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Tests of the Northrop XB-62 Missile in the Ames 40- by 80-Foot Wind Tunnel

Description: Memorandum presenting a series of tests made on a full-scale Northrop XB-62 missile to determine the cause of a directional out-of-trim condition which was encountered on the initial missile flight tests. The results indicated that the directional out-of-trim condition was caused by aerodynamic loads induced by engine operation.
Date: September 27, 1954
Creator: Graham, David
Partner: UNT Libraries Government Documents Department

Longitudinal Aerodynamic Characteristics to Large Angles of Attack of a Cruciform Missile Configuration at a Mach Number of 2

Description: Memorandum presenting the lift, pitching-moment, and drag characteristics of a missile configuration with a body of fineness ratio 9.33 and a cruciform triangular wing and tail of aspect ratio 4 at a Mach number of 1.99 and a Reynolds number of 6.0 million. Testing was performed to investigate the effects on the aerodynamic characteristics of roll angle, wing-tail interdigitation, wing deflection, and interference among the components. Results regarding the body-wing-tail combination, body, wing and tail, body-wing and body-tail combinations, and body-wing-tail interference are provided.
Date: December 6, 1954
Creator: Spahr, J. Richard
Partner: UNT Libraries Government Documents Department

An Empirical Equation for the Coefficient of Heat Transfer to a Flat Surface From a Plane Heated-Air Jet Directed Tangentially to the Surface

Description: Note presenting an investigation of the heat transfer to a surface from plane heated-air jets discharged tangentially to the surface to provide heat-transfer relationships required in the design of heated-air jet installations for aircraft windshield fog prevention. Experimental temperature, velocity, and heat-transfer data were obtained by tests in which the initial jet temperature and velocity were varied.
Date: June 1946
Creator: Zerbe, John & Selna, James
Partner: UNT Libraries Government Documents Department

The Effects of Body Vortices and the Wing Shock-Expansion Field on the Pitch-Up Characteristics of Supersonic Airplanes

Description: Memorandum presenting a technique for predicting the influence of body vortices and the wing shock-expansion field on the pitch-up characteristics of supersonic airplanes to supplement the calculative methods for wing vortices which are well known. The method is applied to the prediction of the pitch-up characteristics of four airplanes with high tails, of which one serves as a calculative example.
Date: March 24, 1958
Creator: Nielsen, Jack N.
Partner: UNT Libraries Government Documents Department

Experimental Investigation of the Stability, Control, and Induced Rolling Moments of a Canard Missile Airframe at a Mach Number of 1.7

Description: Memorandum presenting the results of an investigation of the stability, control, and induced rolling moments of a canard missile with cruciform wings of rectangular plan form at Mach number 1.7. All data including the measured hinge moments of the canard control surfaces, the axial forces on the complete missile, and the forces and moments on the various combinations of the missile components are presented in tabular form.
Date: September 23, 1952
Creator: Chubb, Robert S.
Partner: UNT Libraries Government Documents Department

An Analog Study of the Influence of Internal Modifications to a Wing Leading Edge on Its Transient Temperature Rise During Highspeed Flight

Description: Memorandum presenting an investigation made with an electrical heat-flow analog to determine the effect of internal modifications to a wing leading edge on the surface-temperature rise and temperature distribution for conditions of transient aerodynamic heating at high supersonic speeds. Results regarding the leading-edge temperature rise, influence of conduction on leading-edge temperature for skins of uniform thickness, and surface-temperature distribution are provided.
Date: March 17, 1958
Creator: Neel, Carr B.
Partner: UNT Libraries Government Documents Department

The Spanwise Distribution of Lift for Minimum Induced Drag of Wings Having a Given Lift and a Given Bending Moment

Description: "The problem of the minimum induced drag of wings having a given lift and a given span is extended to include cases in which the bending moment to be supported by the wing is also given. The theory is limited to lifting surfaces traveling at subsonic speeds. It is found that the required shape of the downwash distribution can be obtained in an elementary way which is applicable to a variety of such problems" (p. 1).
Date: December 1950
Creator: Jones, Robert T.
Partner: UNT Libraries Government Documents Department

Large-Scale Wind-Tunnel Tests of an Airplane Model With a 45 Degree Sweptback Wing of Aspect Ratio 2.8 With Area Suction Applied to Trailing-Edge Flaps and With Several Wing Leading-Edge Modifications

Description: Memorandum presenting an investigation of an airplane model to determine the effect of area suction trailing-edge flaps and several leading-edge modifications on the aerodynamic characteristics of a 45 degree sweptback wing. The wing had an aspect ratio of 2.8 and a taper ratio of 0.17.
Date: November 2, 1956
Creator: Koenig, David G. & Aoyagi, Kiyoshi
Partner: UNT Libraries Government Documents Department

Evaluation of Some Aerodynamic Controls for a Low Aspect Ratio Missile

Description: "Results of a static stability controls investigation carried out with a very low-aspect-ratio delta-winged missile are presented. Control effectiveness comparisons are made for tail, canard, and nose control configurations with respect to angle of attack, angle of bank, and Mach number. Trim capabilities of the various configurations are also presented" (p. 1).
Date: July 17, 1958
Creator: Winovich, Warren & Higdon, Nancy S.
Partner: UNT Libraries Government Documents Department

The Subsonic Lateral and Longitudinal Static Stability Characteristics Up to Large Angles of Sideslip for a Triangular-Wing Airplane Model Having a Ventral Fin

Description: "Wind-tunnel tests were conducted to determine the effects of a ventral fin on the static characteristics of a triangular-wing airplane model. Data were obtained for angles of sideslip up to 18 degrees at angles of attack of 0, 6, 12, and 18 degrees at Mach numbers from 0.25 to 0.94. The results of the tests indicated that the ventral fin did not produce as much yawing moment per unit of exposed area at any angle of sideslp as the vertical tail" (p. 1).
Date: October 25, 1956
Creator: Buell, Donald A. & Tinling, Bruce E.
Partner: UNT Libraries Government Documents Department

Some Effects of Aileron Deflection on the Static Lateral and Directional Aerodynamic Characteristics of Four Contemporary Airplane Models

Description: Memorandum presenting some effects of aileron deflection on the static lateral and directional aerodynamic characteristics of four airplane models which are representative of aircraft capable of flight at supersonic speeds. The results are presented for subsonic Mach numbers ranging from 0.60 to 0.90 and for supersonic Mach numbers ranging from 1.20 to 1.90. They are limited to the most pertinent aerodynamic effects of ailerons contributing to the lateral and directional characteristics of each airplane type.
Date: July 23, 1957
Creator: Smith, Willard G. & Intrieri, Peter F.
Partner: UNT Libraries Government Documents Department

Aerodynamic Characteristics of Two Rectangular-plan-form, Allmovable Controls in Combination With a Slender Body of Revolution at Mach Numbers From 3.00 to 6.25

Description: Aerodynamic characteristics of rectangular platform, all-movable controls combined with slender body of revolution at Mach 3 to 6.25. The results showed that lift variations with angle of attack were somewhat nonlinear for both control-body combinations tested.
Date: December 28, 1955
Creator: Wong, Thomas J. & Gloria, Hermilo R.
Partner: UNT Libraries Government Documents Department

Aerodynamic Characteristics of a 0.5-Scale Model of the Fairchild XSAM-N-2 Lark Missile at High Subsonic Speeds

Description: "An investigation was conducted to determine the longitudinal- and lateral-stability characteristics of a 0.5-scale model of the Fairchild Lark missile. The model was tested with 0 deg and with 22.5 deg of roll. Three horizontal wings having NACA 16-009, 16-209, and 64A-209 sections were tested. Pressures were measured on both pointed and blunt noses" (p. 1).
Date: September 28, 1949
Creator: Martin, Andrew & Hunter, Harlo A.
Partner: UNT Libraries Government Documents Department

Preliminary Free-Jet Performance of XRJ43-MA-3 Flight-Weight Ram-Jet Engine at Mach Numbers of 2.35, 2.50, and 2.70

Description: From Summary: "The performance of the XRJ43-MA-3 flight-weight ram-jet engine has been investigated in a free-jet facility as part of the development program for the "Bomarc," ram-jet powered, interceptor-type missile. The engine performance was obtained at Mach numbers of 2.35, 2.50, and 2.70, altitudes from 50,000 to 75,000 feet, and Miami hot day and cold day inlet temperatures at an angle of attack of +4 deg. At each flight condition investigated, the engine control set an inner-ring fuel flow which was held constant as outer-ring fuel flow was varied."
Date: November 18, 1955
Creator: McAulay, John E. & Prince, William R.
Partner: UNT Libraries Government Documents Department

An Experimental Investigation of NACA Submerged-Duct Entrances

Description: The results of an investigation of submerged-duct entrances are presented. It is shown that this type of entrance possesses the following characteristics: 1) very high-critical-compressibility speeds throughout the range of high-speed inlet velocity ratios; 2) very low pressure losses for the air entering the duct at all inlet-velocity ratios; and, 3) low external drag. These characteristics are obtained by the proper shaping of the contour of the upstream approach to the submerged inlets and by proper alignment of the duct lip. Design data are presented and the application of these data to a specific high-speed fighter-airplane design is discussed.
Date: May 23, 1945
Creator: Frick, Charles W.; Davis, Wallace F.; Randall, Lauros & Mossman, Emmet A.
Partner: UNT Libraries Government Documents Department

Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18

Description: Memorandum presenting a study of aerodynamic performance and static stability and control at hypersonic speeds. In the first part of the study, the effect of interference lift is investigated by tests of asymmetric models with conical fuselages and arrow plan-form wings. In the second part, the aerodynamic performance and static stability and control characteristics of a hypersonic glider are investigated in somewhat greater detail.
Date: September 17, 1958
Creator: Syvertson, Clarence A.; Gloria, Hermilio R. & Sarabia, Michael F.
Partner: UNT Libraries Government Documents Department

A Comparison of Flight-Measured Carrier- Approach Speeds With Values Predicted by Several Different Criteria for 41 Fighter-Type Airplane Configurations

Description: Memorandum presenting lift and drag characteristics that have been determined in flight in the landing-approach configuration on 41 jet-propelled fighter-type airplane arrangements, including various wing boundary-layer-control installations. Minimum comfortable approach speeds for carrier-type landings were evaluated for these airplanes by four test pilots. Results regarding the presentation of data, methods for the prediction of minimum comfortable approach speed, reasons for limiting approach speed, comparison of flight and predicted approach speeds, and comparison of test pilots' and service pilots' approach speed are provided.
Date: May 8, 1958
Creator: White, Maurice D.; Schlaff, Bernard A. & Drinkwater, Fred J., III
Partner: UNT Libraries Government Documents Department

GaAs Blocked-Impurity-Band Detectors for Far-Infrared Astronomy

Description: High-purity and doped GaAs films have been grown by Liquid-phase epitaxy (LPE) for development of a blocked impurity band (BIB) detector for far-infrared radiation. The film growth process developed has resulted in the capability to grow GaAs with a net active impurity concentration below 1 x 10{sup 13} cm{sup -3}, ideal for the blocking layer of the BIB detector. The growth of n-type LPE GaAs films with donor concentrations below the metal-insulator transition, as required for the absorbing layer of a BIB detector, has been achieved. The control of the donor concentration, however, was found to be insufficient for detector production. The growth by LPE of a high-purity film onto a commercially grown vapor-phase epitaxial (VPE) n-type GaAs doped absorbing layer resulted in a BIB device that showed a significant reduction in the low-temperature dark current compared to the absorbing layer only. Extended optical response was not detected, most likely due to the high compensation of the commercially grown GaAs absorbing layer, which restricts the depletion width of the device.
Date: December 21, 2004
Creator: Cardozo, Benjamin Lewin
Partner: UNT Libraries Government Documents Department

Soot in the stratosphere: The impact of current and HSCT aircraft emissions

Description: One of the trace components of emissions from aircraft engines and other combustion sources are soot particles. These particles are strongly absorbing in the visible and IR spectra, may act as condensation nuclei, and may provide a large surface area for the catalytic promotion of gas-phase chemical reactions. Soot if found throughout the troposphere, even at remote locations, and also in the stratosphere. Present techniques do not allow an unambiguous identification of the sources. This paper discusses the emission of soot from existing and proposed aircraft and the contribution of this soot to concentrations observed in the troposphere and stratosphere. We consider the implications of these emissions for issues in stratospheric physics and chemistry. 11 refs.
Date: August 1, 1991
Creator: Hansen, A.D.A. (Lawrence Berkeley Lab., CA (United States)); Pueschel, R.F. & Snetsinger, K.G. (National Aeronautics and Space Administration, Moffett Field, CA (United States). Ames Research Center)
Partner: UNT Libraries Government Documents Department

Optical constants of solid methane

Description: Methane is the most abundant simple organic molecule in the outer solar system bodies. In addition to being a gaseous constituent of the atmospheres of the Jovian planets and Titan, it is present in the solid form as a constituent of icy surfaces such as those of Triton and Pluto, and as cloud condensate in the atmospheres of Titan, Uranus, and Neptune. It is expected in the liquid form as a constituent of the ocean of Titan. Cometary ices also contain solid methane. The optical constants for both solid and liquid phases of CH{sub 4} for a wide temperature range are needed for radiative transfer calculations, for studies of reflection from surfaces, and for modeling of emission in the far infrared and microwave regions. The astronomically important visual to near infrared measurements of solid methane optical constants are conspicuously absent from the literature. We present preliminary results of the optical constants of solid methane for the 0.4 {mu}m to 2.6 {mu}m region. We report k for both the amorphous and the crystalline (annealed) states. Using our previously measured values of the real part of the refractive index, n, of liquid methane at 110{degree}K (Bull. Am. Phys. Soc.31, 700 (1986)) we compute n for solid methane using the Lorentz-Lorentz relationship. Work is in progress to extend the measurements of optical constants n and k for liquid and solid to both shorter and longer wavelengths, eventually providing a complete optical constants database for condensed CH{sub 4}. 33 refs., 6 figs., 2 tabs.
Date: January 1, 1989
Creator: Khare, B.N.; Thompson, W.R.; Sagan, C. (Cornell Univ., Ithaca, NY (USA). Lab. for Planetary Studies); Arakawa, E.T.; Bruel, C.; Judish, J.P. (Oak Ridge National Lab., TN (USA)) et al.
Partner: UNT Libraries Government Documents Department