| 出版: | Washington, D.C. : The Foundation |
| 出版: | [Washington : Environmental Protection Agency, Water Quality Office]; for sale by the Supt. of Docs., U.S. Govt. Print. Off.] |
| 出版: | Washington : National Aeronautics and Space Administration : [For sale by the National Technical Information Service, Springfield, Va.] |
| 附註: | Prepared at Flight Research Center. N71-18442 Cover title. Includes bibliographical references (p. 22). Investigation of angle of attack information display for pilots to increase efficiency of general aviation aircraft operation. |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration |
| 附註: | Prepared at Langley Research Center. Cover title. "N71-31330." Includes bibliographical references (p. 13). Static force tests of model of twin jet fighter aircraft at various angles of attack and sideslip angles to obtain data for theoretical spin studies. |
| 出版: | Rockville, Md : U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, National Ocean Survey, Office of Hyrography and Oceanography, Marine Chart Division, Marine Geophysics Group |
| 出版: | San Diego, Calif. : Washington, D.C. : University of California, San Diego, Scripps Institution of Oceanography Visibility Laboratory ; Advanced Research Projects Agency |
| 出版: | Washington, D.C. : U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, National Environmental Satellite Service |
| 出版: | Rockville, Md. : U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, National Ocean Service |
| ISBN: | 0270-5826 |
| 出版: | Washington : The Service. |
| ISBN: | 0364-0116 |
| 附註: | Formed by the union of: Environmental data bulletin; and: National Oceanographic Data Center. Newsletter. |
| 出版: | Washington : U.S. Govt. Print. Off. |
| 出版: | Seattle [etc.] : [Scientific Publications Office, National Marine Fisheries Office, NOAA] |
| ISBN: | 0090-0656 |
| 附註: | Not distributed to depository libraries in a physical form after v. 99, no. 3 (July 2001). Published in Washington, D.C., 1971- Vols. for <1971> prepared by: National Oceanic and Atmospheric Administration; <Apr. 1988-> by the Scientific Publications Office, National Marine Fisheries Service. Electronic serial mode of access: World Wide Web. |
| 出版: | Seattle, Wash. : Washington, D.C. : National Marine Fisheries Service ; For sale by the Supt. of Docs., U.S. G.P.O. |
| ISBN: | 0094-4580 |
| 附註: | Some issues not for sale by Supt. of Docs Chemical abstracts0009-2258 Biological abstracts0006-3169 Numbers not issued in chronological sequence. Merged with: NOAA technical report NMFS CIRC, to form: NOAA technical report NMFS. |
| 出版: | Rockville, Md. : Washington, D.C. : U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, Office of Public Affairs ; For sale by the Supt. of Docs., U.S. G.P.O. |
| ISBN: | 0014-0821 |
| 出版: | Rockville, Md. : Office of Public Affairs, National Oceanic and Atmospheric Administration; for sale by the Supt. of Docs., U.S. Govt. Print. Off. |
| ISBN: | 0014-0821 |
| 附註: | GeoRef0197-7482 A United States Department of Commerce publication. Supersedes U.S. Environmental Science Services Administration. ESSA. |
| 出版: | Washington : The Service; for sale by the Supt. of Docs., U.S. G.P.O. |
| ISBN: | 0099-9202 |
| 出版: | Seattle, WA : National Marine Fisheries Service |
| ISBN: | 0093-9412 |
| 出版: | Washington, DC : National Aeronautics and Space Administration |
| 附註: | "L-7377." "NASA TN D-6113." "March 1971." Includes bibliographical references (p. 57). An analytical study was made to assess the ability of a plot, simulated by permissible error performance, to control the entire lunar approach and descent with relatively simple guidance schemes. The control task consisted of applying retrothrust during the hyperbolic approach to establish a lunar orbit. During this lunar coasting orbit, the lunar module was separated from the command and service module. A second deorbit thrust period was used on the lunar module to establish a coasting descent, and a final thrust period was used to put the vehicle into a reasonable landing situation. Throughout the maneuver the pilot was permitted to make reasonable errors, selected in a random manner, in the thrust time and attitude control. The control schemes consisted of maintaining a constant vehicle attitude with respect to the line of sight to the lunar horizon for the first and second thrust periods, and a constant angle with respect to the line of sight to the orbiting command and service module for the third thrust period.--P. [i]. Also available online in PDF from NASA Technical Reports Server Web site. Sponsored by the National Aeronautics and Space Administration (NASA); performed by the NASA Langley Research Center under127-51-34-03 |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration |
| 附註: | Prepared at George C. Marshall Space Flight Center. Cover title. "N71-17479." Includes bibliographical references (p. 26). The responses of balloon and falling sphere wind sensors in turbulent flows are analyzed using Fourier transform techniques. The linearized equations of motion of a sensor that is subject to drag and gravitational body forces are developed by perturbing a sensor about an equilibrium uniform motion with turbulent or random wind fluctuations. The wind environment and sensor velocities are decomposed with stochastic Fourier-Stieltjes integrals, and the linearized equations of motion are used to derive the response functions and phase angles of the sensor motions. The results of the analysis are used to analyze the response properties of the Jimsphere balloon wind sensor and the effects that balloon motions would have on turbulence spectra if they were calculated with ballon and falling sphere wind data. The Kolmogorov inertial subrange and the Lumley subrange for nearly inertial isotropic turbulence in stably stratified fluids are used as specific examples in the calculations. System requirements: Adobe Acrobat Reader. [electronic resource] |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151] |
| 附註: | Includes bibliographical references (p. 27). An analysis has been made of the effects of spanwise variations of gust velocity in isotropic turbulence on a gust-alleviation system which employs an angle-of-attack vane mounted ahead of the wing to sense the vertical gust velocity. The wing flaps were moved in response to the vane deflection by a linear second-order servosystem to produce a lift opposite to that produced by the gust. Consideration of spanwise variation of gusts has indicated design parameters (gain and natural frequency of flap servosystem and vane location) that give substantial reduction of the lift due to gusts. |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration |
| 附註: | Prepared at Langley Research Center. N71-36411 Includes bibliographical references (p. 12). This report describes a theoretical method for estimating the aerodynamic loading on a wing-body configuration. In order to provide a basis for evaluation of the method, experimental measurements of surface pressures, forces, and moments were made on a series of basic wing-body configurations over a Mach number range from 2.5 to 4.5. Comparison of the theoretical estimates with these experimental data generally indicated good agreement for the entire range of configurations and test conditions. |
| 出版: | Washington, D.C. : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va. 22151] : National Aeronautics and Space Administration |
| 附註: | Includes bibliographical references (p. 36). Theoretical results are presented for the buckling of anisotropic plates. The plates are subjected to simple and combined in-plane loading. The plates are made from fiber composite material of boron/aluminum or high-modulus graphite/resin. The results are presented in nondimensional form as buckling load against fiber orientation angle for various plate aspect ratios. The results indicate that buckling loads of boron/aluminum plates are independent of fiber direction if the plate aspect ratios are greater than about 1, and moderately dependent when this ratio is less than about 1. In addition, the results indicate that the buckling loads are independent of aspect ratio for plates with aspect ratios greater than about 2. Boron/ aluminum composite plates can resist buckling loads more efficiently than graphite/resin composites on a specific buckling stress basis. The numerical algorithm and a listing of the computer code used to obtain the results are included. |
| 出版: | Washington, D.C. : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151] : National Aeronautics and Space Administration |
| 附註: | Includes bibliographical references (p. 18). Onboard procedures requiring only simple calculations have been developed for midcourse and approach guidance for translunar trajectories. For midcourse guidance the procedure relies solely on an optical range measurement. The approach-guidance procedure requires a star-to-body measurement and may require a range measurement, depending on the distance to the moon. For both procedures the velocity-correction vector is applied in a fixed inertial direction. In the approach-guidance procedure either one or two guidance maneuvers are applied, depending on the accuracy desired and tile distance to the moon. An error analysis showed that perilune radius can be controlled to a onesigma accuracy of about 30 km. System requirements: Adobe Acrobat Reader. [electronic resource] |
| 出版: | Washington, D.C. : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151] : National Aeronautics and Space Administration |
| 附註: | Includes bibliographical references (p. 34). Experimental and analytical investigations of the vibratory behavior of ring-stiffened truncated-cone shells are described. Vibration tests were conducted on (1) 60 [degree] conical shells having up to four ring stiffeners and for free-free and clamped-free edge constraints and (2) 90 [degree] conical shells, for two thicknesses, each with two angle rings and for free-free, free-clamped, and clamped-clamped edge constraints. The analytical method is based on linear thin-shell theory, employing the Rayleigh-Ritz method. Discrete rings are represented as composed of one or more segments, each of which is a short truncated-cone shell of uniform thickness. Equations of constraint are used to join a ring and shell along a circumferential line connection. Excellent agreement was obtained for comparisons of experimental and calculated frequencies. |
| 出版: | Washington, D.C. : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151] : National Aeronautics and Space Administration |
| 附註: | Includes bibliographical references (p. 25-26). Results are presented from torsion tests conducted on 36 multilayered, filament-wound, glass-epoxy tubes. Configurations with helical windings and with alternating helical and circumferential windings were investigated for various winding angles. Under small loadings, shear moduli deduced from linear shear stress-strain curves were found to be in reasonable agreement with analytical predictions. Under larger loadings, various degrees of nonlinearity in shear stress-strain curves were encountered, depending on the helical winding angle. Experimental torsional strengths were defined by a 0.2 -percent offset yield stress or by maximum stress when large nonlinearities did not exist. These strengths were compared with torsional buckling predictions for orthotropic cylinders, and with material strength predictions based on orthotropic yield criteria and elastic stress analysis. Computed elastic buckling stresses were considerably higher than the experimental strengths for most of the test specimens except for those with only 30° and 45 [degree] windings. Experimental torsional strengths- were found to correlate with conventional yield predictions if predicted yielding in certain layers were ignored or if unrealistically large transverse tensile and shear strengths of unidirectional laminae were employed in the analysis. System requirements: Adobe Acrobat Reader. [electronic resource] |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce] |
| 附註: | Prepared at Langley Research Center. "December 1971."--Cover. Major NASA subject terms: aerodynamic characteristics, canard configurations, longitudinal stability, variable sweep wings, angle of attack, fighter aircraft, mach number, supersonic speed, wind tunnel stability tests. Includes bibliographical references (p. 8). An experimental investigation was made in the Mach number range from 1.60 to 2.86 to determine the static longitudinal aerodynamic characteristics of close-coupled wing-canard configurations. Three canards, ranging in exposed planform area from 17.5 to 30.0 percent of the wing reference area, were employed in this investigation. The canards were either located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. Most data obtained were for a model with a 60 deg leading-edge-sweep wing; however, a small amount of data were obtained for a 44 deg leading-edge-sweep wing. The model utilized two balances to isolate interference effects between wing and canard. In general, it was determined that at angle of attack for all configurations investigated with the canard in the plane of the wing an unfavorable interference exists which causes the additional lift on the canard generated by a canard deflection to be lost on the wing due to an increased downwash at the wing from the canard. Further, this interference decreased somewhat with increasing Mach number. Raising the canard above the plane of the wing also greatly decreased the interference of the canard deflection on the wing lift. However, at Mach 2.86 the presence of the canard in the high position had a greater unfavorable interference effect at high angles of attack than the canard in the wing plane. This interference resulted in the in-plane canard having better trimmed performance at Mach 2.86 for the same center-of-gravity location. |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration |
| 附註: | "September 1971." Cover title. Includes bibliographical references (p. 50-51). During the 16 glide flights of the M2 -F2 lifting body vehicle, severe lateral pilot-induced oscillations occurred on three occasions in the low - angle of -attack, final-approach, preflare situation. These oscillations were analyzed qualitatively to determine the type and similarity and by a systems analysis to determine the root cause. The analysis was complemented by a piloted simulator study, which verified the results. The systems analysis revealed the presence of a coupled roll-spiral mode which caused the pilots to generate a closed-loop lateral instability in the low-angle -of -attack, preflare flight region. A systems analysis, a piloted simulator study, and flight data showed that the addition of a fixed center fin lessened the pilot-induced-oscillation tendencies in the critical flight region. |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration |
| 附註: | Prepared at Langley Research Center. "August 1971." N 71-33776 Includes bibliographical references (p. 264). The experimental balance and pressure data obtained from tests of an untwisted variable-sweep wing with an outboard pivot exhibited nonlinearities in both total normalforce-coefficient and pitching-moment-coefficient curves for all sweep angles and fuselage conditions. These total effects have been traced back through the section data and pressure distributions to find the causes. The causes of these nonlinearities were found to be (1) separation of flow on the outer panel and (2) a leading-edge vortex flow on the inner panel. A fuselage added to the wing had little effect on the aerodynamic characteristics. Predictions of wing loadings and performance characteristics were made by using the modified Multhopp method and a comparison with experimental results indicated reasonable agreement. The changes in span loading as a result of leading-edge shed-vortex formation and flow separation at the higher angles of attack caused an increase in the induced-drag parameter. |
| 出版: | Washington, D.C. : [Springfield, Va. : National Aeronautics and Space Administration ; For sale by the National Technical Information Service] |
| 附註: | Prepared at Langley Research Center. N71-35213 Cover title. Includes bibliographical references (p. 10). The investigation was conducted to determine the dynamic stability derivatives of an externally blown jet-flap transport configuration having clustered inboard pod-mounted engines and full-span triple-slotted flaps. The results showed that the model had positive damping in pitch, roll, and yaw up to the stall angle of attack. The application of power resulted in an increase in pitch damping at high angles of attack and a moderate increase in yaw damping for the higher flap deflections but had no consistent effects on roll damping. For a given level of total engine thrust, the damping derivatives were generally not affected by frequency or by having one engine inoperative. |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151] |
| 附註: | Includes bibliographical references (p. 29). Results from an investigation of the effects of underexpanded engine exhaust flow on the aerodynamic performance and stability of a cruise airplane at Mach 6 are presented. The influence of wing reflex angle and nozzle geometry on exhaust flow interference effects was investigated on a flat-plate model. The experiments were conducted at a free-stream Reynolds number of 17.05 X 10 (to the 6 power) based on the length of the airplane model over a model angle-of-attack range of 0(degrees) to 10(degrees) and at nozzle static-pressure ratios from 1 to approximately 4 |
| 出版: | Washington, D.C. : Springfield, Va. : National Aeronautics and Space Administration ; For sale by the Clearinghouse for Federal Scientific and Technical Information |
| 附註: | Prepared by Ames Research Center and U.S. Army Air Mobility R & D Laboratory. "November 1971." N72-10031 Includes bibliographical references (p. 9). The aerodynamic characteristics of a full scale executive type jet transport aircraft with a T-tail were investigated in a 40 x 80 ft (12.2 by 24.4 meter) wind tunnel (subsonic). Static, longitudinal, and lateral stability, and control characteristics were determined at angles of attack from -2 deg to 42 deg. The aircraft wing had 13 deg of sweep and an aspect ratio of 5.02. The aircraft was tested power off with various wing leading- and trailing-edge high lift devices. The basic configuration was tested with and without such components as engine nacelles, wing tip tanks, and empannage. Hinge-moment data were obtained and downwash angles in the horizontal-tail plane location were calculated. The data were obtained at Reynolds numbers of 4.1 million and 8.7 million based on mean aerodynamic chord. The model had static longitudinal stability through initial stall. Severe tail buffet occurred near the angle of attack for maximum lift. Above initial stall the aircraft had pronounced pitch-up, characteristic of T-tail configurations. A stable trim point was possible at angles of attack between 30 deg and 40 deg (depending on c.g. location and flap setting). Hinge-moment data showed no regions with adverse effects on stick force. Comparisons of wind-tunnel data and flight-test are presented. |
| 出版: | Washington : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.] |
| 附註: | Cover title. Includes bibliographical references (p. 9-10). Aerodynamic characteristics of a model designed to represent an all body, hypersonic cruise aircraft are presented for Mach numbers from 0.65 to 10.6. The configuration had a delta planform with an elliptic cone forebody and an afterbody of elliptic cross section. Detailed effects of varying angle of attack (-2 to 15 deg), angle of sideslip (-2 to 8 deg), Mach number, and configuration buildup were considered. In addition, the effectiveness of horizontal tail, vertical tail, and canard stabilizing and control surfaces was investigated. The results indicate that all configurations were longitudinally stable near maximum lift drag ratio. The configurations with vertical tails were directionally stable at all angles of attack. Trim penalties were small at hypersonic speeds for a center of gravity location representative of the airplane, but because of the large rearward travel of the aerodynamic center, trim penalties were severe at transonic Mach numbers. |
| 出版: | Washington, D.C. : Springfield, VA : National Aeronautics and Space Administration ; For sale by the Clearinghouse for Federal Scientific and Technical Information |
| 附註: | Prepared at Langley Research Center. Cover title. "N71-30530." Includes bibliographical references (p. 9). Experimental and analytical study of subsonic longitudinal and lateral aerodynamic characteristics of slender sharp edge 74 deg swept wings. |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151] |
| 附註: | Includes bibliographical references (p. 8). |
| 出版: | Seattle : National Marine Fisheries Service: for sale by the Supt. of Docs., U.S. Govt. Print. Off. |
| 出版: | Seattle : National Marine Fisheries Service : For sale by the Supt. of Docs., U.S. Govt. Print. Off. |
| 出版: | La Jolla, Calif. : Dept. of Commerce, National Oceanic and Atmosheric Administration, National Marine Fisheries Service, Southwest Fisheries Center |
| 出版: | Seattle, Wash. : Washington, D.C. : U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, National Marine Fisheries Service ; For sale by the Supt. of Docs., U.S. G.P.O. |
| ISBN: | 0094-680X |
| 附註: | Description based on: 395, issued May 1976 Some issues have title: NOAA technical report NMFS circular. No. 363 not issued. Issues not published in numerical order. Merged with: NOAA technical report NMFS SSRF, to form: NOAA technical report NMFS. |
| 出版: | Seattle, Wash. : Washington, D.C. : National Marine Fisheries Service ; For sale by the Supt. of Docs., U.S. G.P.O. |
| ISBN: | 0094-4580 |