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  • General Chemistry  (516)
  • Cell & Developmental Biology  (123)
  • Aircraft Design, Testing and Performance  (52)
  • SPACE RADIATION
  • 1970-1974
  • 1960-1964  (710)
  • 1961  (710)
Collection
Keywords
Publisher
Years
  • 1970-1974
  • 1960-1964  (710)
Year
  • 1
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    THE MOTION OF SATELLITE 1958 EPSILON AROUND ITS CENTER OF MASS (1961)
    In:  CASI
    Details
    Publication Date: 2008-08-25
    Description: Motion of satellite 1958 epsilon around its center of mass
    Keywords: SPACE RADIATION
    Type: SAO SPECIAL REPT.-70
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  • 2
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    CATALOGUE OF SATELLITE OBSERVATIONS, NO. C-23 (1961)
    In:  CASI
    Details
    Publication Date: 2008-08-25
    Description: Catalog of satellite observations, c-23
    Keywords: SPACE RADIATION
    Type: SAO SPECIAL REPT.-67
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  • 3
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    EVALUATION OF U.S.S.R. VS. U.S. OUTPUT IN SPACE SCIENCE RELEASE NO. 41-31 (1961)
    In:  CASI
    Details
    Publication Date: 2006-03-16
    Keywords: SPACE RADIATION
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  • 4
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    PRINCIPLES FOR THE CALCULATION OF RADIATION DOSE RATES IN SPACE VEHICLES (1961)
    In:  CASI
    Details
    Publication Date: 2012-03-16
    Description: Calculation of radiation dose rates in spacecraft
    Keywords: SPACE RADIATION
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  • 5
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    SUMMARY PROGRESS REPORT OF RESEARCHES, FOR THE PERIOD NOV. 15, 1960-MAY 15, 1961 (1961)
    In:  CASI
    Details
    Publication Date: 2012-03-15
    Description: S-15 gamma ray satellite, payload preparation launch operation and performance
    Keywords: SPACE RADIATION
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  • 6
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    TIDAL DEFORMATIONS AND THE ORIGIN OF THE MOON (1961)
    In:  CASI
    Details
    Publication Date: 2012-05-25
    Keywords: SPACE RADIATION
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  • 7
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    TEKTITES AND NATURAL SATELLITES OF THE EARTH (1961)
    In:  CASI
    Details
    Publication Date: 2012-05-15
    Keywords: SPACE RADIATION
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  • 8
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    LUNAR REFERENCE COORDINATES (1961)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Two nonconflicting conventions defined for lunar and planetary reference coordinates - astronomical versus astronautical maps and charts
    Keywords: SPACE RADIATION
    Type: JPL-TM-33-72 , N-108346
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  • 9
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    RESEARCH STUDY TO DETERMINE PROPULSION REQUIREMENTS AND SYSTEMS FOR SPACE MISSIONS VOL. IVA (1961)
    In:  Other Sources
    Details
    Publication Date: 2019-05-10
    Keywords: SPACE RADIATION
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  • 10
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    RESEARCH STUDY TO DETERMINE PROPULSION REQUIREMENTS AND SYSTEMS FOR SPACE MISSIONS VOL. IIB FINAL REPORT, 〈COVERING PERIOD〈 FEB. 1 THRU OCT. 31, 1961 (1961)
    In:  CASI
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    Publication Date: 2019-05-10
    Keywords: SPACE RADIATION
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  • 11
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    RESEARCH STUDY TO DETERMINE PROPULSION REQUIREMENTS AND SYSTEMS FOR SPACE MISSIONS VOL. 1 FINAL REPORT, 〈COVERING PERIOD〈 FEB. 1, THRU OCT. 31, 1961 (1961)
    In:  CASI
    Details
    Publication Date: 2019-05-10
    Keywords: SPACE RADIATION
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  • 12
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    INTERACTION OF A CHARGED SATELLITE WITH THE IONOSPHERE (1961)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: Interaction of a charged artificial satellite with the ionosphere
    Keywords: SPACE RADIATION
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  • 13
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    RESEARCH STUDY TO DETERMINE PROPULSION REQUIREMENTS AND SYSTEMS FOR SPACE MISSIONS VOL. III FINAL REPORT, 〈COVERING PERIOD〈 FEB. 1 THRU OCT. 31, 1961 (1961)
    In:  CASI
    Details
    Publication Date: 2019-05-10
    Keywords: SPACE RADIATION
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  • 14
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    CHEMICAL ANALYSIS OF LUNAR SURFACES REPORT FOR THE PERIOD FEBRUARY 1 - MAY 1, 1961 (1961)
    In:  CASI
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    Publication Date: 2019-05-10
    Keywords: SPACE RADIATION
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  • 15
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    RESEARCH STUDY TO DETERMINE PROPULSION REQUIREMENTS AND SYSTEMS FOR SPACE MISSIONS VOL. II A FINAL REPORT, 〈COVERING PERIOD〈 FEB. 1 THRU OCT. 31, 1961 (1961)
    In:  CASI
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    Publication Date: 2019-05-10
    Keywords: SPACE RADIATION
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  • 16
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    PRESENCE AND CORRELATION OF FINE STRUCTURE IN JOVIAN DECAMETRIC RADIATION (1961)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Fine structure of spectral emittance of jupiter in decametric region - noise storms
    Keywords: SPACE RADIATION
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  • 17
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    RENDEZVOUS COMPATIBLE ORBITS (1961)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Rendezvous compatible spacecraft orbit calculation for 150 to 850-km region
    Keywords: SPACE RADIATION
    Type: NASA-TM-X-50230 , MTP-M-S&M-F-61-2
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  • 18
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    The solar constant and spectral distribution of solar radiant flux (1961)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Solar constant and spectral distribution of solar radiant flux
    Keywords: SPACE RADIATION
    Type: NASA-TM-X-51677
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  • 19
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    On the intervening role of the magnetic fields of solar corpuscular streams in the determination of the degree of their geoeffectiveness (1961)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Intervening role of magnetic fields of solar corpuscular streams in determining degree of geoeffectiveness
    Keywords: SPACE RADIATION
    Type: NASA-CR-80819 , ST-SP-GM-10497
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  • 20
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    Transonic Loads Characteristics of a 3-Percent-Thick 60 deg Delta-Wing-Body (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An investigation has been made in the Langley 16-foot transonic tunnel to determine the aerodynamic loading characteristics of a 3-percent-thick, aspect-ratio - 2.06, 60 deg delta-wing-body combination. The Mach number range was from 0.80 t o 1.05 and the average Reynolds number based on wing mean aerodynamic chord was 10 x 10(exp 6). The angle-of-attack range was from 0 deg to 26 deg but was limited at the highest Mach numbers by tunnel drive power. Pressure distributions, spanwise loadings, integrated wing coefficients, and tabulated pressure coefficients are presented for the range of Mach numbers and angles of attack. The results indicate that a free leading-edge separation vortex is the dominant flow-field phenomenon at all Mach numbers and that, consequently, there are only slight changes in the spanwise loadings with Mach number. There is a slight outboard shift in center of pressure with an increase in Mach number. The chord-wise position of the center of pressure varies from 46 t o 55 percent of the mean aerodynamic chord when the Mach number i s increased from 0.80 to l.05.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-830 , L-1543
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  • 21
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    Ground Influence on a Model Airfoil with a Jet-Augmented Flap as Determined by Two Techniques (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation was made in the Langley 300-MPH 7- by 10-foot tunnel with a conventional ground-board setup and in the Langley tank no. 1 by using the tow carriage to move the model over a ground board to evaluate the simulation of flight conditions in ground influence with a conventional ground-board setup. The 12-percent-thick airfoil was unswept and untapered with an aspect ratio of 6.0 and had a 10 percent- chord jet-augmented flap. From this investigation it appears that the loss in lift of an airfoil with a jet-augmented flap in ground influence as determined in a wind tunnel with a conventional ground-board setup is considerably larger than would be obtained in free flight.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-658 , L-1199
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  • 22
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    Large-Scale Wind-Tunnel Tests of Exhaust Ingestion Due to Thrust Reversal on a Four-Engine Jet Transport during Ground Roll (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Wind-tunnel tests have been conducted on a large-scale model of a swept-wing jet transport type airplane to study the factors affecting exhaust gas ingestion into the engine inlets when thrust reversal is used during ground roll. The model was equipped with four small jet engines mounted in nacelles beneath the wing. The tests included studies of both cascade and target type reversers. The data obtained included the free-stream velocity at the occurrence of exhaust gas ingestion in the outboard engine and the increment of drag due to thrust reversal for various modifications of thrust reverser configuration. Motion picture films of smoke flow studies were also obtained to supplement the data. The results show that the free-stream velocity at which ingestion occurred in the outboard engines could be reduced considerably, by simple modifications to the reversers, without reducing the effective drag due to reversed thrust.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-686 , A-445
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  • 23
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    Effect of Nose Bluntness on Transition for a Cone and a Hollow Cylinder at Mach Numbers 1.41 and 2.01 (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation has been made to determine the effects of nose bluntness on boundary-layer transition for a cone with an included angle of 10 degrees and for a hollow cylinder. The tests were conducted at Mach numbers of 1.41 and 2.01 for free-stream Reynolds numbers per foot ranging from 1 x 10(exp 6) to 9 x 10(exp 6). The investigation was made with the use of schlieren photography for which the models were aligned with the free stream. For the 10 degree cone, the favorable effects of nose blunting were so small at both test Mach numbers as to be lost within the experimental accuracy. For small amounts of nose blunting on the hollow cylinder, for which the ratio of bluntness height to transition distance for the sharp-leading-edge cylinder was relatively small, there was little, if any, effect of blunting on transition. For somewhat larger values of this ratio, nose blunting had a favorable effect on transition. The magnitude of the favorable effect was dependent upon the size and the shape of the bluntness, and the maximum increase in transition distance relative to the sharp-leading-edge cylinder is in good agreement with the theoretical predictions of NACA Technical Report 1312. For relatively large values of the ratio of nose bluntness to transition distance, the effects of nose blunting were adverse for both the cone and the cylinder. In general, adverse effects due to blunting were larger for the flat bluntness than for the hemispherical or the round bluntness of equal bluntness height. Increasing the Mach number increased the size of bluntness required to induce adverse effects at constant free-stream Reynolds number per foot, delayed the adverse effects to higher values of Reynolds number per foot for constant nose bluntness, and reduced the abruptness of the transition decrease.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-717 , L-762
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  • 24
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    Low-Subsonic-Speed Static Stability of Right-Triangular-Pyramid and Half-Cone Lifting Reentry Configurations (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation has been made to determine the low-subsonic-speed static stability characteristics of several right-triangular-pyramid and half-cone configurations. Also studied were the effects of various modifications, such as base extensions, nose shape, nose incidence, and ridge-line shape. The investigation showed that, in general, the models had satisfactory longitudinal and lateral stability. The basic pyramid model and the conical ridge-line model with or without a rounded nose had almost identical longitudinal and lateral stability characteristics and lift-drag ratios. The lift-drag ratios of the cylindrical ridge-line and half-cone models were considerably lower than those of the conical ridge-line model. The addition of a 20 degree boattail to the models increased the lift-drag ratios but decreased the directional stability, whereas a streamwise base extension was more effective in increasing the lift-drag ratios and increased the directional stability.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-646 , L-1242
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  • 25
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    Take-off Distances of a Supersonic Transport Configuration as Affected by Airplane Rotation During the Take-off Run (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The take-off distances over a 35-foot obstacle have been determined for a supersonic transport configuration characterized by a low maximum lift coefficient at a high angle of attack and by high drag due to lift. These distances were determined analytically by means of an electronic digital computer. The effects of rotation speed, rotation angle, and rotation time were determined. A few configuration changes were made to determine the effects of thrust-weight ratio, wing loading, maximum lift coefficient, and induced drag on the take-off distance. The required runway lengths based on Special Civil Air Regulation No. SR-422B were determined for various values of rotation speed and compared with those based on full engine power. Increasing or decreasing the rotation speed as much as 5 knots from the value at which the minimum take-off distance occurred increased the distance only slightly more than 1 percent for the configuration studied. Under-rotation by 1 deg to 1.5 deg increased the take-off distance by 9 to 15 percent. Increasing the time required for rotation from 3 to 5 seconds had a rather small effect on the take-off distance when the values of rotation speed were near the values which result in the shortest take-off distance. When the runway length is based on full engine power rather than on SR-422B, the rotation speed which results in the shortest required runway length is 10 knots lower and the runway length is 4.3 percent less.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-982 , L-1728
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  • 26
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    Effects of Canard Planform and Wing-Leading-Edge Modification on Low-Speed Longitudinal Aerodynamic Characteristics of a Canard Airplane Configuration (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation has been conducted at low subsonic speeds to study the effects of canard planform and wing-leading-edge modification on the longitudinal aerodynamic characteristics of a general research canard airplane configuration. The basic wing of the model had a trapezoidal planform, an aspect ratio of 3.0, a taper ratio of 0.143, and an unswept 80-percent-chord line. Modifications to the wing included addition of full-span and partial-span leading-edge chord-extensions. Two canard planforms were employed in the study; one was a 60 deg sweptback delta planform and the other was a trapezoidal planform similar to that of the basic wing. Modifications to these canards included addition of a full-span leading-edge chord-extension to the trapezoidal planform and a fence to the delta planform. For the basic-wing-trapezoidal-canard configuration, rather abrupt increases in stability occurred at about 12 deg angle of attack. A slight pitch-up tendency occurred for the delta-canard configuration at approximately 8 deg angle of attack. A comparison of the longitudinal control effectiveness for the basic-wing-trapezoidal-canard combination and for the basic-wing-delta-canard combination indicates higher values of control effectiveness at law angles of attack for the trapezoidal canard. The control effectiveness for the delta-canard configuration, however, is seen to hold up for higher canard deflections and to higher angles of attack. Use of a full-span chord-extension deflected approximately 30 deg on the trapezoidal canard greatly improved the control characteristics of this configuration and enabled a sizeable increase in trim lift to be realized.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-958 , L-1372
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  • 27
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    Free-Flight Investigation of Radio Controlled Models with Parawings (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A free-flight investigation of two radio-controlled models with parawings, a glider configuration and an airplane (powered) configuration, was made to evaluate the performance, stability, and methods of controlling parawing vehicles. The flight tests showed that the models were stable and could be controlled either by shifting the center of gravity or by using conventional elevator and rudder control surfaces. Static wind-tunnel force-test data were also obtained.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-927 , L-1374
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  • 28
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    Experimental Investigation of a Hypersonic Glider Configuration at a Mach Number of 6 and at Full-Scale Reynolds Numbers (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The aerodynamic characteristics of a hypersonic glider configuration, consisting of a slender ogive cylinder with three highly swept wings, spaced 120 apart, with the wing chord equal to the body length, were investigated experimentally at a Mach number of 6 and at Reynolds numbers from 6 to 16 million. The objectives were to evaluate the theoretical procedures which had been used to estimate the performance of the glider, and also to evaluate the characteristics of the glider itself. A principal question concerned the viscous drag at full-scale Reynolds number, there being a large difference between the total drags for laminar and turbulent boundary layers. It was found that the procedures which had been applied for estimating minimum drag, drag due to lift, lift curve slope, and center of pressure were generally accurate within 10 percent. An important exception was the non-linear contribution to the lift coefficient which had been represented by a Newtonian term. Experimentally, the lift curve was nearly linear within the angle-of-attack range up to 10 deg. This error affected the estimated lift-drag ratio. The minimum drag measurements indicated that substantial amounts of turbulent boundary layer were present on all models tested, over a range of surface roughness from 5 microinches maximum to 200 microinches maximum. In fact, the minimum drag coefficients were nearly independent of the surface smoothness and fell between the estimated values for turbulent and laminar boundary layers, but closer to the turbulent value. At the highest test Reynolds numbers and at large angles of attack, there was some indication that the skin friction of the rough models was being increased by the surface roughness. At full-scale Reynolds number, the maximum lift-drag ratio with a leading edge of practical diameter (from the standpoint of leading-edge heating) was 4.0. The configuration was statically and dynamically stable in pitch and yaw, and the center of pressure was less than 2-percent length ahead of the centroid of plan-form area.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-341
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  • 29
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    Near-Field and Far-Field Noise Measurements for a Blowdown-Wind-Tunnel Supersonic Exhaust Jet having about 475,000 Pounds of Thrust (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Near-field and far-field noise surveys were made of the supersonic The exhaust jet of the Langley 9- by 6-foot thermal structures tunnel. The jet had a thrust rating of approximately 475,000 pounds. The sound power radiated was found to be about 3.6 x 10(exp 6) watts, and on an acoustical-mechanical efficiency basis this value is in reasonable agreement with data for smaller supersonic jets and for rocket engines of other investigations. Octave-band analyses of the near-field noise show that the maximum sound pressure levels in the low-frequency bands are greatest downstream, whereas maximum sound pressure levels in the high-frequency bands were greatest near the jet exit. A comparison of near-field noise measurements is made with data previously obtained for rocket engines. Noise survey measurements of the original jet are compared with similar data obtained after the addition of a 97-foot-long exit diffuser section, and an example of the application of this facility to the problem of acoustic environmental testing of a large space capsule is cited.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-517 , L-499
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  • 30
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    Heat-Transfer Measurements on the Apexes of Two 60 deg Sweptback Delta Wings (Panel Semiapex Angle of 30 deg) Having 0 deg and 45 deg Dihedral at a Mach Number of 4.95 (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An experimental investigation was conducted to evaluate the heat-transfer rates at the apex of two 60 degree sweptback delta wings (panel semi-apex angle of 30 degrees) having cylindrical leading edges and 0 degrees and 45 degree positive dihedral. The models tested might correspond to the first several feet of a hypersonic reentry vehicle. The tests were conducted at a Mach number of 4.95 and a stagnation temperature of 400 F. nominal test-section unit Reynolds numbers varied from 2 x 10(exp 6) to 12 x 10(exp 6) per foot. The results of the investigation indicated that the laminar heat-transfer distributions (ratio of local to stagnation-line heating rate) about the models normal to the leading edges were in close agreement with two-dimensional blunt-body theory. The three-dimensional stagnation point heat-transfer rate on the 0 degree dihedral model was in excellent agreement with theory and the stagnation-line heat transfer on the straight portion of the leading edge of both models approached a constant level 12 percent above the theoretical stagnation-line level on an isolated swept infinite cylinder. When the heating rates on the 45 degree dihedral model (planform sweep of 69.3 degree) were compared with those on the 0 degree dihedral model (planform sweep of 60 degrees) at equal angles of attack and equal lifts greater than zero, the stagnation-line heating rates on the 45 degrees dihedral model were, in general, considerably lower as a result of the difference in effective sweeps of the leading edges. On the wing panels inboard from the stagnation lines, the differences in heating were very small. The stagnation-line heat-transfer variation with angle of attack, the shift in stagnation-line location, and the reduction in stagnation-line heat transfer resulting from the increase in effective sweep when positive dihedral is incorporated into a constant-panel 0 degree dihedral wing, all agreed with the results of a theoretical study made of highly swept delta wings with large positive dihedral.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-550 , L-963
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  • 31
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    An Approximate Analysis of Film Cooling on Blunt Bodies by Gas Injection Near the Stagnation Point (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An approximate method for the estimation of laminar heat transfer to blunt bodies with gaseous film cooling i s developed. Attention is focused on the parameters which are important for the design of an attractive heat protection system. Application of the analysis is made to calculate the approximate coolant weight requirement for both a circular and a parabolic entry.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-861 , A-499
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  • 32
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    Wind-Tunnel Investigation of the Effects of Wing Bodies, Fences, Flaps, and a Fuselage Addition on the Wing Buffet Response of a Transonic-Transport Model (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The experimental wing buffet response of a transport-type airplane model with and without wing bodies, fences, flaps, and a fuselage addition has been investigated at Mach numbers from 0.20 to 1.03. The wing had NACA 64A-series airfoil sections inclined 5 degrees to the free-stream direction. The quarter-chord line of the wing was swept back 45 degrees, the aspect ratio was 7, the taper ratio was 0.3, and the thickness ratio varied from 0.115 at the root to 0.074 at the midsemispan and was constant from that station to the tip. The wing was twisted and cambered for a design lift coefficient of 0.3. The results of the investigation indicated that a marked reduction of buffet intensity and a delay of buffet onset at transonic speeds were achieved by the addition to the wing of special bodies designed to reduce shock-induced separation. The further addition of wing fences and wing trailing-edge flaps deflected 30 degrees increased the lift coefficients at which low-speed stall buffeting occurred. An addition to the fuselage near the upper forward portion produced no consistent change in the buffet characteristics.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-637
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  • 33
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    Airspeed Operating Practices of Turbine-Powered Commercial Transport Airplanes (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Data obtained with NASA VGH and V-G recorders installed on three types of turboprop and one type of turbojet commercial transport air- plane have been analyzed to determine the relation of the maximum operational speeds to the placard normal-operating and never-exceed speeds. The frequency of exceeding the placard speeds is compared with corresponding results for past operations with piston-powered transports. In addition, data pertaining to the operational altitudes and the average airspeeds in rough and smooth air for the turbine-powered transports are presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-744
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  • 34
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    Flight Tests of a 1/6-Scale Model of the Hawker P 1127 Jet VTOL Airplane (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An experimental investigation has been made to determine the dynamic stability and control characteristics of a 1/6-scale flying model of the Hawker P lIP7 jet vertical-take-off-and-landing (VTOL) airplane in hovering and transition flight. The model was powered by a counter-rotating ducted fan driven by compressed-air jets at the tips of the fan blades. In hovering flight the model was controlled by jet-reaction controls which consisted of yaw and pitch jets at the extremities of the fuselage and a roll jet on each wing tip. In forward flight the model was controlled by conventional ailerons and rudder and an all-movable horizontal tail. In hovering flight the model could be flown smoothly and easily, but the roll control was considered too weak for rapid maneuvering or hovering in gusty air. Transitions from hovering to normal forward flight and back to hovering could be made smoothly and consistently and with only moderate changes in longitudinal trim. The model had a static longitudinal instability or pitch-up tendency throughout the transition range, but the rate of divergence in the pitch-up was moderate and the model could be controlled easily provided the angle of attack was not allowed to become too high. In both the transition and normal forward flight conditions the lateral motions of the model were difficult to control at high angles of attack, apparently because of low directional stability at small angles of sideslip. The longitudinal stability of the model in normal forward flight was generally satisfactory, but there was a decided pitch-up tendency for the flap-down condition at high angles of attack. In the VTOL landing approach condition, with the jets directed straight down or slightly forward, the nose-down pitch trim required was greater than in the transitions from hovering to forward flight, but the longitudinal instability was about the same. Take-offs and landings in still air could be made smoothly although there was a slight unfavorable ground effect on lift and a nose-down change in pitch trim near the ground. Short take-offs and landings could be made smoothly and consistently although the model experienced a decided nose-up change in pitching moment as it climbed out of ground effect.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-SX-531 , L-1484
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  • 35
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    An Analytical Treatment of Aircraft Propeller Precession Instability (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An analytical investigation is made of a precession-type instability which can occur in a flexibly supported aircraft-engine-propeller combination. By means of an idealized mathematical model which is comprised of a rigid power-plant system flexibly mounted in pitch and yaw to a fixed backup structure, the conditions required for neutral stability are determined. The paper also examines the sensitivity of the stability boundaries to changes in such parameters as stiffness, damping, and asymmetries in the engine mount, propeller speed, airspeed, Mach number, propeller thrust, and location of pitch and yaw axes. Stability is found to depend strongly on the damping and stiffness in the system. With the use of nondimensional charts, theoretical stability boundaries are compared with experimental results obtained in wind-tunnel tests of an aeroelastic airplane model. In general, the theoretical results, which do not account for wing response, show the same trends as observed experimentally; however, for a given set of conditions calculated airspeeds for neutral stability are consistently lower than the measured values. Evidently, this result is due to the fact that wing response tends to add damping to the system.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-659
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  • 36
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    Investigation of a Water-Pond Arresting of a Dynamic Model of a Jet Transport (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Brief dynamic-model tests have been made at the request of the Federal Aviation Agency to investigate the use of a shallow pond of water at the end of a runway as a means of arresting jet-transport aircraft when they are forced to abort on take-off or overrun on landing. Such a scheme is of particular interest for civil aircraft because it requires no modifications or attachments to the airplane and no mechanical devices in the arresting system. A modification of this scheme that uses a flexible plastic cover over the water surface has also been tested. The purpose of this paper is to present the results of a dynamic model investigation which would aid in determining whether the water-pond arresting system could be used as a means of arresting airplane overrun.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-732 , L-1318
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  • 37
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    Analysis of Effects of Interceptor Roll Performance and Maneuverability on Success of Collision-Course Attack (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An attempt has been made to determine the importance of rolling performance and other factors in the design of an interceptor which uses collision-course tactics. A graphical method is presented for simple visualization of attack situations. By means of diagrams showing vectoring limits, that is, the ranges of interceptor position and heading from which attacks may be successfully completed, the relative importance of rolling performance and normal-acceleration capability in determining the success of attacks is illustrated. The results indicate that the reduction in success of attacks due to reduced rolling performance (within the limits generally acceptable from the pilots' standpoint) is very small, whereas the benefits due to substantially increasing the normal-acceleration capability are large. Additional brief analyses show that the optimum speed for initiating a head-on attack is often that corresponding to the upper left-hand corner of the V-g diagram. In these cases, increasing speed beyond this point for given values of normal acceleration and radar range rapidly decreases the width of the region from which successful attacks can be initiated. On the other hand, if the radar range is increased with a variation somewhere between the first and second power of the interceptor speed, the linear dimensions of the region from which successful attacks can be initiated vary as the square of the interceptor speed.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-952
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  • 38
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    Incipient- and Developed-Spin and Recovery Characteristics of a Modern High-Speed Fighter Design with Low Aspect Ratio as Determined from Dynamic-Model Tests (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Incipient- and developed-spin and recovery characteristics of a modern high-speed fighter design with low aspect ratio have been investigated by means of dynamic model tests. A 1/7-scale radio-controlled model was tested by means of drop tests from a helicopter. Several 1/25-scale models with various configuration changes were tested in the Langley 20-foot free-spinning tunnel. Model results indicated that generally it would be difficult to obtain a developed spin with a corresponding airplane and that either the airplane would recover of its own accord from any poststall motion or the poststall motion could be readily terminated by proper control technique. On occasion, however, the results indicated that if a post-stall motion were allowed to continue, a fully developed spin might be obtainable from which recovery could range from rapid to no recovery at all, even when optimum control technique was used. Satisfactory recoveries could be obtained with a proper-size tail parachute or strake, application of pitching-, rolling-, or yawing-moment rockets, or sufficient differential deflection of the horizontal tail.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-956 , L-1662
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  • 39
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    Transonic Investigation of Aerodynamic Characteristics of a Swept-Wing Fighter-Airplane Model with Leading-Edge Droop in Combination with Outboard Chord-Extensions and Notches (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 60 and 20 degrees chord-extension overhangs of 0.075c and 0.15c (where c inboard end of the 0.075c chord-extension to depths of 0.075c and 0.l25c, and indention of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included. Generally, the model wing modifications provided only slight improvements of the airplane longitudinal stability characteristics, but did substantially reduce the airplane drag coefficients at moderate and high lifting conditions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-834 , L-1060
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  • 40
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    Investigation of the Longitudinal Characteristics of a Large-Scale Jet Transport Model Equipped with Controllable Thrust Reversers (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation was conducted to determine the effect of thrust control by means of controllable thrust reversers on the longitudinal characteristics of a large-scale airplane model with a 35' sweptback wing of aspect ratio of 7 and four pylon-mounted jet engines equipped with target-type thrust reversers designed to provide thrust control ranging from full forward thrust to full reverse thrust. The thrust control in landing-approach configurations formed the major portion of the study. Results were obtained with both leading- and trailing-edge high-lift devices.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-786 , A-450
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  • 41
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    Nomographic Solution of the Momentum Equation for VTOL-STOL Aircraft (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: VTOL-STOL aircraft are characterized in general by the fact that in some portion of their flight envelope the wake is sharply inclined to the free stream. Under such conditions, the usual small-angle assumptions used in determining the induced velocities, and consequently, the power required, are no longer valid. Indeed, the use of small-angle assumptions leads to such anomalous results as infinite induced velocities and required power in the extreme case of hovering. The aforementioned difficulties may be avoided by a more complete examination of the horizontal and vertical momentum imparted to the air by the aircraft at low speeds. The resulting equation is a quartic in the induced velocity, and, as such, is difficult to apply. On the other hand, this quartic can be solved in its most general terms and the resulting solution then can be derived and presented in the form of a chart, or nomograph, from which the required induced velocities my be read directly. This paper presents such a chart.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-814 , L-1479
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  • 42
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    Analytical Method of Approximating the Motion of a Spinning Vehicle with Variable Mass and Inertia Properties Acted Upon by Several Disturbing Parameters (1961)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: An analytical method has been developed which approximates the dispersion of a spinning symmetrical body in a vacuum, with time-varying mass and inertia characteristics, under the action of several external disturbances-initial pitching rate, thrust misalignment, and dynamic unbalance. The ratio of the roll inertia to the pitch or yaw inertia is assumed constant. Spin was found to be very effective in reducing the dispersion due to an initial pitch rate or thrust misalignment, but was completely Ineffective in reducing the dispersion of a dynamically unbalanced body.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TR-R-110
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  • 43
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    Aerodynamic Characteristics of a Large-Scale Model with a High Disk-Loading Lifting Fan Mounted in the Fuselage (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation was conducted to determine the longitudinal characteristics during low-speed flight of a large-scale VTOL airplane model with a direct lifting fan enclosed in the fuselage. The model had a shoulder-mounted unswept wing of aspect ratio 5. The effect on longitudinal characteristics of fan operation, propulsion by means of deflecting the fan efflux, trailing-edge flap deflection, and horizontal-tail height were studied.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-775 , A-540
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  • 44
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    Method for Calculating Induced Velocities at the Blades of a Slightly Inclined Propeller with Constant Circulation (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A method for calculating the induced velocities at the blades of an inclined propeller is presented. The calculations are based upon an assumed wake consisting of one skewed helical vortex per blade. The blade circulation is assumed constant with respect to both radial and azimuth positions. The restriction of uniform radial circulation can be removed by superposition; however, the assumption of constant azimuth-wise circulation restricts the analysis to small propeller inclinations. Numerical values have been obtained for one wake skew angle. These values indicate large effects due to wake vortex spacing and to the number of blades.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-818 , L-1392
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  • 45
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    Some Recent Studies in Structural Dynamics of Rotor Aircraft (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: This paper presents a summary of four recent studies relating to the structural-dynamics problems of rotor-powered aircraft. The first study concerns the measurement by means of dynamic models of the forces and moments at the hubs of various rotor configurations. study show that the periodic components of the forces and moments are highly dependent on both the rotor configuration and the flight condition. The results of this The second study treats the problem of resonance amplifications of rotor-blade stress and shows that by using multiple flapping hinges or flex-joints it is possible to control the natural frequencies of the rotor blade so that conditions of resonance between the frequencies of the aerodynamic input forces and the natural frequencies of the lower blade modes are avoided for all rotor speeds. Two studies of the stability of rotor aircraft axe also discussed. One of these involves the mechanical instability or ground resonance of rotorcraft wherein the rotor support in each of two mutually perpendicular directions in the rotor plane is represented as a multiple-degree-of- freedom system in contrast to the system having a single degree of free- dom normally used in helicopter analysis. The consideration of the rotor support system as a two-degree-of-freedom system predicts additional unstable ranges of rotor speed not predicted by former analyses. The other instability treated is propeller whirl for which the significant motions are the pitching and yawing motions of the propeller disk which are coupled together by gyroscopic forces.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-737 , L-1431
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  • 46
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    Aerodynamic Loads at Mach Numbers from 0.70 to 2.22 on a Airplane Model Having a Wing and Canard of Triangular Plan Form and Either Single or Twin Vertical Tails (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Results of an investigation of the aerodynamic loads on a canard airplane model are presented without detailed analysis for the Mach number range of 0.70 t o 2.22. The model consisted of a triangular wing and canard of aspect ratio 2 mounted on a Sears-Haack body of fineness ratio 12.5 and either a single body-mounted vertical tail or twin wing mounted vertical tails of low aspect ratio and sweptback plan form. The body, right wing panel, single vertical tail, and left twin vertical tail were instrumented for measuring pressures. Data were obtained for angles of attack ranging from -4 degrees to +16 degrees, nominal canard deflection angles of 0 degrees and 10 degrees, and angles of sideslip of 0 degrees and 5.3 degrees. The Reynolds number was 2.9 x 10(exp 6) based on the wing mean aerodynamic chord. Selected portions of the data are presented in graphical form and attention is directed to some of the results of the investigation. All of the experimental results have been tabulated in the form of pressure coefficients and integrations of the pressure coefficients and are available as supplements to this paper. A brief summary of the contents of the tabular material is given.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-690 , A-417
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  • 47
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    Rocket-Model Investigation of Lateral Stability Characteristics and Power Effects of a Jet-Engine Airplane Configuration with Tail Boom at Mach Numbers from 1.15 to 1.37 (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Results from a limited research program initiated to study the effects of a hot propulsive jet on the lateral stability characteristics of a fighter-type airplane configuration are presented. The data were obtained on a rocket-boosted free-flight model and a Mach number range from 1.15 to 1.37 was covered. The configuration tested had sweptback-wing and tail surfaces and a tail boom of rectangular cross section. A solid-propellant rocket motor was used to simulate a turbojet engine with afterburner operating. Pulse rockets provided yaw disturbances during both power-on and power-off flight.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-638 , L-772
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  • 48
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    A Preliminary Study of V/STOL Transport Aircraft and Bibliography of NASA Research in the VTOL-STOL Field (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: This group of papers was prepared by the staff of the Langley Research Center to assist in planning for future commercial air-transport facilities in the New York metropolitan area. Areas of particular interest were predictions regarding the types of V/STOL aircraft that are likely to be developed for various commercial transport applications, estimates of the performance and probable operating procedures for such aircraft, and the approximate dates these aircraft could be available for use. Although the NASA has made no comprehensive studies of this type, the extensive research program in the VTOL-STOL field during the last 10 years appeared to provide a source for some of the desired information . The five papers included herein were therefore prepared to summarize pertinent available material in a form suitable for the intended use. In several instances, new studies and analysis were required to provide the necessary information, but because of a time deadline, many of the significant points received only a cursory examination. For example, much of the quantitative data used in the papers for making generalized comparisons was obtained by approximate methods and is not considered appropriate for use in applications where precise estimates are required. It should be recognized, then, that the treatment of the V/STOL transport provided by this group of papers is necessarily of a preliminary nature.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-624 , L-1054 , L-1058
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  • 49
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    Effects of Boattailing and Nozzle Extension on the Thrust-Minus-Drag of a Multiple-Jet Configuration (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A wind-tunnel investigation of the effects of both boattailing and nozzle extension on the thrust-minus-drag of clustered-jet configurations has been conducted at Mach numbers from 0.60 to 1.40 and jet total-pressure ratios from 3 to 20. Three different boattails were tested: an 8 deg conical afterbody, a 16 deg circular-arc afterbody, and a third afterbody having a linear area variation with length. A cylindrical afterbody also was tested for comparison purposes. Extending from these bodies are four circular jet nozzles with a design Mach number of 2.5 which were spaced symmetrically about the body center line. The results indicated that an 8 deg conical afterbody provided the highest net thrust efficiency factors of the four models tested when the nozzle exits were at the optimum longitudinal location in each case. The other afterbodies in order of decreasing performance were the 16 deg circular-arc, the straight-line-area-distribution, and the cylindrical.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-887 , L-862
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  • 50
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    Effects of Gyroscopic Cross Coupling between Pitch and Roll on the Handling Qualities of VTOL Aircraft (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: In order to provide information relative to the effects of gyroscopic cross coupling between pitch and roll on the handling qualities of VTOL aircraft, a flight investigation has been conducted during which cross coupling was simulated. Generality is achieved by presenting the results of the flight investigation in the form of a criterion which may be used t o predict the acceptability of the level of cross coupling in VTOL aircraft as a function of the aircraft design parameters. The criterion is based on pilot's opinions of the acceptability of the motions for the range of cross coupling which was simulated during a maneuver in which cross coupling is particularly objectionable. is used to provide a basis for application of the criterion. The theory which i s developed is shown to predict accurately the aircraft motions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-812
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  • 51
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    Flight Investigation of Effects of Selected Operating Conditions on the Bending and Torsional Moments Encountered by a Helicopter Rotor Blade (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Flight tests have been conducted with a single-rotor helicopter to determine the effects of partial-power descents with forward speed, high-speed level turns, pull-outs from autorotation, and high-forward-speed high-rotor-speed autorotation on the flapwise bending and torsional moments of the rotor blade. One blade of the helicopter was equipped at 14 percent and 40 percent of the blade radius with strain gages calibrated to measure moments rather than stresses. The results indicate that the maximum moments encountered in partial-power descents with forward speed tend to be generally reduced from the maximum moments encountered during partid-power descents at zero forward speed. High-speed level turns and pull-outs from auto-rotation caused retreating-blade stall which produced torsional moments (values up to 2,400 inch-pounds). at the 14-percent-radius station that were as large as those encountered during the previous investigations of retreating-blade stall (values up t o 2,500 inch-pounds). High-forward- speed high-rotor-speed autorotation produced flapwise bending moments (values up to 7,200 inch-pounds) at the 40-percent-radius station which were as large as the flapwise bending moments (values up to 7,800 inch-pounds) a t the 14-percent-radius station encountered during partial - power vertical descents. The results of the present investigation (tip-speed ratios up to 0.325 and an unaccelerated level-flight mean lift coefficient of about 0.6), in combination with the related results of at zero forward speed produce the largest rotor-blade vibratory moments. However, inasmuch as these large moments occur only during 1 percent of the cycles and 88 percent of the cycles are at moment values less than 70 percent of these maximum values in partial-power descents, other conditions, such as high-speed flight where the large moments are combined with large percentages of time spent,must not be neglected in any rotor-blade service-life assessment.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-759 , L-1291
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  • 52
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    Operational Technique for Transition of Several Types of V/Stol Aircraft (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Flight test experience has been obtained with five test bed aircraft which employed widely differing principles of V/STOL operation. speeds these aircraft were supported by wing lift and in the hovering condition they were supported by engine-produced thrust. used to transfer the lift from the wing to the engine are examined. primary items considered in the transition region are longitudinal trim changes, stability , stalled flow during descending transitions, and the flexibility of the transition procedure of each type of aircraft.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TN-D-774 , L-1418
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  • 53
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    Surface Pressures and Heat Transfer on Unswept Blunt Plates in Helium at High Mach Numbers (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Pressure distributions and local convective heat-transfer coefficients on a flat plate at zero angle of attack were measured in helium. Data were obtained with various amounts of leading-edge bluntness at Mach numbers of 12.5 and 14.7. The pressures on a sharp leading-edged plate were not influenced by the leading edge and were predicted by the first-order, hypersonic, weak-interaction theory. Pressures on blunt plates were correlated by introducing the leading-edge Reynolds number as a parameter. Measured heat-transfer coefficients on the sharp plate agreed with predictions obtained form existing exact solutions for hear transfer across the laminar boundary layer. For the blunt plates a comparison of theory with experiment indicated that more knowledge of the flow field between the sock wave and plate surface is necessary before an adequate prediction of convective heat transfer can be made. Shock-wave shapes for the blun plates at a Mach number 12.5 and zero angle of attack were measured. At distances between 2 and 60 leading-edge thicknesses from the shock vertex, the shock-wave shapes were found to be represented by a modified form of the blast-wave analogy.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-688 , A-417
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  • 54
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    Applications of Power Spectral Analysis Methods to Maneuver Loads Obtained on Jet Fighter Airplanes During Service Operations (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Power spectral densities of normal load factor have been obtained for two service operational training flights of a Republic F-84G airplane and three service operational training flights of a North American F-86A airplane in order to indicate the load-factor frequency content and possible uses of power spectral methods in analyzing maneuver load data. It was determined that the maneuvering load-factor time histories appeared to be described by a truncated normal distribution. The power spectral densities obtained were relatively level at frequencies below 0.03 cycle per second and varied inversely with approximately the cube of the frequency at the higher frequencies. In general, the frequency content was very low above 0.2 cycle per second. The load-factor peak distributions were estimated fairly well from the spectrum analysis. In addition, peak load data obtained during service operations of fighter-type airplanes with flight time totaling about 24,000 hours were examined and appeared to agree reasonably well with the type of equations obtained from spectrum peak-load distributions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-902 , L-1557
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  • 55
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    Analysis of X-15 Landing Approach and Flare Characteristics Determined from the First 30 Flights (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: The approach and flare maneuvers for the first 30 flights of the X-15 airplane and the various control problems encountered are discussed. The results afford a relatively good cross section of landing conditions that might be experienced with future glide vehicles having low lift-drag ratios. Flight-derived drag data show that preflight predictions based on wind-tunnel tests were, in general, somewhat higher than the values measured in flight. Depending on configuration, the peak lift-drag ratios from flight varied from 3.5 to 4.5 as compared with a predicted range of from 3.0 to 4.2. By employing overhead, spiral-type patterns beginning at altitudes as high as 40,000 feet, the pilots were consistently able to touch down within about +/-1,000 feet of a designated point. A typical flare was initiated at a "comfortable" altitude of about 800 feet and an indicated airspeed of approximately 300 knots., which allowed a margin of excess speed. The flap and gear were extended when the flare was essentially completed, and an average touchdown was accomplished at a speed of about 185 knots indicated airspeed, an angle of attack of about 7 deg, and a rate of descent of about 4 feet per second. In general, the approach and landing characteristics were predicted with good accuracy in extensive preflight simulations. F-104 airplanes which simulated the X-15 landing characteristics were particularly valuable for pilot training.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-1057 , H-221
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  • 56
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    A Flight Examination of Operating Problems of V/STOL Aircraft in STOL-Type Landing and Approach (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A flight investigation has been conducted using a large twin-engine cargo aircraft to isolate the problems associated with operating propeller-driven aircraft in the STOL speed range where appreciable engine power is used to augment aerodynamic lift. The problems considered would also be representative of those of a large overloaded VTOL aircraft operating in an STOL manner with comparable thrust-to-weight ratios. The study showed that operation at low approach speeds was compromised by the necessity of maintaining high thrust to generate high lift and yet achieving the low lift-drag ratios needed for steep descents. The useable range of airspeed and flight path angle was limited by the pilot's demand for a positive climb margin at the approach speed, a suitable stall margin, and a control and/or performance margin for one engine inoperative. The optimum approach angle over an obstacle was found to be a compromise between obtaining the shortest air distance and the lowest touchdown velocity. In order to realize the greatest low-speed potential from STOL designs, the stability and control characteristics must be satisfactory.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-862 , A-503
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  • 57
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    Effect of Ratio of Jet Area to Total Area and of Pressure Ratio on Lift Augmentation of Annular Jets in Ground Effect Under Static Conditions (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The present investigation was undertaken to determine the effects of the ratio of jet area to total area and of the pressure ratio on the lift-augmentation characteristics of annular jets in ground effect. The investigation was made over an area-ratio range of 1.00 to 0.02 and a pressure-ratio range of about 1.04 to 1.95. Several configurations with center jets were tested through an angle-of-attack range to determine the pitching-moment characteristics. The tests were conducted in a static test room with the use of the compressed-air facilities. The results show that lift augmentation increases somewhat as the area ratio is reduced to about 0.10, below which it deteriorates due to thin jet mixing. The effect of pressure ratio on lift was negligible for the area-ratio range investigated. Calculations of the lift per air horsepower for a given base loading indicate that the greatest lift per air horsepower occurs at area ratios above 0.10, where the greatest lift augmentation occurs. The data show that annular-Jet vehicles are unstable at ratios of height above ground to nozzle diameter above about 0.10. The stability of the annular-jet vehicle can be improved by the use of large center jets. Base compartments also reduces the unstable moment.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-720 , L-1281
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  • 58
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    Investigation of Net-Thrust and Base-Pressure Characteristics of Cylindrical Afterbodies with Clustered Supersonic Nozzles at Transonic Mach Numbers (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A wind-tunnel investigation has been conducted at Mach numbers from 0.9 to 1.4 to determine the net-thrust and base-pressure characteristics of cylindrical afterbodies having clustered supersonic nozzles. The design Mach numbers of the nozzles were 2.0 and 2.5 and the number of clustered nozzles ranged from two to six. The nozzles had throat-to- base diameter ratios of 0.155, 0.225, 0.278, and 0.320. Some models were tested with various configurations of extended, shrouded, flush, and canted nozzles. The nozzles discharged unheated air from the base at ratios of jet total pressure to free-stream static pressure ranging from 1 to approximately 20. The results of this investigation showed that both the ratio of total exit area to base area and the number of jets affect the net-thrust factor to a significant degree for the extended-nozzle configurations. Good net-thrust factors were obtained with all the model configurations near the design jet total-pressure ratio; however, the extended-nozzle configuration had the highest net-thrust factor over the test jet total- pressure-ratio range. Canting the twin nozzles outward resulted in a favorable thrust factor over a limited jet total-pressure-ratio range, and surrounding the nozzles with a single shroud reduced thrust factors for the range of jet total-pressure ratio of this investigation.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-978 , L-1165
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  • 59
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    Hovering Characteristics of a Rotor having an Airfoil Section Designed for Flying-Crane Type of Helicopter (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Results of an investigation, conducted on the Langley helicopter test tower, of a rotor having an NACA 632A015 airfoil thickness distribution in combination with an NACA 230 mean line are presented. Comparison with a previously reported test of a symmetrical rotor blade efficiency was substantially improved over a wide range of tip Mach numbers. The maximum mean lift coefficient was essentially unchanged from that obtained with uncambered blades. Some data showing the effect of a distributed type of leading-edge roughness are also included.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-742 , L-1187
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  • 60
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    Application of Monte Carlo Technique for Determining Maneuvering Loads from Statistical Information on Airplane Motions (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Results of a statistical analysis of horizontal-tail loads on a fighter airplane are presented. The data were obtained from a number of operational training missions with flight at altitudes up to about 50,000 feet and at Mach numbers up to 1.22. The analysis was performed to determine the feasibility of calculating horizontal-tail load from data on the flight conditions and airplane motions. In the analysis the calculated loads are compared with the measured loads for the different types of missions performed. The loads were calculated by two methods: a direct approach and a Monte Carlo technique. The procedures used and some of the problems associated with the data analysis are discussed. frequencies of occurrence of tail loads of given magnitudes are derived from statistical information on the flight quantities. In the direct method, a time history of tail load is calculated from time-history measurements of the flight quantities. The Monte Carlo method could be useful for extending loads information for design of prospective airplanes . For the Monte Carlo method, the The results indicate that the accuracy of loads, regardless of the method used for calculation, is largely dependent on the knowledge of the pertinent airplane aerodynamic characteristics and center-of-gravity location. In addition, reliable Monte Carlo results require an adequate sample of statistical data and a knowledge of the more important statistical dependencies between the various flight conditions and airplane motions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TN-D-524 , L-988
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  • 61
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    Theoretical Evaluation of the Pressures, Forces, and Moments at Hypersonic Speeds Acting on Arbitrary Bodies of Revolution Undergoing Separate and Combined Angle-of-attack and Pitching Motions (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Equations based on Newtonian impact theory have been derived and a computational procedure developed with the aid of several design-type charts which enable the determination of the aerodynamic forces and moments acting on arbitrary bodies of revolution undergoing either separate or combined angle-of-attack and pitching motions. Bodies with axially increasing and decreasing cross-sectional area distributions are considered; nose shapes may be sharp, blunt, or flat faced. The analysis considers variations in angle of attack from -90 degrees to 90 degrees and allows for both positive and negative pitching rates of arbitrary magnitude. The results are also directly applicable to bodies in either separate or combined sideslip and yawing maneuvers.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-652 , L-1225
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  • 62
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    Aerodynamic Loads at Mach Numbers from 0.70 to 2.22 on an Airplane Model Having a Wing and Canard of Triangular Plan Form and Either Single or Twin Vertical Tails (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Tabulated results of a wind-tunnel investigation of the aerodynamic loads on a canard airplane model with twin vertical tails are presented for Mach numbers from 0.70 to 2.22. The Reynolds number for the measurements was 2.9 x 10(exp 6) based on the wing mean aerodynamic chord. The results include local static-pressure coefficients measured on the wing, body, and one of the vertical tails for angles of attack from -4 degrees to 16 degree angles of sideslip of 0 degrees and 5.3 degrees, and nominal canard deflections of O degrees and 10 degrees. Also included are section force and moment coefficients obtained from integrations of the local pressures and model-component force and moment coefficients obtained from integrations of the section coefficients. Geometric details of the model are shown and the locations of the pressure orifices are shown. An index to the data contained herein is presented and definitions of nomenclature are given. Detailed descriptions of the model and experiments and a brief discussion of some of the results are given. Tabulated results of measurements of the aerodynamic loads on the same canard model but having a single vertical tail instead of twin vertical tails are presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-690-II , A-417
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    A Design Study of the Inflated Sphere Landing Vehicle, Including the Landing Performance and the Effects of Deviations from Design Conditions (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The impact motion of the inflated sphere landing vehicle with a payload centrally supported from the spherical skin by numerous cords has been determined on the assumption of uniform isentropic gas compression during impact. The landing capabilities are determined for a system containing suspension cords of constant cross section. The effects of deviations in impact velocity and initial gas temperature from the design conditions are studied. Also discussed are the effects of errors in the time at which the skin is ruptured. These studies indicate how the design parameters should be chosen to insure reliability of the landing system. Calculations have been made and results are presented for a sphere inflated with hydrogen, landing on the moon in the absence of an atmosphere. The results are presented for one value of the skin-strength parameter.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-692
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  • 64
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    Supersonic Panel Flutter Test Results for Flat Fiber-Glass Sandwich Panels with Foamed Cores (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Flutter tests have been made on flat panels having a 1/4 inch-thick plastic-foam core covered with thin fiber-glass laminates. The testing was done in the Langley Unitary Plan wind tunnel at Mach numbers from 1.76 t o 2.87. The flutter boundary for these panels was found to be near the flutter boundary of thin metal panels when compared on the basis of an equivalent panel stiffness. The results also demonstrated that the depth of the cavity behind the panel has a pronounced influence on flutter. Changing the cavity depth from 1 1/2 inches to 1/2 inch reduced the dynamic pressure at start of flutter by 40 percent. No flutter was obtained when the spacers on the back of the panel were against the bottom of the cavity.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-827 , L-1373
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  • 65
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    STOL Characteristics of a Propeller-Driven, Aspect-Ratio-10, Straight-Wing Airplane with Boundary-Layer Control Flaps, as Estimated from Large-Scale Wind-Tunnel Tests (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A study is presented of the improvements in take-off and landing distances possible with a conventional propeller-driven transport-type airplane when the available lift is increased by propeller slipstream effects and by very effective trailing-edge flaps and ailerons. This study is based on wind-tunnel tests of a 45-foot span, powered model, with BLC on the trailing-edge flaps and controls. The data were applied to an assumed airplane with four propellers and a wing loading of 50 pounds per square foot. Also included is an examination of the stability and control problems that may result in the landing and take-off speed range of such a vehicle. The results indicated that the landing and take-off distances could be more than halved by the use of highly effective flaps in combination with large amounts of engine power to augment lift (STOL). At the lowest speeds considered (about 50 knots), adequate longitudinal stability was obtained but the lateral and directional stability were unsatisfactory. At these low speeds, the conventional aerodynamic control surfaces may not be able to cope with the forces and moments produced by symmetric, as well as asymmetric, engine operation. This problem was alleviated by BLC applied to the control surfaces.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-1032 , A-423
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  • 66
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    Investigation of Low-Subsonic Flight Characteristics of a Model of a Hypersonic Boost-Glide Configuration Having a 78 deg. Delta Wing (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An investigation of the low-subsonic stability and control characteristics of a model of a hypersonic boost-glide configuration having 78 deg. sweep of the leading edge has been made in the Langley full-scale tunnel. The model was flown over an angle-of-attack range from 10 to 35 deg. Static and dynamic force tests were made in the Langley free-flight tunnel. The investigation showed that the longitudinal stability and control characteristics were generally satisfactory with neutral or positive static longitudinal stability. The addition of artificial pitch damping resulted in satisfactory longitudinal characteristics being obtained with large amounts of static instability. The most rearward center-of-gravity position for which sustained flights could be made either with or without pitch damper corresponded to the calculated maneuver point. The lateral stability and control characteristics were satisfactory up to about 15 deg. angle of attack. The damping of the Dutch roll oscillation decreased with increasing angle of attack; the oscillation was about neutrally stable at 20 deg. angle of attack and unstable at angles of attack of about 25 deg. and above. Artificial damping in roll greatly improved the lateral characteristics and resulted in flights being made up to 35 deg. angle of attack.
    Keywords: Aircraft Design, Testing and Performance
    Type: L-452
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    Summary of V-G and VGH Data Collected on Lockheed Electra Airplanes During Airplane Operations (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Data obtained by NASA VGH and V-G recorders on several Lockheed Electra airplanes operated over three domestic routes have been analyzed to determine the in-flight accelerations, airspeed practices, and landing accelerations experienced by this particular airplane. The results indicate that the accelerations caused by gusts and maneuvers are comparable to corresponding results for piston-engine transport airplanes. Oscillatory accelerations (apparently caused by the autopilot or control system) appear to occur about one-tenth as frequently as accelerations due to gusts. Airspeed operating practices in rough air generally follow the trends shown by piston-engine transports in that there is no significant difference between the average airspeed in rough or smooth air. Placard speeds were exceeded more frequently by the Electra airplane than by piston-engine transport airplanes. Generally, the landing-impact accelerations were higher than those for piston-engine transports.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-SX-523 , L-1467
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    Some Information of the Operational Experiences of Turbine-Powered Commercial Transports (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: This report presents a brief discussion of some information on the operational experiences noted on VGH records from six types of turbine- powered commercial transport aircraft. These flight characteristics cover oscillatory motions, maneuver accelerations, sinking speeds, placard speed exceedances, and miscellaneous or unusual flight events.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-SX-595 , L-1696
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  • 69
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    Flight-Path Characteristics for Decelerating From Supercircular Speed (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Characteristics of the following six flight paths for decelerating from a supercircular speed are developed in closed form: constant angle of attack, constant net acceleration, constant altitude" constant free-stream Reynolds number, and "modulated roll." The vehicles were required to remain in or near the atmosphere, and to stay within the aerodynamic capabilities of a vehicle with a maximum lift-drag ratio of 1.0 and within a maximum net acceleration G of 10 g's. The local Reynolds number for all the flight paths for a vehicle with a gross weight of 10,000 pounds and a 600 swept wing was found to be about 0.7 x 10(exp 6). With the assumption of a laminar boundary layer, the heating of the vehicle is studied as a function of type of flight path, initial G load, and initial velocity. The following heating parameters were considered: the distribution of the heating rate over the vehicle, the distribution of the heat per square foot over the vehicle, and the total heat input to the vehicle. The constant G load path at limiting G was found to give the lowest total heat input for a given initial velocity. For a vehicle with a maximum lift-drag ratio of 1.0 and a flight path with a maximum G of 10 g's, entry velocities of twice circular appear thermo- dynamically feasible, and entries at velocities of 2.8 times circular are aerodynamically possible. The predominant heating (about 85 percent) occurs at the leading edge of the vehicle. The total ablated weight for a 10,000-pound-gross-weight vehicle decelerating from an initial velocity of twice circular velocity is estimated to be 5 percent of gross weight. Modifying the constant G load flight path by a constant-angle-of-attack segment through a flight- to circular-velocity ratio of 1.0 gives essentially a "point landing" capability but also results in an increased total heat input to the vehicle.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-1091 , E-1001
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  • 70
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    Rapid-Transition Tests of a 1/4-Scale Model of the VZ-2 Tilt-Wing Aircraft (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation of the longitudinal stability and control characteristics of a 1/4-scale model of the VZ-2 tilt-wing vertical-take-off- and-landing aircraft during rapid transitions has been made on the Langley control-line facility. Only the longitudinal characteristics were studied because with the control-line technique the other phases of the model motion are partially restrained. The rapid transitions from hovering to forward flight could be performed easily at any of the accelerations attempted; whereas, the transitions from forward flight to hovering were generally accompanied by a strong nose up pitching moment which at times was uncontrollable because of an inadequate amount of available pitch control. The model was more difficult to control during rapid decelerations than during slow decelerations and was also more difficult to control for rearward center-of-gravity conditions than for forward ones.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-946 , L-1683
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  • 71
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    An Investigation of Landing-Contact Conditions for Two Large Turbojet Transports and a Turboprop Transport During Routine Daylight Operations (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: The National Aeronautics and Space Administration has recently completed a statistical investigation of landing-contact conditions for two large turbojet transports and a turboprop transport landing on a dry runway during routine daylight operations at the Los Angeles International Airport. Measurements were made to obtain vertical velocity, airspeed, rolling velocity, bank angle, and distance from the runway threshold, just prior to ground contact. The vertical velocities at touchdown for one of the turbojet airplanes measured in this investigation were essentially the same as those measured on the same type of airplane during a similar investigation (see NASA Technical Note D-527) conducted approximately 8 months earlier. Thus, it appeared that 8 months of additional pilot experience has had no noticeable tendency toward lowering the vertical velocities of this transport. Distributions of vertical velocities for the turbojet transports covered in this investigation were similar and considerably higher than'those for the turboprop transport. The data for the turboprop transport were in good agreement with the data for the piston-engine transports (see NACA Report 1214 and NASA Technical Note D-147) for all the measured parameters. For the turbojet transports, 1 landing in 100 would be expected to equal or exceed a vertical velocity of approximately 4.2 ft/sec; whereas, for the turboprop transport, 1 landing in 100 would be expected to equal or exceed 3.2 ft/sec. The mean airspeeds at touchdown for the three transports ranged from 22.5 percent to 26.6 percent above the stalling speed. Rolling velocities for the turbojet transports were considerably higher than those for the turboprop transport. Distributions of bank angles at contact for the three transports were similar. For each type of airplane, 1 landing in 100 would be expected to equal or exceed a bank angle at touchdown of approximately 3.0 deg. Distributions of touchdown distances for the three transports were also quite similar. Touchdown distances from the threshold for 1 landing in 100 ranged from 2,500 feet for the turboprop transport to 2,800 feet for one of the turbojet transports.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-899 , L-1528
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  • 72
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    Permeability studies on the red blood cell of the ground-hog, Marmota monaxThis work was done at the Marine Biological Laboratory, Woods Hole, Mass. and supported by the Whitehall Foundation. (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961), S. 1-3 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 1 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030570102
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    The endogenous tissue respiration of the Arctic ground squirrel as affected by hibernation and seasonThe views expressed are those of the authors and do not necessarily represent official Air Force policy. The experiments were conducted according to the “Rules Regarding Animal Care” as established by the American Medical Association (Air Force Regulation 160-94). (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961), S. 5-10 
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    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 2 Tab.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030570103
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    Studies on the localization of cholinesterase in various types of muscle (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961), S. 63-71 
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    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 3 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030570202
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    Investigations on the physiological role of myosincholinesterase in phylogenesis (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961), S. 73-79 
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    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 3 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030570203
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    Ca45 uptake by dog erythrocytes suspended in sodium and potassium chloride solutionsThis investigation was supported by a P.H.S. grant (H-4155) from the National Heart Institute, Public Health Service. (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961), S. 95-100 
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    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 1 Ill.
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    URL: http://dx.doi.org/10.1002/jcp.1030570206
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    Epinephrine and the latency of muscular contractionAided by grant B-1657 from the National Institutes of Health, Bethesda, Md. (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 58 (1961), S. 35-47 
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    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 10 Ill.
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    URL: http://dx.doi.org/10.1002/jcp.1030580106
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    Quantitative measurements of changes in mouse skin following a single dose of ultraviolet light (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 58 (1961), S. 81-96 
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    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 8 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030580109
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    Quantitative analysis of epidermal hyperplasia in mouse skin following single doses of ultraviolet light (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 58 (1961), S. 97-110 
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    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 7 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030580110
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    A quantitative study of the distribution pattern of certain oxidizing enzymes and a lipase in the red and white fibers of the pigeon breast muscle (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 58 (1961), S. 253-260 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 3 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030580306
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    Masthead (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 58 (1961) 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030580401
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    Introduction (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 58 (1961), S. VII 
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    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030580402
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    Reversibility of X irradiation-induced effects in dry biological systemsThis work was performed under the auspices of the United States Atomic Energy Commission. (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 58 (1961), S. 13-25 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 7 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030580404
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    Masthead (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961) 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030570101
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    Some aspects of the electroretinographic response of the American red squirrel, Tamiosciurus hudsonicus loquax (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961), S. 11-19 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 8 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030570104
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    Reversible and irreversible changes in normal human thrombocyte membranes by slow and rapid swelling (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961), S. 21-28 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 1 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030570105
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    The exchange of radioactive magnesium in erythrocytes of several species (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961), S. 119-121 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 4 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030570209
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    Masthead (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961) 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030570301
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    On body size and tissue respiration (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961), S. 135-147 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 6 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030570302
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    Reflex relationships of the abdominal stretch receptors of the crayfish. II. Stretch receptor involvement during the swimming reflexThis paper and the one preceeding it (Eckert, 1961) comprise part of a thesis presented in partial fulfillment of the requirements for the degree of Doctor of Philosophy at Columbia University.This investigation was supported in part by U.S.P.H.S. grant E-2271 (C1) and fellowship BF-8653 (C1). (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961), S. 163-174 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 3 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030570304
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    The effect of stretch on the conduction velocity of single nerve fibers in Aplysia (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961), S. 185-191 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 5 Ill.
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    URL: http://dx.doi.org/10.1002/jcp.1030570306
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    Calcium influx in frog rectus abdominus muscle at rest and during potassium contracture (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961), S. 193-202 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 3 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030570308
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    Retention of urea by frog and mammalian kidney slices in vitroThis work was supported by a grant-in-aid from the American Heart Association. (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961), S. 211-219 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 3 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030570310
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    The free running period of the bat clock; seasonal variations at low body temperatureThis paper is part of a thesis presented to the Department of Biology of Princeton University (unpublished) in partial fulfillment of the requirements for the degree of Doctor of Philosophy.This investigation was supported, in part, by Fellowship no. EF-9327 from the National Institute of Allergy and Infectious Diseases, U. S. Public Health Service. This work was also supported by a grant from the Office of Naval Research (Nonr. 1858 (28)) to C. S. Pittendrigh and by funds from the Eugene Higgins Trust Fund allocated to Princeton University. (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961), S. 81-86 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 3 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030570204
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    Asphyxial changes in the cerebellar cortexThis investigation was supported in part by grant Rg-6965 from the United States Public Health Service. (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 57 (1961), S. 101-110 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 3 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030570207
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    The structure of slow and fast extrafusal muscle fibers in the extraocular muscles and their nerve endings in guinea pigs (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 58 (1961), S. 63-79 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030580108
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    Masthead (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 58 (1961) 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030580201
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    Microelectrode study of taste receptors of rat and hamsterThis research was supported by the National Science Foundation. (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 58 (1961), S. 131-139 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 6 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030580204
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    Cortical intracellular synaptic potentials (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 58 (1961), S. 153-167 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 11 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030580206
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    Cytochromes of marine invertebrates (1961)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 58 (1961), S. 185-194 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 2 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030580210
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