| 出版: | Seattle : U.S.G.P.O. |
| 出版: | Rockville, Md. : [For sale by the Supt. of Docs., U.S. Govt. Print. Off.] |
| ISBN: | 0092-8917 |
| 附註: | Report year ends June 30 Also issued online. Continued by: Manned undersea science and technology, ISSN 0270-5885, issued by: United States. National Oceanic and Atmospheric Administration. |
| 出版: | Silver Spring, Md. : Environmental Data Service |
| 附註: | This report describes the data available from the Barbados Oceanographic and Meteorological Experiment (BOMEX) conducted in the summer of 1969 |
| 出版: | [Washington] : Naval History Division, Dept. of the Navy; [for sale by the Supt. of Docs., U.S. Govt. Print. Off.] |
| 附註: | First ed. published in 1956 under title: A selected and annotated bibliography on United States naval history, naval biography, naval strategy, and tactics. |
| 出版: | London. : |
| 附註: | Continues in part its Transactions (quarterly) |
| 出版: | [Washington, D.C. : Springfield, Va. : National Oceanic and Atmospheric Administration, Environmental Data Service ; available from National Technical Information Service] |
| ISBN: | 0361-848X |
| 出版: | Washington : U.S. Dept. of the Interior; [for sale by the Supt. of Docs., U.S. Govt. Print. Off.] |
| 出版: | [Washington] : |
| ISBN: | 0092-0002 |
| 附註: | Prepared by the United States. Department of Commerce, National Oceanic and Atmospheric Administration, Environmental Data Service, under contract to the National Science Foundation, Office for the International Decade of Ocean Exploration. Period covered by report for 1970/72 ends July 30; report year for 1972/73- ends. Apr. 30 |
| 出版: | Washington, D.C. : The Committee : For sale by the Supt. of Docs., U.S. G.P.O. |
| ISBN: | 0091-8520 |
| 出版: | Washington, D.C. : For sale by the Supt. of Docs., U.S. G.P.O. |
| 出版: | [Washington : U.S. Environmental Protection Agency; for sale by the Supt. of Docs., U.S. Govt. Print. Off.] |
| 出版: | Seattle, Wash. : Washington, D.C. : NMFS, Scientific Publications Office ; Supt. of Docs., U.S. G.P.O., [distributor] |
| ISBN: | 0090-1830 |
| 附註: | Latest issue consulted: Vol. 59, no. 1 (1997) No longer distributed to depository libraries in a physical format after v. 61, no. 4 (1999) Title from cover Some numbers issued in combined form; vols. for <1990- > lack chronological designation Also issued online UCLA Library - CDL shared resource. UPDscp111205 |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration |
| 附註: | Prepared by Ames Research Center. N72-12980 Includes bibliographical references (p. 8). Static aerodynamic forces and moments were measured to study the effects of Reynolds number and body corner radius on the aerodynamic characteristics of a straight wing space shuttle orbiter at subsonic speeds. A 0.02-scale model was tested at Mach numbers from 0.3 to 0.9 and Reynolds numbers from about 600,000 to 3 million, based on body width. The body alone and the body with its wing and horizontal tail attached were tested at angles of attack from 35 to 75 degrees. The effects of rounding the body corners at the junctures connecting the bottom and sides were investigated for corner radii from 0 to 8.5 percent of the body width. At low subsonic Mach numbers (free stream Mach number approximately equal 0.3) the aerodynamic characteristics are affected significantly by changes in Reynolds number and body corner radius. With increase in Mach number to free stream Mach number = 0.9 the effect of Reynolds number seems to vanish, but a significant effect of body corner radius remains. |
| 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. 36-37). Centrifugal compressor performance was examined analytically to determine optimum geometry for various applications as characterized by specific speed. Seven specific losses were calculated for various combinations of inlet tip-exit diameter ratio, inlet hub-tip diameter ratio, blade exit backsweep, and inlet-tip absolute tangential velocity for solid body prewhirl. The losses considered were inlet guide vane loss, blade loading loss, skin friction loss, recirculation loss, disk friction loss, vaneless diffuser loss, and vaned diffuser loss. Maximum total efficiencies ranged from 0.497 to 0.868 for a specific speed range of 0.257 to 1.346. Curves of rotor exit absolute flow angle, inlet tip-exit diameter ratio, inlet hub-tip diameter ratio, head coefficient and blade exit backsweep are presented over a range of specific speeds for various inducer tip speeds to permit rapid selection of optimum compressor size and shape for a variety of applications. |
| 出版: | Washington, DC : National Aeronautics and Space Administration |
| 附註: | An investigation was conducted to evaluate the effectiveness of an automatic spin-prevention system for current fighter airplanes as a first step in determining the feasibility of such a system. The concept makes use of the components of the conventional flight-control system with the addition of control logic to monitor angle of attack, yaw rate, and normal acceleration. Analytical techniques were used to study the system concept applied to three representative fighter configurations, and model flight tests were employed to evaluate a prototype system on a representative fighter configuration. Emphasis was placed on the development of the control logic required. A discussion of possible implementations of the system concept is presented. Results of the investigation indicated that a relatively simple system (with full control authority) was effective in preventing the developed spins of the fighter configurations considered and that the system design is dependent on the stall and spin characteristics of the particular airplane. |
| 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. 10-11). The landing contact conditions for the HL-10, M2-F2/F3, and the X-24A lifting body vehicles are analyzed statistically for 81 landings. The landing contact parameters analyzed are true airspeed, peak normal acceleration at the center of gravity, roll angle, and roll velocity. Ground measurement parameters analyzed are lateral and longitudinal distance from intended touchdown, lateral distance from touchdown to full stop, and rollout distance. The results are presented in the form of histograms for frequency distributions and cumulative frequency distribution probability curves with a Pearson Type 3 curve fit for extrapolation purposes. |
| 出版: | Washington, DC : National Aeronautics and Space Administration |
| 附註: | "L-8030." "NASA TN D-6574." "February 1972." Includes bibliographical references (p. 8-9). Pitot-pressure profiles and surface pressure measurements have been obtained at four axial stations along the center lines of space shuttle straight-wing and delta-wing orbiters at angles of attack from 20⁰ to approximately 60⁰ and Mach numbers of 20.3 (helium) and 6.8 (air). The results show that the Mach number at the edge of the boundary layer is best predicted by tangent-cone theory up to shock detachment.--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 under171-07-01-01 |
| 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: | The program method is based on a mean-diameter flow analysis. Input design requirements include power or pressure ratio, flow, temperature, pressure, and speed. Turbine designs are generated for any specified number of stages and for any of three types of velocity diagrams (symmetrical, zero exit swirl, or impulse). Exit turning vanes can be included in the design. Program output includes inlet and exit annulus dimensions, exit temperature and pressure, total and static efficiencies, blading angles, and last-stage critical velocity ratios. The report presents the analysis method, a description of input and output with sample cases, and the program listing. |
| 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. 10). The refraction of acoustic waves by a moving medium layer is theoretically treated and the expressions for reflection and transmission coefficients are determined. The moving medium layer velocity is assumed to have a space dependence in one direction. A partitioning of the moving medium layer into constant-velocity sublayers is introduced and the number of sublayers is allowed to increase until the reflection and transmission coefficients converage to their respective values. Numerical results for several sublayer approximations of Poiseuille's flow are presented as functions of the moving layer velocity for several angles of incidence of the acoustic wave. The degenerate case of single constant-velocity layer is also treated, both theoretically and by a numerical analysis. |
| 出版: | Washington, DC : National Aeronautics and Space Administration |
| 附註: | Test data are presented for a 38-cm (15-in.) diameter, 1.28 pressure ratio model VTOL lift fan installed in a two-dimensional wing and tested in a 2.74-by 4.58-meter (9-by 15-ft)V/STOL wind tunnel. Tests were run with and without exit louvers over a wide range of crossflow velocities and wing angle of attack. Tests were also performed with annular-inlet vanes, inlet bell-mouth surface disconuities, and fences to induce fan windmilling. Data are presented on the axial force of the fan assembly and overall wing forces and moments as measured on force balances for various static and crossflow test conditions. Midspan wing surface pressure coefficient data are also given. |
| 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. 16). Noise data were obtained with a model of an externally blown flap of the type that is currently being considered for STOL aircraft. The noise caused by impingement of the jet on the flap is much louder than the nozzle jet noise. It is especially so directly below the wing. The noise level increases as the jet velocity and flap angle are increased. The sound power level increased with the sixth power of velocity. Several physical variations to the STOL model configuration were also tested. Two such variations, a large board and a slotless curved plate wing, had the same power spectra density (Strouhal number curve) as the model. |
| 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. 37-40). The method of integral relations is applied in a one-strip approximation to the perturbation equations governing small motions of an inclined, sharp-edged, flat surface about the mean supersonic steady flow. Algebraic expressions for low reduced-frequency aerodynamics are obtained and a set of ordinary differential equations are obtained for general oscillatory motion. Results are presented for low reduced-frequency aerodynamics and for the variation of the unsteady forces with frequency. The method gives accurate results for the aerodynamic forces at low reduced frequency which are in good agreement with available experimental data. However, for cases in which the aerodynamic forces vary rapidly with frequency, the results are qualitatively correct, but of limited accuracy. Calculations indicate that for a range of inclination angles near shock detachment such that the flow in the shock layer is low supersonic, the aerodynamic forces vary rapidly both with inclination angle and with reduced frequency. |
| 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. 18). Thrust measurements of a hollow cathode mercury discharge were made with a synthetic mica target on a torsion pendulum. Thrust measurements were made for various target angles, tip temperatures, flow rates, keeper discharge powers, and accelerator electrode voltages. The experimental thrust data are compared with theoretical values for the case where no discharge power was employed. |
| 出版: | Washington, D.C. : [Springfield, Va. : National Aeronautics and Space Administration ; For sale by the National Technical Information Service] |
| 附註: | Prepared at Ames Research Center. Cover title. Bibliography: p. 15 Calculations of laminar heat transfer to windward wing and body surfaces of a straight wing MSC orbiter have been made at high angles of attack and with yaw. The predictions of heat transfer made by swept cylinder theory generally agree with measurements in areas free of external flow interference. An optimum elliptic cross section was then determined using swept cylinder theory for an aerodynamically heated windward body surface in radiation equilibrium. |
| 出版: | Washington, DC : National Aeronautics and Space Administration |
| 附註: | Elevon hinge moments were determined from measured surface pressures on a typical delta-wing shuttle orbiter model at selective deflection angles for comparison with the extensive experimental and analytical hinge-moment data previously reported for a simple 75 [degrees] delta wing with a trailing-edge control. The angles of attack were from 0 [degrees] to 55 [degrees] at elevondeflection angles of -45.5 [degrees], O [degrees], and 20°. The results show that the elevon hinge moments on the shuttle orbiter are essentially the same as those measured earlier for the more basic model. Also included is an appendix describing a cubic spline function technique used to determine the hinge moments from elevon surface-pressure measurements. |
| 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. Cover title. Bibliography: p. 10 The phase-change-coating technique was used to study the interference heating to the windward surface of 14 deg, 25 deg, and 50 deg swept wings of an entry vehicle configuration. One wing root of each model was faired to the fuselage with a fillet. Tests were made at Mach 8 at angles of attack of 0 deg, 20 deg, 40 deg, and 60 deg and at free-stream Reynolds numbers based on model length of 0.47 and 1.7 million. Bow shock impingement heating was found to increase in magnitude and affected area with increasing angle of attack until at a higher angle of attack it decreases; this angle of attack is lower for a 50 deg swept wing. Wing root interference heating was found to increase with angle of attack up to 40 deg and then to remain approximately constant. Consequently, wing root interference heating becomes the major type of interference heating at large angles of attack, and this occurs at a lower angle of attack for the highest sweep angle. A wing leading-edge root fillet reduces the peak in wing root interference heating near the leading edge, and increasing Reynolds number increases the level of interference heating. System requirements: Adobe Acrobat Reader. [electronic resource] |
| 出版: | Seattle, WA. : The Administration |
| ISBN: | 0749-8438 |
| 出版: | Washington, D.C. : U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, National Marine Fisheries Service, Market Research and Services Division |
| 出版: | Denver, Colo. : Dept. of the Interior, Fish and Wildlife Service. |
| ISBN: | 0362-0700 |
| 附註: | "Activities in the Divisions of Research for the fiscal year 1975-76." Vols. for 1972 issued by the Bureau of Sport Fisheries and Wildlife, for Jan. 1973/June 1974- by the U.S. Fish and Wildlife Service. Formed by the union of: Wildlife research problems, programs, progress, and: Progress in sport fishery research. |
| 出版: | [S.l : s.n.] |
| 出版: | [Seattle] : National Oceanic and Atmospheric Administration, National Marine Fisheries Service |
| 出版: | Seattle, WA : Washington, D.C. : U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, National Marine Fisheries Service ; for sale by the Superintendent of Documents, U.S. G.P.O. |
| 附註: | "December 1972." |
| 出版: | Seattle, Wash. : U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, National Marine Fisheries Service |
| 出版: | Seattle, WA : Washington, D.C. : U.S. Dept. of Commerce, National Oceanic and Atmoapheric Administration, National Marine Fisheries Service ; for sale by the Superintendent of Documents, U.S. G.P.O. |
| 附註: | "October 1972." |