order to avoid the increased strength associated with short lengths, a ratio of length to web width above 3.5 should be used. 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 May 1944."FU "Originally issued May 1944 as Advance Confidential Report L4E31."FU "Report no. L-139."FU Includes bibliographic references (p. 6). Summary: The results of flight investigations of the profile drag of several carefully finished conventional and low-drag airfoils are presented. The results indicated that in all cases lower profile-drag coefficients were obtained with the low-drag than with the conventional airfoils over the range of lift coefficient tested and that, for comparable conditions of lift coefficient and Reynolds number, the low-drag airfoils may have profile-drag coefficients which are at least 27 percent lower than the profile-drag coefficients of the conventional airfoils. Also available in electronic format.FU |
| 出版: | Washington : U. S. Govt. print. off. |
| 附註: | Issued also with the numbering of the congressional series under title: Distribution methods and costs. pt. 1 Important food products.--pt. 3 Building materials.--pt. 4 Petroleum products.--pt. 5 Advertising factor in distribution.--pt. 6 Milk distribution, prices, spreads, and profits.--pt. 7 Cost of production and distribution of fish in the Great Lakes area.--pt. 8 Cost of production and distribution of fish in New England.--pt. 9 Cost of production and distribution of fish on the Pacific Coast. |
| 出版: | New York : A. A. Knopf |
| 附註: | "The chronicle of a typical, rather than an actual community, a composite of numerous Oklahoma settlements."--Pref. "First edition." |
| 出版: | Oak Ridge, Tenn. : U.S. Atomic Energy Commission. Technical Information Service |
| 附註: | Date Declassified: October 16, 1950 This report is based on CP-2509 Work performed under Contract No. W-7401-eng-37 |
| 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 June 1944."FU "Originally issued June 1944 as Memorandum Report."FU "Report no. L-131."FU Summary: Tests were made in the LMAL 16-foot high-speed tunnel to determine the aerodynamic characteristics of a 1000-pound AN-M-65-AZON radio-controlled bomb at Mach numbers ranging from 0.2 to 0.6. Over the Mach number range covered in the tests the hinge-moment coefficients, yawing-moment coefficients, and lateral-force coefficients exhibited no important changes with increasing speed. The drag coefficients increased gradually with increasing Mach number but no sudden increases were observed. The effect on the bomb aerodynamic characteristics of antenna struts mounted on the bomb tail was found to be small. The rudder and aileron operating mechanisms were found to be capable of supplying several times the required torques for maximum control deflections at a Mach number of 0.6 at sea level. The operating mechanism is also adequate for maximum control deflections at a Mach number of 1.0 provided that no appreciable increases in hinge-moment coefficient occur between M = 0.6 and M = 1.0. However, because of uncertainty as to the value of the hinge-moment coefficient at or near M = 1.0, the desirability of providing more powerful control mechanisms was indicated. 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 November 1944 as Advance Restricted Report L4J05a."FU Includes bibliographic references (p. 24-25). Summary: An investigation has been made in the Langley free-flight tunnel to obtain an experimental verification of the theoretical rudder-free stability characteristics of an airplane model equipped with conventional rudders having negative floating tendencies and negligible friction. The model used in the tests was equipped with a conventional single vertical tail having rudder area 40 percent of the vertical tail area. The model was tested both in free flight and mounted on a strut that allowed freedom only in yaw. Measurements were made of the rudder-free oscillations following a disturbance in yaw. Tests were made with three different amounts of mass, moment of inertia, and center-of-gravity location of the rudder. Most of the stability derivatives required for the theoretical calculations were determined from force and free-oscillation tests of the particular model tested. The theoretical analysis showed that the rudder-free motions of an airplane consist largely of two oscillatory modes - a long-period oscillation somewhat similar to the normal rudder-fixed oscillation and a short-period oscillation introduced only when the rudder is set free. It was found possible in the tests to create lateral instability of the rudder-free short-period mode by large values of rudder mass parameters even though the rudder-fixed condition was highly stable. 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 June 1944."FU "Originally issued June 1944 as Advance Restricted Report L4F05."FU "Report no. L-93."FU Summary: Flight measurements were made on a modern pursuit airplane to determine the approximate magnitude of the horizontal tail loads in accelerated flight. In these flight measurements, pressures at a few points were used as an index of the tail loads by correlating these pressures with complete pressure-distribution data obtained in the NACA full-scale tunnel. In addition, strain gages and motion pictures of tail deflections were used to explore the general nature and order of magnitude of the fluctuating tail loads in accelerated stalls. The results indicated that, if the airplane were not stalled, a total up load of 5700 pounds would be experienced on the horizontal tail in an 8g pull-up and that, with power on, this load would be distributed unsymmetrically with about 800 pounds more up load on the left stabilizer than on the right. When stalling occurred there was an initial abrupt increase in the up tail load of the order of 100 percent of the previous load, which was followed by repeated load and stress variations due to tail buffeting. Under the condition of tail buffeting, the possibility of excessive stresses due to resonance was indicated. Also available in electronic format.FU |
| 出版: | New York, N.Y. : The Nitralloy corporation |
| 附註: | Bibliography: p. [43]-46 |