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  • LUNAR AND PLANETARY EXPLORATION  (449)
  • AERODYNAMICS  (299)
  • 2005-2009
  • 1980-1984
  • 1970-1974  (748)
  • 1925-1929
  • 1974  (748)
Collection
Keywords
Years
  • 2005-2009
  • 1980-1984
  • 1970-1974  (748)
  • 1925-1929
Year
  • 101
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    A new criterion for modeling systems (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The criterion that is proposed is an expected value of the mean square response error as an alternative to testing a model against new data. Modeling with respect to this new criterion does not change the estimate for a given model format from a maximum likelihood estimate or mean square response error estimate. The new criterion does, however, provide a means of comparing models with different formats and varying complexity. A numerical example is used to illustrate the application of the proposed criteria and the problem of searching for the best model. For all but the most trivial system identification problems, it is shown that a prohibitive number of combinations of terms of the model must be investigated to ensure the final model is best.
    Keywords: AERODYNAMICS
    Type: Parameter Estimation Tech. and Appl. in Aircraft Flight Testing; p 291-313
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  • 102
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    Effects of flight instrumentation errors on the estimation of aircraft stability and control derivatives (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An error analysis program based on an output error estimation method was used to evaluate the effects of sensor and instrumentation errors on the estimation of aircraft stability and control derivatives. A Monte Carlo analysis was performed using simulated flight data for a high performance military aircraft, a large commercial transport, and a small general aviation aircraft for typical cruise flight conditions. The effects of varying the input sequence and combinations of the sensor and instrumentation errors were investigated. The results indicate that both the parameter accuracy and the corresponding measurement trajectory fit error can be significantly affected. Of the error sources considered, instrumentation lags and control measurement errors were found to be most significant.
    Keywords: AERODYNAMICS
    Type: Parameter Estimation Tech. and Appl. in Aircraft Flight Testing; p 261-280
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  • 103
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    Nonlinear parameter identification: Ballistic range experience applicable to flight testing (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The parameter identification scheme being used is a differential correction least squares procedure (Gauss-Newton method). The position, orientation, and derivatives of these quantities with respect to the parameters of interest (i.e., sensitivity coefficients) are determined by digital integration of the equations of motion and the parametric differential equations. The application of this technique to three vastly different sets of data is used to illustrate the versatility of the method and to indicate some of the problems that still remain.
    Keywords: AERODYNAMICS
    Type: Parameter Estimation Tech. and Appl. in Aircraft Flight Testing; p 191-195
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  • 104
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    Feldspar basalts in lunar soil and the nature of the lunar continents (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: It is found that 25% on the Apollo-14 glasses have the same composition as the glasses in two samples taken from the Luna-16 column. The compositions are equivalent to feldspar basalt and anorthosite gabbro, and are similar to the feldspar basalts identified from Surveyor-7 analysis for lunar continents.
    Keywords: LUNAR AND PLANETARY EXPLORATION
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  • 105
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    Spectral behavior of Jupiter near 1 MHz (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Emission from Jupiter has been observed by the IMP-6 spacecraft at 25 frequencies between 425 and 9900 kHz covering the period April 1971 to October 1972. The Jovian bursts were identified through the phase of the observed modulated signal detected from the spinning dipole antenna. Approximately 500 days of data have been scanned for Jupiter emissions with a positive detection of at least 382 events. The static spectral behavior of the emission has been investigated and can be divided naturally into three types. Type one (normal) shows a high correlation with earth-based observations and follows the same spectral behavior. These bursts are seldom detected much below 1 MHz. The second type (md-frequency) occurs near or below 1 MHz and shows low and high-frequency cutoffs. The emission peak is near 900 kHz with a 3 db bandwidth of approximately 450 kHz. A third type consists of a complex combination of the previous types.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Astrophysical Journal; 194; Dec. 15
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  • 106
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    Possible formation of meteoritic chondrules and inclusions in the precollapse Jovian protoplanetary atmosphere (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Icarus; 23; Nov. 197
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  • 107
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    Infrared measurements of Uranus and Neptune (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: New measurements verify that Neptune is brighter than Uranus near 20 microns and show that both planets have increasing brightness temperature with decreasing wavelength between 34 and 22.5 microns. The observations are not compatible with existing models for the atmospheres of these planets.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Astrophysical Journal; 193; Nov. 1
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  • 108
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    Preliminary results of a cosmic dust experiment on the moon (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A three-axis cosmic dust experiment placed on the lunar surface by the Apollo 17 crew is registering impact parameters of cosmic dust and lunar ejecta. A total of 1117 events have been recorded in eight months of data. Preliminary conclusions on the nature of the data include possible evidence of lunar soil transport associated with the terminators. Particle fluxes have been derived for two of the three sensor systems and for specified conditions of exposure.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Geophysical Research Letters; 1; Nov. 197
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  • 109
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    The asteroid belt - Doubts about the particle concentration measured with the asteroid/meteoroid detector on Pioneer 10 (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Science; 186; Nov. 15
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  • 110
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    Hydrodynamic instability of the solar nebula in the presence of a planetary core (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: When a planetary core composed of condensed matter accumulates in the primitive solar nebula, the gas in the nebula becomes gravitationally concentrated as an envelope about the planetary core. An analysis of models of such gaseous envelopes indicates that giant planets (such as Jupiter and Saturn) formed in a massive primitive solar nebula of the type constructed by Cameron and Pine (1973). When the mass of the accumulating planetary core becomes sufficiently great, the surrounding gaseous envelope will become hydrodynamically unstable against collapse onto the planetary core. Much of the surrounding gas also may be compressed onto the core by the background pressure of the gas.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Icarus; 22; Aug. 197
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  • 111
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    Aerodynamics of jet flap and rotating cylinder flap STOL concepts (1974)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: The aerodynamic effectiveness of various propulsive lift concepts to provide for the low speed performance and control required for short takeoff and landing aircraft is discussed. The importance of the interrelationship between the propulsion system and aerodynamic components of the aircraft is stressed. The relative effectiveness of different lift concepts was evaluated through static and wind tunnel tests of various aerodynamic models and propulsion components, simulations of aircraft, and in some cases, flight testing of research aircraft incorporating the concepts under study. Results of large scale tests of lift augmentation devices are presented. The results of flight tests of STOL research aircraft with augmented jet flaps and rotating cylinder flaps are presented to show the steeper approach flight paths at low forward speeds.
    Keywords: AERODYNAMICS
    Type: AGARD V/STOL Aerodyn.; 6 p
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  • 112
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    Elemental abundances in interplanetary dust (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The paper reports on measurements taken of elemental abundances in two interplanetary dust grains. Meteoroidal residue found inside micrometeoritic craters was discovered by optically scanning the 800 sq cm aluminum surface of the S-228 transuranic cosmic-ray experiment exposed to space for 67d during the Skylab-IV mission. Crater analyses for two randomly sampled meteoroids showed a composition consistent with troilite in the 9 micron-minute particle. Chondritic abundances were found in the 30 micron-minute particle. Particles of similar size and chemistry were common in carbonaceous chondrite meteorites. The inferred grain sizes within the 30 micron-minute particle provided evidence for the similarity to carbonaceous chondrites rather than to other meteorite types.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Nature; 252; Dec
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  • 113
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    Depth/diameter relations of fresh lunar craters - Revision from spacecraft data (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The first systematic data from Apollo photogrammetry provide a high standard of accuracy for the depth/diameter relation of fresh lunar craters. Apollo depth-diameter results resemble results obtained by measuring shadows on Lunar Orbiter imagery. The depth-diameter distribution inflects at a crater diameter of 10 to 15 km. Lunar craters less than 15 km across are at least 50% deeper than older, telescopic data indicated, but larger craters are not much deeper. There is no marked depth-diameter difference between fresh upland and postmare craters. The new depth-diameter relation for small lunar craters resembles those of experimental and impact craters on earth.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Geophysical Research Letters; 1; Nov. 197
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  • 114
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    Major, minor and trace element abundances in samples from the Apollo 17 station 7 boulder - Implications for the origin of early lunar crustal rocks (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Earth and Planetary Science Letters; 23; 3, Oc; Oct. 197
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  • 115
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    A generalized-capacity-matrix technique for computing aerodynamic flows (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A numerical generalized-capacity-matrix technique is developed for application to aerodynamic flow computations. This technique allows the very fast direct (noniterative) numerical elliptic solvers to be used in problems with arbitrary internal boundaries and with a wide class of boundary conditions, including numerical application of the Kutta condition on an airfoil without iteration. Accuracy, speed, and usefulness of the technique are demonstrated with linear problems for potential flows over airfoil shapes. The method's main advantages, however, can be exploited within iterative procedures for a variety of complex flow problems governed by systems of equations not necessarily elliptic or linear.
    Keywords: AERODYNAMICS
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  • 116
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    Fast direct numerical solution of the nonhomogeneous Cauchy-Riemann equations (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A fast direct (noniterative) 'Cauchy-Riemann Solver' is developed for solving the finite-difference equations representing systems of first-order elliptic partial differential equations in the form of the nonhomogeneous Cauchy-Riemann equations. The method is second-order accurate and requires approximately the same computer time as a fast cyclic-reduction Poisson solver. The accuracy and efficiency of the direct solver are demonstrated in an application to solving an example problem in aerodynamics: subsonic inviscid flow over a biconvex airfoil. The analytical small-perturbation solution contains singularities, which are captured well by the computational technique. The algorithm is expected to be useful in nonlinear subsonic and transonic aerodynamics.
    Keywords: AERODYNAMICS
    Type: Journal of Computational Physics; 15; May 1974
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  • 117
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    Estimation of longitudinal aerodynamic coefficients and comparison with wind-tunnel values (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Some recent experience at Ames Research Center in the estimation of aerodynamic coefficients for the Lear-Jet and the Augmentor Wing Jet STOL Research Aircraft is reviewed. The coefficients estimated from flight data are compared with values based on large-scale wind-tunnel tests. The results obtained by the regression and quasilinearization identification techniques are also compared. The regression method generally provides the lower standard deviation in the coefficient estimates and provides the better fit to the wind-tunnel values. The addition of nonlinear terms in the aerodynamic equations decreases the difference between the estimated and measured time histories but also increases the standard deviation in the estimated coefficient values.
    Keywords: AERODYNAMICS
    Type: Parameter Estimation Tech. and Appl. in Aircraft Flight Testing; p 125-148
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  • 118
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    Vortex-induced heating to cone flaps at Mach 6 (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Discussion of the local heating effect on the lee-side control flaps of supersonic configurations due to the interaction between vortices and leeward control surfaces at an angle of attack. Considerations are given for an appropriate positioning of control flaps to alleviate such interactions and the resulting thermal effect. Tests are carried out on a sharp right circular cone with two types of flap configurations in a study of oil flow patterns about the cone at selected angles of attack. Splitting of flaps and moving them to positions away from the symmetry plane did reduce the heating but also reduced the average flap pressure and increased flow complexity.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 11; Mar. 197
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  • 119
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    An improved static probe design (1974)
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    Publication Date: 2011-08-16
    Description: A new static probe design is described in which the static holes are located much closer to the tip than in conventional probes. The new probe shows promise for use in some situations where conventional probes become highly inaccurate. An additional advantage of the new design is that, when used in static pressure survey rakes, the probes can be located much closer together than in conventional designs and still ensure that disturbances from neighboring probe tips do not affect the static readings.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 12; Apr. 197
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  • 120
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    Vortex-induced heating to a cone-cylinder body at Mach 6 (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Presented data on vortex-induced heating in a cone-cylinder body at Mach 6 show that the most severe heating need not occur as a result of the interaction of the primary vortices with the lee surface, even though this interaction produces a large, well-defined featherline oil smear. It is pointed out that the severity of vortex-induced heating is extremely sensitive to Reynolds number and geometry and that there exists a 'threshold Reynolds number' below which vortex-induced heating decreases abruptly.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 11; Feb. 197
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  • 121
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    Simulation of real-gas effects for Mars entry (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The changes in aerodynamic characteristics due to real-gas effects associated with high speed flight (characterized by large shock density ratios) are primarily the result of changes in surface pressures acting on the forebody. The surface pressures are affected by a change in shock density ratio (real-gas effects) in two ways. First, the level of pressure at the stagnation point relative to freestream dynamic pressure is changed, and second, the distribution of surface pressure relative to stagnation-point pressure is changed. The density-ratio effect on the stagnation point pressure level can be estimated by considering the flow of a perfect gas about a blunt body.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 11; Jan. 197
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  • 122
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    V/STOL aerodynamics: A review of the technology (1974)
    In:  CASI
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    Publication Date: 2012-05-22
    Description: An analysis of the development and technological applications of V/STOL aircraft is presented. The use of V/STOL aircraft to overcome the limitations of conventional aircraft is discussed. The aspects of V/STOL aircraft which are considered are: (1) economic penalties of propulsive lift, (2) advantages of propulsive lift, (3) potential improvements in V/STOL aircraft, (4) the aerodynamics of V/STOL aircraft, and (5) proposals for additional research in V/STOL development.
    Keywords: AERODYNAMICS
    Type: AGARD V/STOL Aerodyn.; 13 p
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  • 123
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    Pioneer 10 Jupiter atmospheric definition results: A summary (1974)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The various entry probes for measuring outer planetary atmospheric compositions are discussed. Considered are chemical components and physical accumulation processes observable by spectroscopic studies, as well as pressure gauges, temperature gauges, accelerometers, nephelometers, and visible and infrared sensors for determining abundances.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Dynatrend, Inc. Proc. of Outer Planet Probe Technol. Workshop, Sect. 1 through 11; 23 p
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  • 124
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    Compositional measurements by outer planet entry probe (1974)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Recommended is a very simple probe on the Pioneer 8 mission with ESRO which does nothing more than enter the Jupiter atmosphere to make temperature and pressure measurements.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Dynatrend, Inc. Proc. of Outer Planet Probe Technol. Workshop, Sect. 1 through 11; 11 p
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  • 125
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    New IR observations of Titan and potential of in-situ atmospheric analysis of the outer planets (1974)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: Ground based telescopic observations of Titan and outer planet atmospheres are evaluated for their abundances and an effort is made to deduce the various hydrogen-to-carbon ratios. Jupiter and Saturn atmospheres seem to have roughly solar abundances as far as hydrogen and methane are concerned; for Uranus, Titan and Neptune these ratios are way down.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Dynatrend, Inc. Proc. of Outer Planet Probe Technol. Workshop, Sect. 1 through 11; 23 p
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  • 126
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    A general purpose stabilised balloon platform (1974)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The development of a three axis stabilized balloon platform capable of being operated in three modes of increasing accuracy is discussed. The system relies on angular motion sensing for primary feedback with linear accelerometers, magnetometers, and a star sensor for positional information. When under primary control the system will acquire and stabilize on any accessible part of the celestial sphere. A video verification system is included to provide pointing confirmation. Under improved accuracy control, the star sensor is used to lock onto a target star.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Res. Center Telescope Systems for Balloon-Borne Res.; p 284-293
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  • 127
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    Air Force Cambridge Research Laboratories balloon operations (1974)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The establishment and functions of the AFCRL balloon operations facility are discussed. The types of research work conducted by the facility are defined. The facilities which support the balloon programs are described. The free balloon and tethered balloon capabilities are analyzed.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Res. Center Telescope Systems for Balloon-Borne Res.; p 160-164
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  • 128
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    Balloon platform for extended-life astronomy research (1974)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: A configuration has been developed for a long-life balloon platform to carry pointing telescopes weighing as much as 80 pounds (36 kg) to point at selected celestial targets. A platform of this configuration weighs about 375 pounds (170 kg) gross and can be suspended from a high altitude super pressure balloon for a lifetime of several months. The balloon platform contains a solar array and storage batteries for electrical power, up and down link communications equipment, and navigational and attitude control systems for orienting the scientific instrument. A biaxial controller maintains the telescope attitude in response to look-angle data stored in an on-board computer memory which is updated periodically by ground command. Gimbal angles are computed by using location data derived by an on-board navigational receiver.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Res. Center Telescope Systems for Balloon-Borne Res.; p 136-144
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  • 129
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    An orientable, stabilized balloon-borne gondola for around-the-world flights (1974)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: A system capable of pointing a balloon-borne telescope at selected celestial objects to an accuracy of approximately 10 arc minutes for an extended period (weeks to months) without reliance on telemetry is described. A unique combination of a sun/star tracker, an on-board computer, and a gyrocompass is utilized for navigation, source acquisition and tracking, and data compression and recording. The possibilities for intelligent activities by the computer are also discussed.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Res. Center Telescope Systems for Balloon-Borne Res.; p 71-80
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  • 130
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    Experimental and analytical studies in tilt-rotor aeroelasticity (1974)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An overview of an experimental and analytical research program underway for studying the aeroelastic and dynamic characteristics of tilt-rotor VTOL aircraft is presented. Selected results from several investigations of scaled models in the transonic dynamics tunnel, as well as some results from a test of a flight-worthy proprotor in the full-scale wind tunnel are shown and discussed with a view toward delineating various aspects of dynamic behavior peculiar to proprotor aircraft. Included are such items as proprotor/pylon stability, whirl flutter, gust response, and blade flapping. Theoretical predictions are shown to be in agreement with the measured stability and response behavior.
    Keywords: AERODYNAMICS
    Type: Its Rotorcraft Dyn.; p 171-184
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  • 131
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    Theory and comparison with tests of two full-scale proprotors (1974)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A nine degrees-of-freedom theoretical model was developed for investigations of the dynamics of a proprotor operating in high inflow axial flight on a cantilever wing. The theory is described, and the results of the analysis are presented for two proprotor configurations: a gimballed, stiff-inplane rotor, and a hingeless, soft-inplane rotor. The influence of various elements of the theory are discussed, including the modeling used for the blade and wing aerodynamics, and the influence of the rotor lag degree of freedom. The results from full-scale tests of the two proprotors are presented and compared with the theoretical results.
    Keywords: AERODYNAMICS
    Type: Its Rotorcraft Dyn.; p 159-169
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  • 132
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    Metal-olivine associations and Ni-Co contents in two Apollo 12 mare basalts (1974)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Olivine crystals in mare basalts 12004,8 and 12022,12 are normally zoned with Cr-poor rims. The Ni content of rare 2- to 10-micron metal inclusions in olivine decreases markedly as Fe/Mg in their immediate olivine hosts increases. Each metal grain appears to have been enclosed by late olivine almost immediately after it crystallized. The fractionation trend for the olivine and metal contrasts with the subsolidus equilibration trend for pallasites. For the basalts, not even local equilibrium of Fe, Ni and Co at metal/olivine interfaces can be detected by microprobe. Ni and Co concentrations range from about 300 ppm in olivine cores to about 70 ppm in rims. The limits of detection, at 95% confidence, are 36 ppm (Ni) and 25 ppm (Co). The distribution of Ni and Co in olivine, like that of Mg and Cr, records the depletion of these elements in the melt.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Earth and Planetary Science Letters; 24; 1; Nov. 197
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  • 133
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    Ferroan anorthosite - A widespread and distinctive lunar rock type (1974)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Eight of eleven Apollo 16 rake-sample anorthosites are very similar to each other, to hand-specimen Apollo 16 anorthosites, and to Apollo 15 anorthosites. They have feldspar An-96.6, both high- and low-Ca pyroxene with a restricted range of (low-magnesium) composition, minor olivine, traces of ilmenite and chromite, and originally coarse-grained, but now cataclastic texture. Such ferroan anorthosite is evidently a coherent, distinctive and widespread lunar rock type of cumulate origin which may not necessarily be very closely related genetically to other highland rock types.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Earth and Planetary Science Letters; 24; 1; Nov. 197
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  • 134
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    Comparison of the experimental aerodynamic characteristics of theoretically and experimentally designed supercritical airfoils (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A lifting airfoil theoretically designed for shockless supercritical flow utilizing a complex hodograph method has been evaluated in the Langley 8-foot transonic pressure tunnel at design and off-design conditions. The experimental results are presented and compared with those of an experimentally designed supercritical airfoil which were obtained in the same tunnel.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3082 , L-9548 , NAS 1.15:X-3082
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    A study of the nonlinear aerodynamics of bodies in nonplanar motion (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Concepts from the theory of functionals are used to develop nonlinear formulations of the aerodynamic force and moment systems acting on bodies in large-amplitude, arbitrary motions. The analysis, which proceeds formally once the functional dependence of the aerodynamic reactions upon the motion variables is established, ensures the inclusion, within the resulting formulation, of pertinent aerodynamic terms that normally are excluded in the classical treatment. Applied to the large-amplitude, slowly varying, nonplanar motion of a body, the formulation suggests that the aerodynamic moment can be compounded of the moments acting on the body in four basic motions: steady angle of attack, pitch oscillations, either roll or yaw oscillations, and coning motion. Coning, where the nose of the body describes a circle around the velocity vector, characterizes the nonplanar nature of the general motion.
    Keywords: AERODYNAMICS
    Type: NASA-TR-R-421 , A-5057
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  • 136
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    Lunar paleointensity from three Apollo 15 crystalline rocks using an A.R.M. method (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: An anhysteretic remanent magnetization method described by Banerjee and Mellema (1974) is used in the lunar paleointensity studies reported. The range of the difference in the paleointensity values obtained by the new method is not quite as great as the range of differences ordinarily found in values determined with the conventional method reported by Thellier and Thellier (1959). The results of the investigation show that the three Apollo 15 rocks studied acquired their natural remanent magnetization in a finite-sized magnetic field which was two or three orders of magnitude greater than the present ambient interplanetary field at the moon.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Earth and Planetary Science Letters; 23; 2, Se; Sept
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  • 137
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    Simple methods for determining the virtual origin of turbulent boundary layers in hypersonic flow on sharp-edged flat plates (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Two methods for determining the virtual origin of turbulent boundary layers in hypersonic flow are evaluated. The results of the analyses are restricted to wind-tunnel models having sharp-edged surfaces with zero or small pressure gradients. Virtual origin and skin friction estimates from these two methods are compared with values from a base method for which the virtual origin is calculated from the measured momentum thickness at a station downstream of boundary layer transition.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 74-APM-V
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  • 138
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    Substorms on Mercury? (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Qualitative similarities between some of the variations in the Mercury encounter data and variations in the corresponding regions of the earth's magnetosphere during substorms are pointed out. The Mariner 10 data on Mercury show a strong interaction between the solar wind and the plant similar to a scaled down version of that for the earth's magnetosphere. Some of the features observed in the night side Mercury magnetosphere suggest time dependent processes occurring there.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: NASA-CR-143509 , CSR-TR-75-1
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  • 139
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    Phase chemistry of Apollo 14 soil sample 14259 (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: 0.26 gm of Apollo 14 soil sample 14259 has been investigated by optical, X-ray diffraction and electron microprobe techniques. The mineral abundances in the soil are 45% plagioclase, 41% pyroxene, 7% olivine, 3% oxides, 2% K-feldspar, 1% nickel-iron and less than 1% troilite. Eleven percent of the glasses have compositions like those of mare basalts or mare soils and are believed to be mare-derived. Eighty-six percent of the glasses are equivalent in composition to basalts that have higher Al, and lower Ca/Al and Fe/Mg ratios than mare basalts. The most abundant compositional type is named Fra Mauro basaltic glass and is subdivided into three related types. The other major glass type in the soil corresponds in composition to anorthositic gabbro.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Modern Geology; 5; May 1974
    Format: text
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  • 140
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    Magnetism in meteorites (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: An overview of this subject is presented. The paper includes a glossary of magnetism terminology and a discussion of magnetic techniques used in meteorite research. These techniques comprise thermomagnetic analysis, alternating field demagnetization, thermal demagnetization, magnetic anisotropy, low-temperature cycling, and coercive forces, with emphasis on the first method. Limitations on the validity of paleointensity determinations are also discussed.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Meteoritics; 9; Dec. 31
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  • 141
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    Mercury's infrared phase effect (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Predictions based on a smooth spherical blackbody do not agree with the observed brightness temperatures of the planet Mercury. The curves of measured effective brightness temperature as a function of phase angle are more steep than and reach lower values near absolute values of i of about 180 deg and higher values near absolute values of i of about 0 deg than those of a smooth sphere. Phase curves of the moon have also been obtained which confirm earlier measurements. The distribution of Mercury's emitted energy in wavelength is dependent upon phase angle, changing from clearly identifiable thermal spectra for absolute values of i less than 150 deg to a superposition of thermal emission at several color temperatures for greater phase angles. No significant variation of infrared brightness temperature with subearth longitude intensity was found. These results provide further evidence that the surfaces of Mercury and the moon are similar and that the top layer of the planetary terrain is rough on a millimeter scale.-
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Astronomical Journal; 79; Dec. 197
    Format: text
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  • 142
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    Planetary accretions in jet streams (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The problem of planetary accretion in a jet stream is studied using the model developed by Alfven and Arrhenius. We find that there are basically three types of planetary accretion, corresponding to cases where the characteristic time of the occurrence of catastrophic accretion is less than, equal to, or greater than the time-scale of mass injection to the planetary system (300 m.y.). These different time scales of accretion are found to be closely related to the primordial thermal profiles and equatorial inclinations of the planets. Finally, Venus' retrograde rotational spin is shown to be a possible result of accretion process in a jet stream.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Astrophysics and Space Science; 31; Nov. 197
    Format: text
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  • 143
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    Forward slanted slot throat stability bypass to increase the stable airflow range of a Mach 2.5 inlet with 60 percent internal contraction (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of an experimental investigation to increase the stable airflow operating range of a supersonic mixed-compression inlet are presented. Two forward-slanted slot stability-bypass entrance configurations were tested. In terms of diffuser-exit corrected airflow, a large inlet stable airflow range of 18.5 percent was obtained with the superior configuration if a constant pressure was maintained in the bypass plenum. Limited unstart angle-of-attack data are presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2973 , E-7706
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  • 144
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    Effect of screen-induced total-pressure distortion on axial-flow compressor stability (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was made to determine the effects of screen-induced total-pressure distortions on two J85-GE-13 turbojet engines. Results were compared to those from a previous program run with a third engine. All compressors were found to be sensitive to a critical angle of circumferential distortion equal to 60 deg., and they all adhered closely to the parallel compressor model. The sensitivity of compressor exit pressure to virtually any type of distortion pattern can be determined by defining stall lines for undistorted, hub radial distorted, and tip radial distorted inflows. The effect of multiple sectors of circumferential distortion is defined.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3017 , E-7792
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  • 145
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    Combined Quadrupole-dipole Model for Inlet Flow Distortion Noise from a Subsonic Fan (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A combined quadrupole-dipole model has been developed for the noise generated by inlet flow distortion in a subsonic fan. A formula is derived for the total upstream-radiated acoustic power in each tone as a function of the design parameters of the fan and the properties of the inlet flow distortion. Numerical results are obtained for values of the parameters corresponding to various quiet fans. The analysis is compared with noise measurements taken on a 51-cm (20-in.) diameter research fan as well as with those taken on a number of full-scale fan stages. Fairly good agreement was obtained. It should therefore be possible to use this model to study the noise-reduction potential of the various fan design parameters.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7676 , E-7881
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  • 146
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    Low speed aerodynamic characteristics of NACA 6716 and NACA 4416 airfoils with 35 percent-chord single-slotted flaps (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted in a low-turbulence pressure tunnel to determine the two-dimensional lift and pitching-moment characteristics of an NACA 6716 and an NACA 4416 airfoil with 35-percent-chord single-slotted flaps. Both models were tested with flaps deflected from 0 deg to 45 deg, at angles of attack from minus 6 deg to several degrees past stall, at Reynolds numbers from 3.0 million to 13.8 million, and primarily at a Mach number of 0.23. Tests were also made to determine the effect of several slot entry shapes on performance.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2623 , L-8410
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  • 147
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    Flight Reynolds number effects on a contoured boattail nozzle at subsonic speeds (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A contoured boattail nozzle typical of those used on a twin-engine fighter was tested on an underwing nacelle mounted on an F-106B aircraft. The gas generator was a J85-GE-13 turbojet engine. The effects of Reynolds number, Mach number, and angle of attack on boattail drag and boattail pressure profiles were investigated. Increasing Reynolds number caused a slight reduction in boattail drag at both Mach 0.7 and 0.9. The nozzle had relatively low boattail drag even though the flow was separated over a large portion of the boattail.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3053 , E-7818
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  • 148
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    An Analytical Investigation of Wing-Jet Interaction (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic interaction between the wing and an inviscid jet with Mach number nonuniformity is formulated by using a two-vortex-sheet model for the jet. One of the vortex sheets accounts for the induced jet flow and the other the induced outer flow. No additional source distribution is needed for the jet at an angle of attack. The above problem is solved by satisfying the jet and wing tangency and the jet pressure-continuity conditions and using a quasi vortex lattice method for computing the induced flow field. The latter method is derived through theoretical consideration by properly accounting for singularities present in the equations and possesses the same simplicity and generality as the conventional vortex lattice method but has a better rate of numerical convergence. The resulting system of algebraic equations is solved by Purcell's vector method. The numerical formulation is first applied to the wing-slipstream interaction problem. Results for one centered-jet configuration are compared with those predicted by some existing theories.
    Keywords: AERODYNAMICS
    Type: NASA-CR-138140 , CRINC-FRL-74-001
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  • 149
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    Flutter suppression and gust alleviation using active controls (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of active controls on the suppression of flutter and gust alleviation of two different types of subsonic aircraft (the Arava, twin turboprop STOL transport, and the Westwind twin-jet business transport) are investigated. The active controls are introduced in pairs which include, in any chosen wing strip, a leading-edge (LE) control and a trailing-edge (TE) control. Each control surface is allowed to be driven by a combined linear-rotational sensor system, located on the activated strip. The control law, which translates the sensor signals into control surface rotations, is based on the concept of aerodynamic energy. The results indicate the extreme effectiveness of the active systems in controlling flutter. A single system spanning 10% of the wing semispan made the Arava flutter-free, and a similar active system, for the Westwind aircraft, yielded a reduction of 75% in the maximum bending moment of the wing and a reduction of 90% in the acceleration of the cg of the aircraft. Results for simultaneous activation of several LE - TE systems are presented. Further work needed to bring the investigation to completion is also discussed.
    Keywords: AERODYNAMICS
    Type: NASA-CR-138658 , TAE-198
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  • 150
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    The passage of an infinite swept airfoil through an oblique gust (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An approximate solution is reported for the unsteady aerodynamic response of an infinite swept wing encountering a vertical oblique gust in a compressible stream. The approximate expressions are of closed form and do not require excessive computer storage or computation time, and further, they are in good agreement with the results of exact theory. This analysis is used to predict the unsteady aerodynamic response of a helicopter rotor blade encountering the trailing vortex from a previous blade. Significant effects of three dimensionality and compressibility are evident in the results obtained. In addition, an approximate solution for the unsteady aerodynamic forces associated with the pitching or plunging motion of a two dimensional airfoil in a subsonic stream is presented. The mathematical form of this solution approaches the incompressible solution as the Mach number vanishes, the linear transonic solution as the Mach number approaches one, and the solution predicted by piston theory as the reduced frequency becomes large.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2395
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  • 151
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    Wind tunnel blockage and support interference effects on winged-body models at Mach numbers from 0.6 to 1.0 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Three sting-mounted winged-body models with tunnel blockages of 0.1, 1.0, and 2.0 percent were tested in the Lewis Research Center's 8- by 6- Foot Supersonic Wind Tunnel. Fuselage pressures were obtained over a Mach number range of 0.6 to 1.0 at angles of attack from 0 deg to 4 deg. Two other types of model support were investigated, which included simulated wing-tip and fuselage support-strut mountings. The effects of tunnel porosity and sidewall geometry were also investigated. Model blockage effects were small up to M sub 0 = 0.95. At higher speeds the major blockage effect observed was a displacement of the local transonic terminal shocks on the model. The effects of the wing-tip type of model support were small up to M sub 0 = 0.95, but disturbances were observed on the fuselage at higher speeds. Changes in local tunnel porosity were effective in reducing the disturbances up to M sub 0 = 0.975, but a change in sidewall geometry was not.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3011 , E-7596
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  • 152
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    An experimental study of the validity of the heat-field concept for sonic-boom alleviation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental program was carried out in the NASA-Langley 4 ft x 4 ft supersonic pressure tunnel to investigate the validity of the heat-field concept for sonic boom alleviation. The concept involves heating the flow about a supersonic aircraft in such a manner as to obtain an increase in effective aircraft length and yield an effective aircraft shape that will result in a shock-free pressure signature on the ground. First, a basic body-of-revolution representing an SST configuration with its lift equivalence in volume was tested to provide a baseline pressure signature. Second, a model having a 5/2-power area distribution which, according to theory, should yield a linear pressure rise with no front shock wave was tested. Third, the concept of providing the 5/2-power area distribution by using an off-axis slender fin below the basic body was investigated. Then a substantial portion (approximately 40 percent) of the solid fin was replaced by a heat field generated by passing heated nitrogen through the rear of the fin.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2381 , ATR-74(7218)-1
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  • 153
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    Estimation of deviation angle for axial-flow compressor blade sections using inviscid-flow solutions (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Development of a method of estimating deviation angles by analytical procedures was begun. Solutions for inviscid, irrotational flow in the blade-to-blade plane were obtained with a finite-difference calculation method. Deviation angles for a plane cascade with a rounded trailing edge were estimated by using the inviscid-flow solutions and three trailing-edge hypotheses. The estimated deviation angles were compared with existing experimental data over a range of incidence angles at inlet flow angles of 30 deg and 60 deg. The results indicate that deviation angles can be estimated accurately (within 1 deg) by using one of the three trailing-edge hypotheses, but only when pressure losses are low. A new trailing-edge hypotheses is presented which is suitable (for the cascade considered) for both low- and high-loss operating points.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7549 , E-7453
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  • 154
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    Normal loads program for aerodynamic lifting surface theory (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A description of and users manual are presented for a U.S.A. FORTRAN 4 computer program which evaluates spanwise and chordwise loading distributions, lift coefficient, pitching moment coefficient, and other stability derivatives for thin wings in linearized, steady, subsonic flow. The program is based on a kernel function method lifting surface theory and is applicable to a large class of planforms including asymmetrical ones and ones with mixed straight and curved edges.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62326
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  • 155
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    Cold-air study of the effect on turbine stator blade aerodynamic performance of coolant ejection from various trailing-edge slot geometries. 1: Experimental results (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Trailing-edge slot configurations were investigated in a two-dimensional cascade of turbine stator blades. The trailing-edge slots were incorporated into blades with round trailing edges. The five blade configurations investigated included blades with two different trailing-edge thicknesses and four different slot widths. The results of the investigation showed that there was, in general, a significant increase in primary-air efficiency due to the coolant flow, the increase varying with slot configuration. For the five configurations tested, the average percent change in primary-air efficiency per percent coolant flow varied almost linearly from zero to about 1.4 percent over a range of coolant- to primary-air exit-velocity ratios between 0 and 1.2. However, for different configurations there was considerable deviation from the average values in the lower range of exit velocity ratios.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3000 , E-7743
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  • 156
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    A rapid numerical solution to subsonic flow over planar and axisymmetric profiles at an angle of attack of 0 deg (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A numerical solution is presented for the incompressible flow over thin planar and axisymmetric profiles at an angle of attack of 0 degrees. The method uses a finite-difference field solution to the governing equation with a Gauss-Seidel successive overrelaxation scheme. However, the use of a simple Cartesian grid system restricts this method to slender profiles. Results are presented for a cambered airfoil, airfoil in wall effect (two-dimensional flowthrough inlet), body of revolution, and flowthrough nacelle. A computer program is presented which can be used for any of the previously mentioned cases with simple input changes. Results for compressible flow are available with the use of the appropriate two-dimensional or axisymmetric compressibility corrections. Computational time for a typical field calculation of 3000 grid points and 200 cycles through the field is less than 1 minute with less than 50,000 octal storage on the Control Data Corporation 6600 computing system.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7410 , L-8904
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  • 157
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    Numerical calculations of velocity and pressure distribution around oscillating airfoils (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analytical procedure based on the Navier-Stokes equations was developed for analyzing and representing properties of unsteady viscous flow around oscillating obstacles. A variational formulation of the vorticity transport equation was discretized in finite element form and integrated numerically. At each time step of the numerical integration, the velocity field around the obstacle was determined for the instantaneous vorticity distribution from the finite element solution of Poisson's equation. The time-dependent boundary conditions around the oscillating obstacle were introduced as external constraints, using the Lagrangian Multiplier Technique, at each time step of the numerical integration. The procedure was then applied for determining pressures around obstacles oscillating in unsteady flow. The obtained results for a cylinder and an airfoil were illustrated in the form of streamlines and vorticity and pressure distributions.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2368
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  • 158
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    Equation solving program for aerodynamic lifting surface theory (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A description of and user's manual are presented for one of a group of FORTRAN programs which, together, can be used for the analysis and design of wings in steady, subsonic flow according to a kernel function method lifting surface theory. This particular program is the one which solves the sets of simultaneous, linear, algebraic equations arising from the thin wing analysis. This program has the capability of striking out rows and columns of the aerodynamic influence matrix and rows of the associated boundary condition vectors (right hand sides). This capability significantly enhances the effectiveness of the kernel function method of lifting surface theory because studies of the convergence of solutions with the number of control points can be done with the calculation of only a single influence matrix.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62325
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  • 159
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    Research turbine for high temperature core engine application. 1: Cold-airoverall performance of solid scaled turbine (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A solid, half-scale model of a 50.8-cm (20-in) research turbine designed for a high temperature core engine application was investigated over a range of speeds and pressure ratios. The results of this test are presented. The effect of rotor blade twist was also investigated. At the design equivalent speed and specific work output, the total efficiency of the turbine with untwisted rotor blades was 87.1 percent; at the same pressure ratio the efficiency of the turbine with twisted rotor blades was 88.0 percent.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7557 , E-7592
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  • 160
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    Fixed-base simulation study of decoupled controls during approach and landing of a STOL transport airplane (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A fixed-base visual simulation study has been conducted to evaluate the use of decoupled controls as a means for reducing pilot workload during approach and landing of an externally blown jet-flap short take-off and landing (STOL) transport. All six rigid-body degrees of freedom were employed with the aerodynamic characteristics based on wind-tunnel data. The primary piloting task was to use a flight director to capture and maintain a two-segment glide slope, with a closed-circuit television display of a STOL airport used during simulations of the flare and landing. The decoupled longitudinal controls used constant prefilter and feedback gains to provide steady-state decoupling of flight-path angle, pitch angle, and forward velocity. The pilots were enthusiastic about the decoupled longitudinal controls but believed the decoupled concept offered no significant advantage over conventional controls in the lateral mode.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7363 , L-8825
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  • 161
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    Venus and Mercury Encounters (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Mariner 10 observations of Venus, Mercury, Comet Kohoutek, and other interplanetary objects are reported. Data cover planetary atmospheres, temperature, and surface detail.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: NASA-CR-142829 , ISSUE-4
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  • 162
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    Mission to the Inner Planets (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Mariner 10 mission objectives to investigate Mercury and Venus are discussed along with the spacecraft's design and its flight path. Scientific instruments onboard the spacecraft are also discribed.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: NASA-CR-142828 , ISSUE-3
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  • 163
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    Venus and Mercury as Planets (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A general evolutionary history of the solar planetary system is given. The previously observed characteristics of Venus and Mercury (i.e. length of day, solar orbit, temperature) are discussed. The role of the Mariner 10 space probe in gathering scientific information on the two planets is briefly described.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: NASA-CR-142826 , ISSUE-2
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  • 164
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    Innermost Planets of the Solar System (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The appearance and characteristics of Mercury and Venus as evening and morning stars are discussed. Inferior and superior conjunction are defined. The motions, phases, and planetary dynamics of the two planets are compared with those of the earth and moon.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: NASA-CR-142827 , ISSUE-1
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  • 165
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    Fast response vanes for sensing flow patterns in helicopter rotor environment (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Wind tunnel experiments were conducted on four small-scale flow-direction vanes for the determination of aerodynamic response. The tests were further extended to include a standard sized low-inertia vane currently employed in aircraft flight testing. The four test vanes had different aspect ratios and were about 35 percent of the surface area of the standard vane. The test results indicate satisfactory damping and frequency response for all vanes tested and compare favorably with the standard design.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132545
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  • 166
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    Data users note: Apollo 17 lunar photography (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The availability of Apollo 17 pictorial data is announced as an aid to the selection of the photographs for study. Brief descriptions are presented of the Apollo 17 flight, and the photographic equipment used during the flight. The following descriptions are also included: service module photography, command module photography, and lunar surface photography.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: NASA-TM-X-72535 , NSSDC-74-08
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  • 167
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    Correlation of thermomagnetic behavior of carbonaceous chondrites with chemical petrographic classification (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Some degree of correlation was noted between the thermomagnetic behavior of the carbonaceous chondrites and the chemical-petrographic classification scheme of Van Schmus and Hayes.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: NASA-CR-141060
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  • 168
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    Thermomagnetic analysis of meterorites. 4: Ureilites (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Samples of all available ureilites have been analyzed thermomagnetically. For three of the six (Dyalpur, Goalpara and Havero) evidence was found for only low-nickel metallic-iron as the magnetic component and the (saturation magnetization vs, temperature) curves were reversible. In the Novo Urei ureilite, magnetite in addition to low-nickel metallic-iron was indicated and again the Js-T curve was reversible. For the two badly weathered ureilites, Dingo Pup Donga and North Haig, indication was also found that both initial magnetite and low-nickel metallic-iron were present. However, the Js-T curves were somewhat irreversible and the final saturation magnetization was 20% and 50% greater than initially for North Haig and Dingo Pup Donga, respectively. This behavior is interpreted to be the result of magnetite production from a secondary iron oxide during the experiment.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: NASA-CR-141143
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  • 169
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    Radiation-gas dynamic shock layer coupling (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The present work considers theoretically the problem of radiation losses on the shock layer during hypersonic flight, and in particular, results are presented for the stagnation line shock layer for a wide variety of flight conditions, providing a new overview of radiation-gas dynamic coupling within a shock layer. The present results are based on a previous model (Engel, Farmer, et al., 1973) of a viscous radiating shock layer. An important result is that the radiation-gas dynamic coupling effect on the radiative heating can be related to a single parameter, namely, the radiative cooling parameter, whereas the effect on the shock layer thickness is not a simple function of this parameter.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 12; Aug. 197
    Format: text
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  • 170
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    Mach disk from underexpanded axisymmetric nozzle flow (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The flowfield associated with the underexpanded axisymmetric nozzle freejet flow including the appearance of a Mach disk has been studied. It is shown that the location and size of the Mach disk are governed by the appearance of a triple-point shock configuration and the condition that the central core flow will reach a state of 'choking at a throat'. It is recognized that coalescence of waves requires special attention and the reflected wave, as well as the vorticity generated from these wave interactions, have to be taken accurately into account. The theoretical results obtained agreed well with the experimental data.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 12; Aug. 197
    Format: text
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  • 171
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    Calculation of compressible turbulent free shear layers (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Rudy and Bushnell's (1972) mixing length theory for the prediction of mean velocity fields in turbulent shear layers is extended to include supersonic free turbulent mixing. The normal momentum equation is coupled with the conventional equations of motion and is solved iteratively. Results show that transverse static pressure variation has very little effect on the mean flow variables in compressible free turbulent shear layers.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 12; Mar. 197
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  • 172
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    Effect of rotor-to-stator spacing on acoustic performance of a full-scale fan (QF-5) for turbofan engines (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study was made of the effect of increasing the fan rotor-to-stator spacing on the noise level of a full-scale, single-stage, 1.6-pressure-ratio fan. Noise data were obtained with axial spacing of 1.14, 1.65, and 2.27 rotor chord lengths. Over this spacing range, data indicate a reduction of 1.5 PNdb. Apparently, rotor-alone noise at the frequency at which the rotor-stator interaction noise was cut off limited the noise reduction for the QF-5 fan. It seems, however, that the reduction in sound power level with increases in spacing is potentially about 6 db over the range of spacing tested.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3103 , E-7879
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  • 173
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    Boundary-layer transition on a plate subjected to simultaneous spanwise and chordwise pressure gradients (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The boundary-layer transition on a short plate was studied by means of the china-clay visual technique. The plate model was mounted in a wind tunnel so that it was subjected to small simultaneous spanwise and chordwise pressure gradients. Results of the experimental study, which was performed at three subsonic velocities, indicated that the transition pattern was appreciably curved in the spanwise direction but quite smooth and well behaved. Reasonable comparisons between predictions of transition and experiment were obtained from two finite-difference two-dimensional boundary-layer calculation methods which incorporated transition models based on the concept of a transition intermittency factor.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3107 , E-7979
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  • 174
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    A streamline curvature method for design of supercritical and subcritical airfoils (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: An airfoil design procedure, applicable to both subcritical and supercritical airfoils, is described. The method is based on the streamline curvature velocity equation. Several examples illustrating this method are presented and discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7770 , L-9747
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  • 175
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    Subsonic annular wing theory with application to flow about nacelles (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A method has recently been developed for calculating the flow over a subsonic nacelle at zero angle of attack. The method makes use of annular wing theory and boundary-layer theory and has shown good agreement with both experimental data and more complex theoretical solutions. The method permits variation of the mass flow by changing the size of a center body.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7630 , L-9274
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  • 176
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    A viscous potential flow interaction analysis method for multi-element infinite swept wings, volume 2 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The program input and output are described, and the program listing is presented. A sample program output for an infinite swept wing calculation is shown.
    Keywords: AERODYNAMICS
    Type: NASA-CR-137550 , REPT-20
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  • 177
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    The effect of canard and vertical tails on the aerodynamic characteristics of a model with a 59 deg sweptback wing at a Mach number of 0.30 (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: An investigation has been conducted to determine the effects of canard, canard location, vertical tails, and vertical-tail location on the aerodynamic characteristics of a model having a 59 deg sweptback wing. The investigation was conducted at a Mach number of 0.30, at angles of attack up to 22 deg and at sideslip angles of 0 deg and plus or minus 5 deg. The results of the study indicate that adding the canard to the model had only a slight effect on the lift at the lower angles of attack. At the higher angles of attack there is a significant effect of canard height on lift, canard in the high location (above the wing chord plane) resulting in the highest lifts. The lift drag characteristics are predicted well for the configuration with the mid or high canard locations by combining a potential flow solution on the canard with a potential plus vortex solution on the wing. Variations in the height significantly affect the pitching-moment characteristics of the configuration; the configuration with the low or mid canard location exhibits an increase in stability at the higher lift coefficients, whereas the configuration with the high canard exhibits pitch-up. Adding the vertical tails in the outboard location caused a significant loss in lift at the higher angles of attack; this lift loss was eliminated by moving the vertical tails inboard.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3088 , L-9662
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  • 178
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    Calculations of the pressure distribution on axisymmetric boattails including effects of viscous interactions and exhaust jets in subsonic flow (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A method of calculating the pressure distributions on boattails is proposed. This method accounts for viscous effects including the presence of a separated region for base flows by combining an inviscid analysis with a boundary layer analysis in an iterative calculation. Details of the reversed flow region are not considered. Some preliminary results have been obtained for boattails at subsonic free stream Mach number with turbulent boundary layers separating at the boattail base. In some cases convergence could not be obtained using the present computer program. It is possible, in principle, to extend this method to the calculation of boattail flows with pressure gradient induced separation on the boattail.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3109 , E-7811
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  • 179
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    Subsonic and supersonic longitudinal stability and control characteristics of an aft tail fighter configuration with cambered and uncambered wings and uncambered fuselage (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: An investigation has been made in the Mach number range from 0.20 to 2.16 to determine the longitudinal aerodynamic characteristics of a fighter airplane concept. The configuration concept employs a single fixed geometry inlet, a 50 deg leading-edge-angle clipped-arrow wing, a single large vertical tail, and low horizontal tails. The wing camber surface was optimized in drag due to lift and was designed to be self-trimming at Mach 1.40 and at a lift coefficient of 0.20. An uncambered or flat wing of the same planform and thickness ratio was also tested. However, for the present investigation, the fuselage was not cambered. Further tests should be made on a cambered fuselage version, which attempts to preserve the optimum wing loading on that part of the theoretical wing enclosed by the fuselage.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3078 , L-9463
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  • 180
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    Performance of a highly loaded two stage axial-flow fan (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A two-stage axial-flow fan with a tip speed of 1450 ft/sec (442 m/sec) and an overall pressure ratio of 2.8 was designed, built, and tested. At design speed and pressure ratio, the measured flow matched the design value of 184.2 lbm/sec (83.55kg/sec). The adiabatic efficiency at the design operating point was 85.7 percent. The stall margin at design speed was 10 percent. A first-bending-mode flutter of the second-stage rotor blades was encountered near stall at speeds between 77 and 93 percent of design, and also at high pressure ratios at speeds above 105 percent of design. A 5 deg closed reset of the first-stage stator eliminated second-stage flutter for all but a narrow speed range near 90 percent of design.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3076 , E-7851
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  • 181
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    Transonic off-design drag and performance of an axisymmetric inlet with 40 percent internal contraction on design (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: An experimental investigation determined the drag and pressure performance of an axisymmetric supersonic inlet when operated in the transonic speed range. The inlet configuration was derived from a Mach 2.5 mixed compression inlet design with assumed variable geometry. At typical engine airflows the drag coefficient varied from 0.057 to 0.192 when the Mach number changed from 0.80 to 1.27. The presence of a wing simulator resulted in a sizable increase in total drag at Mach 1.2. This interference drag, which is roughly a 0.1 increase in drag coefficient, originates equally from an increase in both additive and cowl pressure drag.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3042 , E-7692
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  • 182
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    Aerodynamic characteristics of three slender sharp-edge 74 degrees swept wings at subsonic, transonic, and supersonic Mach numbers (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Slender sharp-edge wings having leading-edge sweep angles of 74 deg have been studied at Mach numbers from 0.60 to 2.80, at angles of attack from about minus 4 deg to 22 deg, and at angles of sideslip from 0 deg to 5 deg. The wings had delta, arrow, and diamond planforms. The experimental tests were made in the Langley 8-foot transonic pressure tunnel and the Langley Unitary Plan wind tunnel test section number 1. The theoretical predictions were made using the theories of NASA TN D-3767 and NASA TN D-6243. The results of the study indicated that the lift and drag characteristics as affected by planform and Mach number could be reasonably well predicted for the delta wing in the subsonic and transonic Mach number range. In the supersonic range, the delta and diamond wings were about equally good in the degree of agreement between experiment and theory. In making drag-due-to-lift predictions the vortex lift effects must be taken into account if reasonable results are to be obtained at moderate or high lift coefficients.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7631 , L-9433
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  • 183
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    Lateral-directional stability characteristics of a wing-fuselage configuration at angles of attack up to 44 deg (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: An investigation has been conducted to determine the effects of configuration variables on the lateral-directional stability characteristics of a wing-fuselage configuration. The variables under study included variations in the location of a single center-line vertical tail and twin vertical tails, wing height, fuselage strakes, and horizontal tails. The study was conducted in the Langley high-speed 7-by 10-foot tunnel at a Mach number of 0.30, at angles of attack up to 44 deg and at sideslip angles of 0 deg and plus or minus 5 deg.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3087 , L-9541
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  • 184
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    An analytical study of the effects of jets located more than one jet diameter above a wing at subsonic speeds (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A procedure has been developed for calculating the effects of blowing two jets over a swept tapered wing at low subsonic speeds. The algorithm used is based on a vortex-lattice representation of the wing lifting surface and a line sink-source distribution to simulate the effects of the jet exhaust on the wing lift and drag. The method is limited to those cases in which the jet exhaust does not intersect or wash the wing. The predictions of this relatively simple procedure are in remarkably good agreement with experimentally measured interference lift and interference induced drag.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7754 , L-9683
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  • 185
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    Aeronautical engineering: A special bibliography, supplement 44 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This special bibliography lists 249 reports, articles, and other documents introduced into the NASA scientific and technical information system in April 1974.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(44)
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  • 186
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    Theoretical and experimental longitudinal aerodynamic characteristics of an aspect ratio 0.25 sharp-edge delta wing at subsonic, supersonic, and hypersonic speeds (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The suction analogy concept of Polhamus for predicting vortex lift in conjunction with an appropriate potential-flow solution is called the present method. This method is applied to an aspect ratio 0.25 sharp-edge delta wing from a Mach number of 0.143 to 10.4 in free air and at 0.074 in ground effect, and also to an aspect ratio 0.35 triangular crosssectional body at a Mach number of 6.9. The models had subsonic leading edges at the test Mach numbers. Vortex-flow effects could be neither confirmed nor denied to exist at high speeds because of the lack of flow visualization above a Mach number of 0.143. The data, however, could be better predicted by including a vortex-flow effect, although not always to the extent predicted from the present method because of the presence of actual and hypothesized unmodeled flow situations. The method of Nenni and Tung (NASA CR-1860) tended to confirm the existence of vortex flow at hypersonic speeds. The hypersonic-tangent-cone method predicted best the delta-wing results over the test angle-of-attack range and hypersonic Mach number range and did equally as well as the present method for the triangular body.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7651 , L-9328
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  • 187
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    Assessment of a wake vortex flight test program (1974)
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    Publication Date: 2019-06-27
    Description: A proposed flight test program to measure the characteristics of wake vortices behind a T-33 aircraft was investigated. A number of facets of the flight tests were examined to define the parameters to be measured, the anticipated vortex characteristics, the mutual interference between the probe aircraft and the wake, the response of certain instruments to be used in obtaining measurements, the effect of condensation on the wake vortices, and methods of data reduction. Recommendations made as a result of the investigation are presented.
    Keywords: AERODYNAMICS
    Type: NASA-CR-114736 , NEAR-TR-48
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  • 188
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    Longitudinal aerodynamic performance of a series of power-law and minimum wave drag bodies at Mach 6 and several Reynolds numbers (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Experimental data have been obtained for two series of bodies at Mach 6 and Reynolds numbers, based on model length, from 1.4 million to 9.5 million. One series consisted of axisymmetric power-law bodies geometrically constrained for constant length and base diameter with values of the exponent n of 0.25, 0.5, 0.6, 0.667, 0.75, and 1.0. The other series consisted of positively and negatively cambered bodies of polygonal cross section, each having a constant longitudinal area distribution conforming to that required for minimizing zero-lift wave drag at hypersonic speeds under the geometric constraints of given length and volume. At the highest Reynolds number, the power-law body for minimum drag is blunter (exponent n lower) than predicted by inviscid theory (n approximately 0.6 instead of n = 0.667); however, the peak value of lift-drag ratio occurs at n = 0.667. Viscous effects were present on the bodies of polygonal cross section but were less pronounced than those on the power-law bodies. The trapezoidal bodies with maximum width at the bottom were found to have the highest maximum lift-drag ratio and the lowest mimimum drag.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2713 , L-7609
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  • 189
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    Aeronautical engineering: A special bibliography with indexes, supplement 43, April 1974 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This special bibliography lists 421 reports, articles, and other documents introduced into the NASA scientific and technical information system in March 1974.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(43)
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  • 190
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    Performance of a short annular dump diffuser using wall trailing-edge suction (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A short annular dump (abrupt flow area change) diffuser was tested with suction through wall trailing-edge slots at inlet Mach numbers of 0.19 and 0.27 and at near ambient inlet temperature and pressure, with suction flow varied from zero to 10 percent of the inlet air mass-flow rate. The overall ratio of diffuser exit area to inlet area was 4.0, and the ratio of length to inlet height was 2.0. By applying suction flow separately on either wall or to both walls simultaneously, the original annular jet profile could be altered to either a hub- or tip-biased profile. Diffuser effectiveness was increased from about 25 percent with no suction to 50 percent at 6 percent outer-wall suction and to 52 percent at a combined suction rate on both walls of 10.25 percent. At the same time, diffuser total pressure loss was reduced by one-fourth.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3093 , E-7944
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  • 191
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    An assessment of airfoil design by numerical optimization (1974)
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    Publication Date: 2019-06-27
    Description: A practical procedure for optimum design of aerodynamic shapes is demonstrated. The proposed procedure uses an optimization program based on the method of feasible directions coupled with an analysis program that uses a relaxation solution of the inviscid, transonic, small-disturbance equations. Results are presented for low-drag, nonlifting transonic airfoils. Extension of the method to lifting airfoils, other speed regimes, and to three dimensions if feasible.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3092 , A-5506
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  • 192
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    A finite difference method for the solution of the transonic flow around harmonically oscillating wings (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A finite difference method for the solution of the transonic flow about a harmonically oscillating wing is presented. The partial differential equation for the unsteady transonic flow was linearized by dividing the flow into separate steady and unsteady perturbation velocity potentials and by assuming small amplitudes of harmonic oscillation. The resulting linear differential equation is of mixed type, being elliptic or hyperbolic whereever the steady flow equation is elliptic or hyperbolic. Central differences were used for all derivatives except at supersonic points where backward differencing was used for the streamwise direction. Detailed formulas and procedures are described in sufficient detail for programming on high speed computers. To test the method, the problem of the oscillating flap on a NACA 64A006 airfoil was programmed. The numerical procedure was found to be stable and convergent even in regions of local supersonic flow with shocks.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2257 , D6-41082
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  • 193
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    Throat stability-by pass systems to increase the stable airflow range of a Mach 2.5 inlet with 60-percent internal contraction (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The results of an experimental investigation to increase the stable airflow range (without unstart) of a supersonic mixed-compression inlet are presented. Various stability bypass entrances were located on the cowl side of the inlet throat. The types of entrance were distributed porous (normal holes), forward-slanted slot, and distributed educated slots. A large stable airflow range was obtained for each entrance type if a constant pressure was maintained in the stability bypass plenum. The distributed porous entrance provided the largest stable airflow range. Inlet unstart angle of attack was unaffected by the entrances.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2976 , E-7738
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  • 194
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    Planetary mission summary. Volume 3: Mars surface sample return (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-23129.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: NASA-CR-147095 , JPL-SP-43-10-VOL-3
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  • 195
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    Planetary mission summary. Volume 4: Mars rover (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-23129.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: NASA-CR-147096 , JPL-SP-43-10-VOL-4
    Format: application/pdf
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  • 196
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    User's manual for the coupled mode version of the normal modes rotor aeroelastic analysis computer program (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This User's Manual was prepared to provide the engineer with the information required to run the coupled mode version of the Normal Modes Rotor Aeroelastic Analysis Computer Program. The manual provides a full set of instructions for running the program, including calculation of blade modes, calculations of variable induced velocity distribution and the calculation of the time history of the response for either a single blade or a complete rotor with an airframe (the latter with constant inflow).
    Keywords: AERODYNAMICS
    Type: NASA-CR-137899 , SER-50910
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  • 197
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    Analysis of Mariner 5 Radio Tracking Data (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Mariner 5 radio tracking data was analyzed to support the following goals: (1) the determination of the mass of Venus, (2) the determination of, or the placement of a stringent upper bound on, the second order terms in the harmonic expansion of Venus' gravity field; and (3) an independent estimate of the locations of the Deep Space Net tracking stations relative to the coordinate system defined by the orbits of the planets. The rotation vector of Venus was also studied using radar observations of the planet.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: NASA-CR-148482
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  • 198
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    Correlation of turbulent trailing vortex decay data (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A correlation function, derived on the basis of self similar variable eddy viscosity decay, is introduced and utilized to correlate aircraft trailing vortex velocity data from ground and flight experiments. The correlation function collapses maximum tangential velocity data from scale model and flight tests to a single curve. The resulting curve clearly shows both the inviscid plateau and the downstream decay regions. A comparison between experimental data and numerical solution shows closer agreement with the variable eddy viscosity solution than the constant viscosity analytical solution.
    Keywords: AERODYNAMICS
    Type: NASA-CR-146282
    Format: application/pdf
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  • 199
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    Investigation of a glass spherule from the Luna-16 probe (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A glass spherule of the form of a flattened spheroid measuring 580 microns in diameter is studied. The spherule is transparent, shiny, and of a yellowish brown tint. It contains a number of central and peripheral spherical bubble-type cavities. The surface and morphology features resemble those of Apollo spherules, but differ in chemical composition, which is close to that of the Luna-16 regolith.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Format: text
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  • 200
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    Mineralogy, petrology, and chemistry of basalt fragments returned by Luna 16 (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Mineralogical, petrological, and chemical analyses, along with Rb-Sr age and Ar-40/Ar-39 measurements, were carried out with the B-1 sample returned from the Luna 16 mission. The sample, weighing 62 mg, is a fine-grain basalt of ophitic structure. It differs from the Apollo samples in that the pyroxene and plagioclass contents are almost identical, and the ilmenite content (7%) lies between those of the Apollo-11 and Apollo-12 samples. Chemically, it is characterized by a high Sr content and a high K/U ratio.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Format: text
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