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  • Chemistry  (4,705)
  • Aircraft Design, Testing and Performance  (43)
  • Analytical Chemistry and Spectroscopy
  • Chemical Engineering
  • 1940-1944  (4,748)
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  • 1
    Publication Date: 2013-08-31
    Description: Development work on an arrangement using ailerons and spoilers for lateral control was carried out by the Vought-Sikorsky Aircraft Division of the United Aircraft Corporation on a small commercial airplane in flight and on an airfoil in a wind tunnel. Spoiler hinge moments were reduced by aerodynamic balance. The arrangement was then built into an experimental airplane and further improvements were adopted as the result of flight and tunnel tests. The use of ailerons for lateral control with flaps up, spoilers with flaps full down, and gradual transition as the flaps are lowered was found to provide lateral control under the flight conditions for which they were best suited. The ailerons were of short span, permitting the use of long-span flaps, and were drooped to a relatively large angle when the flaps were deflected. A high maximum lift coefficient was thus attained. With large control deflections in the intermediate flap-angle range and spoiler effectiveness near neutral improved by "ventilating" the spoiler, the lateral control was satisfactory for the experimental airplane and was a definite improvement over that of a conventional control arrangement.
    Keywords: Aircraft Design, Testing and Performance
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  • 2
    Publication Date: 2018-06-05
    Description: An investigation has been conducted on a full-scale model of the proposed XP-46 airplane in the N. A. C. A. full-scale wind tunnel pursuant to the request of the Amy Air Corps, Materiel Division. The primary purpose of the investigation was to determine the optimum arrangement of the various component parts to obtain the maximum high speed and to provide adequate engine cooling. Additional tests included a determination of the stalling characteristics and the effectiveness of ailerons and elevators. The profile drag of the wing was ascertained by the momentum method; the location of the transition point on the wing and the critical compressibility velocities of the various airplane components were determined from surface pressure surveys.
    Keywords: Aircraft Design, Testing and Performance
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  • 3
    Publication Date: 2018-06-05
    Description: An extensive series of wind-tunnel tests on a half-scale conventional, nacelle model were made by the United Aircraft Corporation to determine and correlate the effects of many variables on cooling air flow and nacelle drag. The primary investigation was concerned with the reaction of these factors to varying conditions ahead of, across, and behind the engine. In the light of this investigation, common misconceptions and factors which are frequently overlooked in the cooling and cowling of radial engines are considered in some detail. Data are presented to support certain design recommendations and conclusions which should lead toward the improvement of present engine installations. Several charts are included to facilitate the estimation of cooling drag, available cooling pressure, and cowl exit area.
    Keywords: Aircraft Design, Testing and Performance
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  • 4
    Publication Date: 2018-06-05
    Description: Experience has shown that the determination of the take-off and. landing characteristics of airplanes requires specialized, equipment of a high degree of precision and reliability and demands great care in the evaluation and interpretation of data. It is believed, therefore, that a description of the apparatus and methods that have been developed by the NACA for these measurements might be of considerable interest, particularly to flight-test groups that have had little experience with landing and. take-off measurements. The basic principles and essential details of the Committee's equipment are described, the methods of utilizing the apparatus and of reducing the data are explained, and sample test results are presented.
    Keywords: Aircraft Design, Testing and Performance
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  • 5
    Publication Date: 2019-06-28
    Description: A study was made of the performance of a jet-propulsion system composed of an engine-driven blower, a combustion chamber, and a discharge nozzle. A simplified analysis is made of this system for the purpose of showing in concise form the effect of the important design variables and operating conditions on jet thrust, thrust horsepower, and fuel consumption. Curves are presented that permit a rapid evaluation of the performance of this system for a range of operating conditions. The performance for an illustrative case of a power plant of the type under consideration id discussed in detail. It is shown that for a given airplane velocity the jet thrust horsepower depends mainly on the blower power and the amount of fuel burned in the jet; the higher the thrust horsepower is for a given blower power, the higher the fuel consumption per thrust horsepower. Within limits the amount of air pumped has only a secondary effect on the thrust horsepower and efficiency. A lower limit on air flow for a given fuel flow occurs where the combustion-chamber temperature becomes excessive on the basis of the strength of the structure. As the air-flow rate is increased, an upper limit is reached where, for a given blower power, fuel-flow rate, and combustion-chamber size, further increase in air flow causes a decrease in power and efficiency. This decrease in power is caused by excessive velocity through the combustion chamber, attended by an excessive pressure drop caused by momentum changes occurring during combustion.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-E-212 , NACA-ACR-E4E06
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  • 6
    Publication Date: 2019-06-28
    Description: Flights were made in natural icing conditions at the NACA Ice Research Project, Minneapolis, Minn. to test several designs of thermal-electric propeller de-icing blade shoes and a hub-generator design. It was found that a minimum average unit power of 2.5 watts per square inch of blade-shoe area would protect the propeller blades at the test conditions. The most satisfactory blade shoe of the three designs tested extended to the 20-percent-chord point and to 90 percent of the blade radius. A concentration of heat in the leading-edge region of this shoe was found to reduce the power input necessary for satisfactory de-icing. A satisfactory thermal design of blade shoe and a hub generator of sufficient capacity were developed.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-A-47 , NACA-ARR-4A20
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  • 7
    Publication Date: 2019-06-28
    Description: The effects of changes in aileron rigging between 2 deg up and 2 deg down on the stick forces were determined from wind-tunnel data for a finite-span wing model. These effects were investigated for ailerons deflecting equally in both directions and linearly with stick deflection. Data were analyzed for a Frise, a sealed internally balanced, and a beveled-trailing-edge aileron. The results of the analysis showed that only ailerons having linear hinge-moment characteristics are unaffected by changes in rigging and indicated that ailerons having decidedly nonlinear hinge-moment-coefficient curves, particularly for deflections near 0 deg, are very sensitive to changes in rigging.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-289 , NACA-RB-L4E11
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  • 8
    Publication Date: 2019-06-28
    Description: Aerodynamic characteristics of a tapered NACA 23012 airfoil with single and double perforated split flaps have been determined in the NACA 7- by 10-foot wind tunnel. Dynamic pressure surveys were made behind the airfoil at the approximate location of the tail in order to determine the extent and location of the wake for several of the flap arrangements. In addition, computations have been made of an application of perforated double split flaps for use as fighter brakes. The results indicated that single or double perforated split flaps may be used to obtain satisfactory dive control without undue buffeting effects and that single or double perforated split flaps may also be used as fighter brakes. The perforated split flaps had approximately the same effects on the aerodynamic and wake characteristics of the tapered airfoil as on a comparable rectangular airfoil.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-373
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  • 9
    Publication Date: 2019-06-28
    Description: Cooling tests were made of a Northrop A-17A attack airplane successively equipped with a conventional.NACA cowling and with a wing-duct cooling system. The method of cooling the engine by admitting air from the propeller slipstream into wing ducts, passing it first through the accessory compartment and then over the engine from rear to front, appeared to offer possibilities for improved engine cooling, increased cooling of the accessories, and better fairing of the power-plant installation. The results showed that ground cooling for the wing duct system without cowl flap was better than for the NACA cowling with flap; ground cooling was appreciably improved by installing a cowl flap. Satisfactory temperatures were maintained in both climb and high-speed flight, but, with the use of conventional baffles, a greater quantity of cooling air appeared to be required for the wing duct system.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-813
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  • 10
    Publication Date: 2019-06-28
    Description: In open box beams subjected to torsion, secondary stresses arise owing to lateral bending of the spar caps. The present paper outlines a simple method for estimating the magnitude of these stresses and gives the results of tests of an open box beam in the neighborhood of a discontinuity where the cover changed from the top to the bottom of the box.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-14 , NACA-ARR-L4I23
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  • 11
    Publication Date: 2019-06-28
    Description: An investigation was carried out in the NACA low-turbulence tunnel to develop low-drag airfoil sections suitable for admitting air at the leading edge. A thickness distribution having the desired type of pressure distribution was found from tests of a flexible model. Other airfoil shapes were derived from this original shape by varying the thickness, the camper, the leading-edge radius, and the size of the leading-edge opening. Data are presented giving the characteristics of the airfoil shapes in the range of lift coefficients for high-speed and cruising flight. Shapes have been developed which show no substantial increases in drag over that of the same position along the chord. Many of these shapes appear to have higher critical compressibility speeds than plain airfoils of the same thickness. Low-drag airfoil sections have been developed with openings in the leading edge as large as 41.5 percent of the maximum thickness. The range of lift coefficients for low drag in several cases is nearly as large as that of the corresponding plain airfoil sections. Preliminary measurements of maximum lift characteristics indicate that nose-opening sections of the type herein considered may not produce any marked effects on the maximum lift coefficient.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-694
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  • 12
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-577 , AD-A801579
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  • 13
    Publication Date: 2019-06-28
    Description: A correlation of what are believed to be the most reliable data available on duct components of aircraft power-plant installations is presented. The information is given in a convenient form and is offered as an aid in designing duct systems and, subject to certain qualifications, as a guide in estimating their performance. The design and performance data include those for straight ducts; simple bends of square, circular, and elliptical cross sections; compound bends; diverging and converging bends; vaned bends; diffusers; branch ducts; internal inlets; and an angular placement of heat exchangers. Examples are included to illustrate methods of applying these data in analyzing duct systems. (author)
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-208 , NACA-ARR-L4F26
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  • 14
    Publication Date: 2018-06-05
    Description: The available test results of internally balanced ailerons have been correlated and summarized herein. Although several variables have yet to-be-investigated, the results presented will be useful in the preliminary design of internally balanced ailerons and in the determination of the most promising modifications to unsatisfactory ailerons.
    Keywords: Aircraft Design, Testing and Performance
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  • 15
    Publication Date: 2018-06-05
    Description: The Army Air Force has made available several pursuit-type airplanes for quantitative investigation of their flying and handling qualities. One Item of special interest obtained from the results of the investigation is a comparison of the aileron control characteristics of the P-36, P-40, Hawker Hurricane, and Supermarine Spitfire airplanes. Figure 1 shows the design characteristics of the ailerons and the control sticks of the four airplanes. Aileron effectiveness may be expressed in terms of the helix angle generated by the wing tip in a steady roll. This angle is given by the expression pb/2V, where p is the rolling velocity, b the wing span, and V the true airspeed, expressed in consistent units. This quantity is convenient to use because, although it does not rep resent directly the rolling velocity of airplanes of different spans or airplanes operating at different speeds, it provides a satisfactory basis for computing the rate of roll and the time required to bank a given amount under any given set of conditions. The ratio of pb/2V obtained in any roll to the maximum value reached with full aileron deflection indicates the fraction of the maximum aileron travel that was reached. A complete discussion of this criterion for aileron effectiveness is given in reference 1. The aileron effectiveness of the various airplanes is compared in the following table on the basis of the response obtained with stick forces of 30 and 5 pounds. A force of 30 pounds is somewhat less than the greatest stick force exerted by the pilot. Repeated flight measurements have shown, however, that this force is a reasonable upper limit for maneuvering at high speeds.
    Keywords: Aircraft Design, Testing and Performance
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  • 16
    Publication Date: 2018-06-05
    Description: The present trend is toward faster and larger pursuit airplanes. Because both speed and size increase the aileron control forces, the design of ailerons for manual operation is becoming increasingly difficult. In order to obtain a clearer picture of the future problem of balancing ailerons, and inspection has been made of the effects of airplane size and speed on the control forces. Computations were made of the aileron control forces required to meet specified rolling conditions for plain ailerons on wings with spans from 40 to 80 feet and for speeds up to 500 miles per hour. The rolling conditions were specified by two alternative criterions. One was the rolling criterion pb/2V of reference 1. For reasons, which will be discussed later, a value of 0.09 rather than the recommended value of 0.07 was assigned to this criterion. For the criterion pb/2V, the required value of the rolling velocity p varies inversely with the airplane span b. There is some question as to whether the rolling velocity of a pursuit airplane can be permitted to decrease simply because its size is increased. For the second criterion, therefore, the rolling velocity is independent of span (p/V is a constant). The value assigned to this criterion was so chosen that for a wing of 40-foot span the value of pb/2V would be 0.09. The computations neglected compressibility effects. Available experimental data and the results of tests given in reference 2 indicate that the effect of compressibility is to increase the control force. Recent flight tests have indicated that, with certain types of aileron, serious compressibility effects may cause discontinuity at speeds of approximately 400 miles per hour in the aileron control force curves.
    Keywords: Aircraft Design, Testing and Performance
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  • 17
    Publication Date: 2019-06-28
    Description: An investigation has been made in the Langley free-flight tunnel to obtain an experimental verification of the theoretical rudder-free stability characteristics of an airplane model equipped with conventional rudders having negative floating tendencies and negligible friction. The model used in the tests was equipped with a conventional single vertical tail having rudder area 40 percent of the vertical tail area. The model was tested both in free flight and mounted on a strut that allowed freedom only in yaw. Tests were made with three different amounts of rudder aerodynamic balance and with various values of mass, moment of inertia, and center-of-gravity location of the rudder. Most of the stability derivatives required for the theoretical calculations were determined from forced and free-oscillation tests of the particular model tested. The theoretical analysis showed that the rudder-free motions of an airplane consist largely of two oscillatory modes - a long-period oscillation somewhat similar to the normal rudder-fixed oscillation and a short-period oscillation introduced only when the rudder is set free. It was found possible in the tests to create lateral instability of the rudder-free short-period mode by large values of rudder mass parameters even though the rudder-fixed condition was highly stable. The results of the tests and calculation indicated that for most present-day airplanes having rudders of negative floating tendency, the rudder-free stability characteristics may be examined by simply considering the dynamic lateral stability using the value of the directional-stability parameter Cn(sub p) for the rudder-free condition in the conventional controls-fixed lateral-stability equations. For very large airplanes having relatively high values of the rudder mass parameters with respect to the rudder aerodynamic parameters, however, analysis of the rudder-free stability should be made with the complete equations of motion. Good agreement between calculated and measured rudder-free stability characteristics was obtained by use of the general rudder-free stability theory, in which four degrees of lateral freedom are considered. When this assumption is made that the rolling motions alone or the lateral and rolling motions may be neglected in the calculations of rudder-free stability, it is possible to predict satisfactorily the characteristics of the long-period (Dutch roll type) rudder-free oscillation for airplanes only when the effective-dihedral angle is small. With these simplifying assumptions, however, satisfactory prediction of the short-period oscillation may be obtained for any dihedral. Further simplification of the theory based on the assumption that the rudder moment of inertia might be disregarded was found to be invalid because this assumption made it impossible to calculate the characteristics of the short-period oscillations.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-184 , NACA-ARR-L4J05A
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  • 18
    Publication Date: 2019-06-28
    Description: Two graphical methods are presented for determining the stick-free neutral point, and they are extensions of the methods commonly used to determine the stick-free neutral point. A mathematical formula for computing the stick-free neutral point is also given. These methods may be applied to determine approximately the increase in tail size necessary to shift the neutral point (stick fixed or free) to any desired location on an airplane having inadequate longitudinal stability.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-251 , NACA-RB-4B21
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  • 19
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-MR-A4L14
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  • 20
    Publication Date: 2019-07-13
    Description: The extent of agreement of the theoretical impact computations with the actual phenomenon has not as yet been fully clarified. There is on the one hand a certain imperfection in the theory (simplifying assumptions made) and on the other an insufficiency in the experimental data available. The object of our present paper is to show how far test results agree with the available approximate computation methods, to investigate in greater detail the physical nature of impact on water, and to perfect the experimental method of studying the phenomenon.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1046 , ; 438
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  • 21
    Publication Date: 2019-07-12
    Description: The effect of several armament installations on the drag of a 1/8 scale model of the B-32 airplane was determined. Turrets in the following positions were tested: nose, tail, upper forward, upper aft, and lower. The nose and tail turrets were each equipped with two.50-caliber guns. Upper turrets were of three types: two.50-caliber guns, four.50-caliber guns, and 20-millimeter cannon. Lower turrets were of two types: two.50-caliber guns and four.50-caliber guns. The effect of streamlining the upper two- and four-gun turrets and of extending the lower two-gun turret was determined. The tests were conducted in the Langley 19-foot. pressure tunnel at a Reynolds number of approximately 2,960,000 and a Mach number of 0.13. Large increases in drag coefficient were caused by the complete armament installations. At a lift coefficient of 0. 4 the installations with nonstreamlined upper turrets and the lower turret retracted increased the drag coefficient by 0.0022 and 0.0027 for the two-gun and four-gun turret installations, respectively. Streamlining the upper turrets reduced the drag of these installations by approximately 40 percent with the upper turrets streamlined, the drag increase was about the same for either the two- or four-gun turret installation. The streamlined two-cannon upper turrets increased the drag about the same amount as the two-gun upper turrets that were not streamlined. Extension of the lower turret. increased the drag slightly more than the whole streamlined gun-turret installation.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-MR-L4L30a
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  • 22
    Publication Date: 2019-07-11
    Description: For computing the critical flutter velocity of a wing among the data required are the position of the line of centers of gravity of the wing sections along the span and the mass moments and radii of inertia of any section of the wing about the axis passing through the center of gravity of the section. A sufficiently detailed computation of these magnitudes even if the weights of all the wing elements are known, requires a great deal of time expenditure. Thus a rapid competent worker would require from 70 to 100 hours for the preceding computations for one wing only, while hundreds of hours would be required if all the weights were included. With the aid of the formulas derived in the present paper, the preceding work can be performed with a degree of accuracy sufficient for practical purposes in from one to two hours, the only required data being the geometric dimensions of the outer wing (tapered part), the position of its longerons, the total weight of the outer wing, and the approximate weight of the longerons, The entire material presented in this paper is applicable mainly to wings of longeron construction of the CAHI type and investigations are therefore being conducted by CAHI for the derivation of formulas for the determination of the preceding data for wings of other types.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1052 , Report of the Central Aero-Hydrodynamical Institute, Moscow; Rept-452
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  • 23
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    Unknown
    In:  CASI
    Publication Date: 2019-07-11
    Description: The few available test data on the heat dissipation of wholly or partly heated airfoil models are compared with the corresponding data for the flat plate as obtained by an extension of Prandtl's momentum theory, with differentiation between laminar and turbulent boundary layer and transitional region between both, the extent and appearance of which depend upon certain critical factors. The satisfactory agreement obtained justifies far-reaching conclusions in respect to other profile forms and arrangements of heated surface areas. The temperature relationship of the material quantities in its effect on the heat dissipation is discussed as far as is possible at tk.e present state of research, and it is shown that the profile drag of heated wing surfaces can increase or decrease with the temperature increase depending upon the momentarily existent structure of the boundary layer.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1044 , Jahrbuch 1938 der Deutschen Luftfahrtforschung; 245-256
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  • 24
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-08-17
    Description: The writer sets out to prove by calculation and experiment that by extensive utilization of the skin to carry axial load (reduction of stringer spacing) the stringer sections can be made small enough to afford a substantial saving in structural weight. This saving ranges from 5 to about 40 percent.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1031 , Luftfahrtforschung; 18; 9; 331-337
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  • 25
    Publication Date: 2019-08-13
    Description: An experimental investigation concerned primarily with the extension of test data on the drag of revolving disks, cylinders, and streamline rods to high Mach numbers and Reynolds numbers is presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TR-793
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  • 26
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    Unknown
    In:  CASI
    Publication Date: 2019-08-15
    Description: Unduly high diving speeds can be effectively controlled by diving brakes but their employment involves at the same time a number of disagreeable features: namely, rotation of zero lift direction, variation of diviving moment, and, the creation of a potent dead air region.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1033
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  • 27
    Publication Date: 2019-11-26
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-ACR-3I30 , NACA-WR-W-6
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  • 28
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    In:  CASI
    Publication Date: 2019-07-11
    Description: The report presents a method for the computation of axial fan characteristics. The method is based on the assumption that the law of constancy of the circulation along the blade holds, approximately, for all fan conditions for which the blade elements operate at normal angles of attack (up to the stalling angles). Pressure head coefficient K(sub a) and power coefficient K(sub u) for the force components in the axial and tangential directions, respectively, and analogous to the lift and drag coefficients C(sub y) and C(sub x) are conveniently introduced.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1042 , Report of the Central Aero-Hydrodynamical Institute, Moscow; Rept-295
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  • 29
    Publication Date: 2019-07-11
    Description: The present paper is devoted to the theoretical and experimental investigation of one of the stationary elements of a fan, namely, the vaneless diffuser. The method of computation is based on the principles developed by Pfleiderer (Forschungsarbeiten No. 295). The practical interest of this investigation arises from the fact that the design of the fan guide elements - vaneless diffusers, guide vanes, spiral casing - is far behind the design of the impeller as regards accuracy and. reliability. The computations conducted by the method here presented have shown sufficiently good agreement with the experimental data and indicate the limits within which the values of the coefficient of friction lie.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1038 , Report of the Central Aero-Hydrodynamical Institute, Moscow; Rept-224
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  • 30
    facet.materialart.
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    In:  CASI
    Publication Date: 2019-07-11
    Description: An approximate theory of buffeting is here presented, based on the assumption of harmonic disturbing forces. Two cases of buffeting are considered: namely, for a tail angle of attack greater and less than the stalling angle, respectively. On the basis of the tests conducted and the results of foreign investigators, a general analysis is given of the nature of the forced vibrations the possible load limits on the tail, and the methods of elimination of buffeting.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1041 , Report of the Central Aero-Hydrodynamical Institute, Moscow; Rept-395
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  • 31
    Publication Date: 2019-07-12
    Description: The drag of several types of gunner's turrets, windshields, blisters, and other protuberances, including projecting guns, was investigated at speeds from 75 to 440 miles per hour in the NACA 8-foot high-speed wind tunnel. The various gunner's enclosures were represented by 1/10 and 1/7 full-size models on a midwing-fuselage combination representative of bomber types. Most of the usual types of retractable turrets are very poor aerodynamically; they caused wind drag increments, dependent upon the size of the turret relative to the fuselage and upon the speed, up to twice the drag of the fuselage alone. A large streamline blister sufficient to enclose completely one type of rotating cylindrical turret caused a drag increment of approximately one-half that of the turret and at the same time provided space adequate for two gunners rather than for one gunner. A large portion of the drag increments for some types of turret appeared to be due to adverse effects on the fuselage flow caused by the turret rather than by the direct drag of the turret.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-202
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  • 32
    Publication Date: 2019-07-12
    Description: A method that utilizes the Doppler effect on radio signals for determining the speed of an airplane and the distance traveled by the airplane has been developed and found to operate satisfactorily. In this method, called the NACA radio ground-speed system, standard readily available radio equipment is used almost exclusively and extreme frequency stability of the transmitters is not necessary. No complicated equipment need be carried in the airplane, as the standard radio transmitter is usually adequate. Actual flight tests were made in which the method was used and the results were consistent with calibrated air speed indications and stop-watch measurements. Inasmuch as the fundamental accuracy of the radio method is far better than either of the checking systems used, no check was made on the limitations of the accuracy.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-ACR-256 , NACA-SR-256
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  • 33
    Publication Date: 2019-07-12
    Description: Adjustable cowling flaps, an adjustable-length cowling skirt, and a bottom opening with adjustable flap were tested as means of controlling the rate of cooling-air flow through an air-cooled radial-engine cowling. The devices were tested in the NACA 20-foot tunnel on a model wing-nacelle-propeller combination, through an airspeed range of 20 to 80 miles per hour, and with the propeller blade angle set 23 degrees at 0.75 of the tip radius. The resistance of the engine to air flow through the cowling was simulated by a perforated plate. The results indicated that the adjustable cowling flap and the bottom opening with adjustable flap were about equally effective on the basis of pressure drop obtainable and that both were more effective means of increasing the pressure drop through the cowling than the adjustable-length skirt. At conditions of equal cooling-air flow, the net efficiency obtained with the adjustable cowling flaps and the adjustable-length cowling skirt was about 1% greater than the net efficiency obtained with the bottom opening with adjustable flap.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-144
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  • 34
    Publication Date: 2019-07-12
    Description: It is shown that on the basis of existing high-speed airfoil data, propeller efficiencies appreciably in excess of 40% do not appear possible at speeds above 500 miles per hour at 20,000 feet. The assumption that present propeller-blade thicknesses cannot be reduced radically, is implied. Until the reliability and applicability of the airfoil data are established, this conclusion must not be regarded as infallible. Dive tests with airplanes equipped with thrust meters and torque meters are proposed to provide an urgently needed check. The design of high-speed propellers is dictated wholly by compressibility considerations. The blade width, thickness, and pitch distribution; also the airfoil sections, the lift coefficient, the propeller diameter, and rpm must all be adjusted if reasonable efficiencies are to be maintained at airplane speeds that are now being approached. Research is urgently needed on: 1) airfoils at subsonic, sonic, and supersonic speeds; 2) propellers at high forward speeds in wind tunnels; 3)propellers in free flight at high speeds; and 4) jet propulsion and related devices. The breakdown of propeller efficiency indicated by airfoil data, should serve as an incentive for accelerated research on jet propulsion. This device may extend the attainable speed of current airplanes to the neighborhood of 550 miles per hour at 20,000 feet.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-187
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  • 35
    Publication Date: 2019-07-12
    Description: A chart is presented for the values of the coefficient in the formula for the critical compressive stress at which buckling may be expected to occur in flat rectangular plates supported along all edges and, in addition, elastically restrained against rotation along the unloaded edges. The mathematical derivations of the formulas required in the construction of the chart are given.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-189
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  • 36
    Publication Date: 2019-07-12
    Description: A preliminary investigation of a number of duct entrances of rectangular shape installed in the leading edge of a wing was conducted in the NACA 20-foot tunnel to determine the external drag, the available pressure, the critical Mach numbers, and the effect on the maximum lift. The results showed that the most satisfactory entrances, which had practically no effect on the wing characteristics, had their lips approximately in the vertical plane of the leading edge of the wing. This requirement necessitated extending the lips outside the wing contour for all except the small entrances. Full dynamic pressure was found to be available over a fairly wide range of angle of attack. The critical Mach number for a small entrance was calculated to be as high as that for the plain wing but was slightly lower for the larger entrances tested.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-154
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  • 37
    Publication Date: 2019-07-12
    Description: Test of 10-foot diameter, 4- and 6-blade single- and dual-rotating propellers were conducted in the 20-foot propeller-research tunnel. The propellers were mounted at the front end of a streamline body incorporating spinners to house the hub portions. The effect of a symmetrical wing mounted in the slipstream was investigated. The blade angles investigated ranged from 20 degrees to 65 degrees; the latter setting corresponds to airplane speeds of over 500 miles per hour. The results indicate that dual-rotating propellers were from 0 to 6% more efficient than single-rotating ones; but when operating in the presence of a wing the gain was reduced about one-half. Other advantages of dual-rotating propellers were found to include greater power absorption and greater efficiency at the low V/nD operating range of high pitch propellers.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-157
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  • 38
    Publication Date: 2019-07-12
    Description: A chart is presented for the values of the coefficient in the formula for the critical compressive stress at which buckling may be expected to occur in outstanding flanges. These flanges are flat rectangular plates supported along the Loaded edges, supported and elastically restrained along one unloaded edge, and free along the other unloaded edge. The mathematical derivations of the formulas required for the construction of the chart are given.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-188
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  • 39
    Publication Date: 2019-07-11
    Description: Detail calculations are presented of the shifts in stick-fixed neutral point of the Republic XF-12 airplane due to the windmilling propellers and to the fuselage. The results of these calculations differ somewhat from those previously made for this airplane by Republic Aviation Corporation personnel under the direction of Langley flight division personnel. Due to these differences the neutral point for the airplane is predicted to be 37.8 percent mean aerodynamic chord, instead of 40.8 percent mean aerodynamic chord as previously reported.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-CMR-L4J16
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  • 40
    Publication Date: 2019-08-15
    Description: Pressure distribution and spray measurements were carried out on rectangular flat and V-bottom planing surfaces. Lift, resistance, and center of pressure data are analyzed and it is shown how these values may be computed for the pure planing procees of a flat or V-bottom suface of arbitrary beam, load and speed, the method being illustrated with the aid of an example.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1061 , Jahrbuch 1937 der Deutschen Luftfahrtforschung; 320-339
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  • 41
    Publication Date: 2019-08-26
    Description: An investigation has been made of the effect of aerodynamic heating on propeller-blade temperatures. The blade temperature rise resulting from aerodynamic heating was measured and the relation between the resulting blade temperatures and the outer limit of the iced-over region was examined. It was found that the outermost station at which ice formed on a propeller blade was determined by the blade temperature rise resulting from the aerodynamic heating at that point.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-153
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  • 42
    Publication Date: 2019-08-26
    Description: Force tests were made of a 1/8-scale model of a twin-engine low-wing transport airplane in the NACA 8-foot high-speed wind tunnel to investigate compressibility and interference effects at speeds up to 450 miles per hour. In addition to tests of the standard arrangement of the model tests were made with several modifications designed to reduce the drag and to increase the critical speed. The results show serious increases in drag at critical speeds below 450 miles per hour due to the occurrence of compressibility burbles on the standard radial-engine cowlings, on sections of the wing as a result of wing-nacelle interference, and on the semi-retracted main landing wheels. The critical speed at which the shock occurred on the standard cowlings was 20 miles per hour lower in the presence of the fuselage than in the presence of the wing only. The drag of the complete model was reduced 25% at 300 miles per hour by completely retracting the landing gear, fairing the windshield irregularities, and substituting streamline nacelles (with allowance made for the proper amount of cooling-air flow) for the standard nacelle arrangement. The values of the critical Mach number were extended from 0.47 to 0.60 as a result of the aforementioned improvements. The principal purpose of the reported tests was to investigate the effect of compressibility on the drag of the component parts of a representative large airplane and on the overall drag of such an airplane. The influence of interference on compressibility effects was also studied. In addition, it was proposed to test several modifications of the standard component parts that gave promise of an improvement in aerodynamic characteristics.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-143
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  • 43
    Publication Date: 2019-08-16
    Description: An analysis is made of the stability of an airplane with ailerons free, with particular attention to the motions when the ailerons have a tendency to float against the wind. The present analysis supersedes the aileron investigation contained in NACA Report No. 709. The equations of motion are first written to include yawing and sideslipping, and it is demonstrated that the principal effects of freeing the ailerons can be determined without regard to these motions. If the ailerons tend to float against the wind and have a high degree of aerodynamic balance, rolling oscillations, in addition to the normal lateral oscillations, are likely to occur. On the basis of the equations including only the rolling motion and the aileron deflection, formulas are derived for the stability and damping of the rolling oscillations in terms of the hinge moment derivatives and other characteristics of the ailerons and airplane. Charts are also presented showing the oscillatory regions and stability boundaries for a fictitious airplane of conventional proportions. The effects of friction in the control system are investigated and discussed. If the ailerons tend to trail with the wind, the condition for stable variation of stick force with aileron deflection is found to determine the amount of aerodynamic balance that may be used. If the ailerons tend to float against the wind, the period and damping of the rolling oscillations are found to be satisfactory (in a mass-balanced system) so long as the restoring moment is not completely balanced out. Unbalanced mass behind the hinge, however, has an unfavorable effect on the damping of the oscillations and so shifts the boundary that close aerodynamic balance may not be attainable.
    Keywords: Aircraft Design, Testing and Performance
    Type: AD-A301275 , NACA-TR-787 , NASA-TM-111361 , NAS 1.15:111361
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  • 44
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    Zeitschrift für anorganische Chemie 246 (1941), S. 243-257 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 1. Der zeitliche Verlauf der Reduktion von Molybdänlösungen mit Zn und Cd wird bei Gegenwart verschiedener Säuren untersucht. Aus Potentialmessungen geht hervor, daß die Reduktion zunächst zur Bildung von Mo(V) und dann bis Zum Mo(III). führt. Mo(IV) tritt nicht auf.
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  • 45
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    Zeitschrift für anorganische Chemie 246 (1941), S. 275-283 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 1. Kobalt(III)-sulfat und Rubidiumkobaltalaun sind diamagnetisch bzw. ganz schwach paramagnetisch und stellen somit Durchdringungskomplexe dar. Es wird darauf hingewiesen, daß mit großer Wahrscheinlichkeit in allen Verbindungen des dreiwertigen Kobalts Atombindungen vorhanden sind. Der Übergang von Co2+ zu Co3+ scheint überhaupt nur dann möglich zu sein, wenn ein Energiegewinn durch Ausbildung von Atombindungen vorhanden ist.
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  • 46
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    Zeitschrift für anorganische Chemie 246 (1941), S. 329-329 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
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  • 47
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    Zeitschrift für anorganische Chemie 246 (1941), S. 331-346 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 1. Bei den Cadmium/Wismutoxyhalogeniden treten tetragonale Phasen auf, die dieselbe einfache Art von Metall-Sauerstoffschichten wie die in früheren Arbeiten beschriebenen Oxyhalogenide - die Typen X1, X1X2, X1X1X2, X2  -  enthalten. Deshalb ist die a-Achse in allen etwa 3,9 Å. In den neuen Verbindungen erscheinen zwischen den Me—O-Schichten dreifache Halogenschichten  -  also X3-Schichten  - , von denen jede eine unvollständige Cadmiumschicht einschließt. Bei den „X3“-Phasen gibt es nur X3-Schichten. Bei den anderen Phasen wechseln X3- und X2-Schichten regelmäßig in der Reihenfolge X2X3 oder X2X2X3 ab.
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  • 48
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    Zeitschrift für anorganische Chemie 246 (1941), S. 347-362 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es werden die in der Literatur angegebenen Messungsergebnisse kritisch ausgewertet und die zur Zeit besten diamagnetischen Inkremente wiedergegeben für: edelgasähnliche Ionen in gelöstem Zustande, höher geladene edelgasähnliche Kationen, komplexe Anionen und Ionen mit 18, 18 + 2 und 8 + 2 Außenelektronen. Ferner wird die Abhängigkeit der Anionenwerte von der Ladung des Kations besprochen. Anhangsweise werden die Diamagnetismuswerte für einige Ionen abgeschätzt, deren direkte Bestimmung nicht möglich ist.
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  • 49
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    Zeitschrift für anorganische Chemie 247 (1941), S. 205-210 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es wurden die Extinktionskurven von Ni(SCN)2 in Wasser und in verschieden konzentrierten Wasser-Nichtelektrolytgemischen, sowie die von wasserfreiem Ni(SCN)2 in organischen Lösungsmitteln gemessen.
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  • 50
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    Zeitschrift für anorganische Chemie 247 (1941), S. 211-220 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Im System Si/As werden durch thermische Analyse und röntgenographische Untersuchungen die Verbindungen Si As2 und SiAs nachgewiesen. SiAs2 zersetzt sich bei 944° C. SiAs schmilzt kongruent bei 1083° C.
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    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Verschiedene Anteile eines sehr reinen, fein dispersen Kupferpulvers werden unter konstanten Bedingungen im Wasserstoffstrom auf verschieden hohe Temperaturen erhitzt. Nach dem Abkühlen wird das mikroskopische Bild, das Röntgenogramm, die pyknometrische Dichte, das Schüttvolumen, die Lösbarkeit in verdünnter Salpetersäure, die elektromotorische Kraft, die Reaktivität gegen eine Silbernitratlösung, die Adsorptionsisotherme gegenüber Methanoldampf und die katalytische Wirksamkeit gegenüber dem Zerfall von Wasserstoffperoxyd bestimmt. Aus den Ergebnissen und einigen Rechenwerten derselben wird versucht, den Verlauf der Frittungsvorgänge zu beschreiben.
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  • 52
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    Zeitschrift für anorganische Chemie 247 (1941), S. 259-276 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Cadmiumhydroxyd verhält sich Laugen gegenüber im Prinzip wie Zinkhydroxyd. Es gelingt aus konzentrierten Laugen kristallisierte Cadmate darzustellen, die wie die Zinkate als Hydroxosalze aufgefaßt werden müssen. Folgende Hydroxo-Cadmate konnten isoliert werden: Na2[Cd(OH)4] (1) Na2[Cd(OH)4] · l/2NaOH · 1 - 1 1/2H20 (2) Na3[Cd(OH)5 (H20)]·l H20 (3) Sr2[Cd(OH)6] (4) Ba2[Cd(OH)6] · (5)Das Dinatriumcadmat (1) bildet wahrscheinlich auch ein Hydrat.
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    Zeitschrift für anorganische Chemie 247 (1941), S. 307-307 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
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  • 54
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    Zeitschrift für anorganische Chemie 247 (1941), S. 308-308 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
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  • 55
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    Zeitschrift für anorganische Chemie 247 (1941), S. 309-332 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
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  • 56
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    Zeitschrift für anorganische Chemie 247 (1941), S. 367-383 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die AlCI3 · 6H2O-Fällung aus wäßriger Salzsäure bei Gegenwart von Be erweist sich als nahezu ebenso Be-arm wie bei der Fällung aus ätherisch-wäßriger Salzsäure.
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  • 57
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    Zeitschrift für anorganische Chemie 247 (1941), S. 392-414 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Oxydation von 3-wertigem Wismut in Natronlauge wird in Abhängigkeit von Oxydationsmittel, Temperatur und Konzentration der Lauge untersucht. In Natronlauge mit 25-50% NaOH erhält man bei Temperaturen über 100° durch Oxydation mit viel überschüssigem NaOCl oder Brom braune Reaktionsprodukte, die 92-97% des Wismuts in 5-wertiger Form enthalten. Ihr mit der Laugenkonzentration wechselnder Gehalt an Natrium liegt zwischen 3 und 6 Na auf 1 Bi. Die Darstellung eines definierten Natriumbismutats rnit ausschließlich 5-wertigem Bi gelingt auf diese Weise nicht. Führt man die Oxydation in verdünnterer Natronlauge mit 5-22% NaOH durch, so resultieren in Abhängigkeit vom Gehalt an 5-wertigem Bi dunkelgrüne bis schwarze Oxydationsprodukte mit 30-90% 5-wertigem Bi und einem Gehalt an Alkali zwischen 0,1 und 0,9 Na auf 1 Bi-Atom.
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    Zeitschrift für anorganische Chemie 247 (1941), S. 1-21 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
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    Zeitschrift für anorganische Chemie 247 (1941), S. 22-30 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
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  • 60
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    Zeitschrift für anorganische Chemie 247 (1941), S. 31-32 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
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    Zeitschrift für anorganische Chemie 247 (1941), S. 53-64 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Titan kann Sauerstoff in fester Phase lösen; dabei ändern sich die Gitterkonstanten und damit das Molvolumen nur wenig. Während die c-Achse bis zur Phasengrenze bei der Zusammensetzung TiO0,42 regelmäßig um 1,8% anwächst, kommt die Änderung der a-Achse.
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    Zeitschrift für anorganische Chemie 247 (1941), S. 65-95 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Beim Zusammenkochen von Lösungen von Magnesiumchlorid und Kieselsäurehydrat mit Kaliumhydroxyd und Calciumhydroxyd wurden Magnesiumsilikatgele erhalten, die im Unterschied zu analog gefällten Aluminiumsilikaten deutliche Interferenzen gaben, und zwar alle für die Silikatschichten der Tonmineralien charakteristischen.
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    Zeitschrift für anorganische Chemie 247 (1941), S. 113-123 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es wurden die Wärmeinhalte von NaSH, KSH, RbSH, NaSeH, KSeH und RbSeH zwischen O° bzw. Zimmertemperatur und einer Temperatur, die etwa 30° über dem Umwandlungspunkt liegt, gemessen. Die Messungen wurden zum Teil mit einem Eiskalorimeter, zum Teil mit einem Hochtemperaturkalorimeter durchgeführt.
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    Zeitschrift für anorganische Chemie 247 (1941), S. 131-134 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Löslichkeit von Deuterium in festem Nickel wurde bei Atmosphärendruck und Temperaturen von 200-1120° gemessen und ähnlich wie früher beim Eisen etwas kleiner gefunden als die des Wasserstoffs. Der Unterschied beträgt bei hohen Temperaturen (600-1100°) wie beim Eisen rund 10%.
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    Zeitschrift für anorganische Chemie 247 (1941), S. 147-160 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Mit Hilfe von Löslichkeitsbestimmungen oberhalb von 100° wurden die experimentellen Grundlagen zur Aufstellung der Schmelzpunkts-Konzentrationsdiagramme von Zweistoffsystemen geschaffen, die außer Wasser Chloride oder Sulfate enthalten.
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    Zeitschrift für anorganische Chemie 247 (1941), S. 180-184 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es wurde eine neue Methode ausgearbeitet, nach der man den freien Kalk neben Calciumcarbonat und Calciumsilikaten sowie in Zementen bestimmen kann und die des weiteren auch für die Ermittlung von Calciumhydroxyd neben Calciumhydrosilikat anwendbar ist.
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    Zeitschrift für anorganische Chemie 248 (1941), S. 1-31 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es werden Zahl und Konstitution der Phasen des binären Systems Nb—O mit präparativen, analytischen und röntgenographischen Verfahren untersucht. Danach existieren nur die Nioboxyde Nb2O5, NbO2 und NbO mit kleinen Homogenitätsgebieten. Sie sind alle durch ausgedehnte heterogene Zustandsgebiete voneinander und vom Niobmetall abgegrenzt.
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    Zeitschrift für anorganische Chemie 250 (1942), S. 1-9 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Verschieden hoch vorerhitzte Eisenpulver werden in bezug auf ihre Geschwindigkeit zu rosten und sich in einer wäßrigen Eisen(III)-chloridlösung aufzulösen, geprüft. Die wesentlichsten Merkmale der beobachteten Rost-Kurven sind von der Eisensorte wenig abhängig. Bei den im Wasserstoffstrom vorerhitzten Proben zeigen sich Minima in der Rostgeschwindigkeit bei den auf 200°, 400° und 780° vorerhitzten und Maxima bei den auf 355°, 530° und 850° vorerhitzten Proben. Ähnliche Merkmale zeigen die Auflösungsgeschwindigkeiten in einer Eisen(III)-chloridlösung.
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    Zeitschrift für anorganische Chemie 250 (1942), S. 10-22 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 1. Es wurde die Zersetzung von CaSO4 in Gegenwart von SiO2 im molaren (1:1) Verhältnis bei 1100° C innerhalb von 4 Stunden in Luft, SO2, N2, O2, wasserdampfgesättigter Luft von 40, 80, 90° C und Wasserdampf bei den Gasströmungsgeschwindigkeiten von 2 und 4 Litern pro Stunde geprüft. Rohmaterialien, Apparatur und Versuchsbedingungen werden beschrieben.
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    Zeitschrift für anorganische Chemie 250 (1942), S. 23-35 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es wird untersucht, wie sich die Reduktion von Eisenoxyd mit Wasserstoff durch Zusatz keiner Mengen von Chlor, HCl, HBr, Brom, Schwefeldioxyd, NH, und NO beeinflussen läßt.
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    Zeitschrift für anorganische Chemie 250 (1942), S. 36-41 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Ausstoßung der in verschiedenen Eisenpulvern enthaltenen Gase erfolgt, bevorzugt in den Gebieten von 200°, 400° und 710°.
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    Zeitschrift für anorganische Chemie 251 (1943), S. 166-166 
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    Keywords: Chemistry ; Inorganic Chemistry
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    Zeitschrift für anorganische Chemie 251 (1943), S. 161-165 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 1. In einem strömenden Schwefeldampf-Stickstoffgemisch setzt sich Zinkoxyd bei ∼ 1000° im Laufe 1 Stunde quantitativ zu ZnS und SO2 um. Aus der titrimetrisch bequem erfaßbaren SO2-Menge läßt sich die vorhandene Oxydmenge mit großer Genauigkeit ermitteln.
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    Zeitschrift für anorganische Chemie 251 (1943), S. 201-212 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 1. Aus feinteiligem Nickelmetall oder Nickelhalogeniden wurde in strömendem Ammoniak bei 445 bzw. 410°C die Verbindung Ni3N erhalten. Chemisches Verhalten und thermische Beständigkeit der Verbindung werden angegeben.
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    Zeitschrift für anorganische Chemie 251 (1943), S. 213-220 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es wird eine neue Methode zur Darstellung des KURROL'schen Salzes beschrieben. Die an diesem Salz beobachteten Eigenschaften weichen in wesentlichen Punkten von den Angaben von PASCAL ab.
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    Zeitschrift für anorganische Chemie 251 (1943), S. 221-221 
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    Keywords: Chemistry ; Inorganic Chemistry
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    Zeitschrift für anorganische Chemie 251 (1943), S. 222-232 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 1. Es werden die Fragen erörtert, die bezüglich des Auftretens des NiAs-, CdJ2- und Pyritgitters bzw. des Überganges vom NiAs- zum CdJ2-Typ bei den Chalkogeniden der Übergangselemente auftreten.
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    Zeitschrift für anorganische Chemie 250 (1942), S. 110-120 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: KNa2 kristallisiert im Strukturtyp des MgZn2 (C14-Typ):a = 7,48, c = 12,27, c/a = 1,64.
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    Zeitschrift für anorganische Chemie 250 (1942), S. 122-126 
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    Keywords: Chemistry ; Inorganic Chemistry
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    Topics: Chemistry and Pharmacology
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    Zeitschrift für anorganische Chemie 250 (1942), S. 121-121 
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    Notes: 1. Die Prüfung der in wäßrigen Lösungen von Borat und Brenzkatechin vorliegenden Gleichgewichte ergab, daß bei nicht zu großem Brenzkatechinüberschuß viel Monobrenzkatechinborat neben wenig Dibrenzkatechinborat vorliegt. Die Bildung von Monobrenzkatechinborat am Borat und Brenzkatechin verläuft praktisch vollständig. Die Dibrenzkatechinboratkonzentration gehorcht bei 25°C der Gleichung .
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    Zeitschrift für anorganische Chemie 251 (1943), S. 233-240 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Bei der Einwirkung von Aluminiummetall auf AlF3 entsteht ein niederes Fluorid der Zusammensetzung (AlF)x. Daneben tritt eine geringe Sublimation von AlF3 selbst ein, die neben der Verflüchtigung des Subfluorids um so stärker in Erscheinung tritt, je niedriger die Temperatur ist. Bei der Kondensation zerfällt das Subfluorid in Metall und Trifluorid.
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    Zeitschrift für anorganische Chemie 251 (1943), S. 251-259 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die bisher bekannten Eigenschaften des Elements 93 und der vor ihm stehenden Elemente Uran und Thorium ergeben, wenn man das Verhalten der Lanthaniden zum Vergleich heranzieht, trotz auffallender chemischer Ähnlichkeit in der vierwertigen Oxydationsstufe nicht die Notwendigkeit der Aufstellung einer Thoridengruppe. Dagegen besteht eine gewisse Berechtigung für die Einordnung des Elements 93 in eine Uranidengruppe. Die bestehende Unsicherheit hinsichtlich der Einordnung der genannten Elemente in das periodische System erscheint nicht nur durch noch fehlendes experimentelles Material bedingt, sondern auch prinzipiell begründet.
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    Zeitschrift für anorganische Chemie 250 (1942), S. 159-172 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Farbumschlagskurven des CrIII/CrVI-Indikators in ternären Schmelzen der Zusammensetzung Na2O-B2O3-MexO3 für 1100° in Luft wurden ermittelt. Die Kurven zeigen, daß sich B2O3 gegenüber K2O und Na2O wie eine äußerst schwache Säure verhalt. Die Anwesenheit stärker polarisierender, namentlich zwei- und dreiwertiger Kationen hat zur Folge, daß die Metaboratstufe ganz erheblich an Beständigkeit gewinnt, so daß B2O3 zu einer starken Säure wird. Auf Grund dieser Erscheinung ist es möglich, auf den Dissoziationsgrad der gelösten Oxyde zu schließen.
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    Zeitschrift für anorganische Chemie 250 (1942), S. 199-201 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Löslichkeit des Indiumjodats in Salpetersäure verschiedener Konzentrationen wird bei 20°C bestimmt. Die erhaltene Kurve zeigt ein ausgeprägtes Maximum der Löslichkeit bei 300 g HNO3/Liter.
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    Zeitschrift für anorganische Chemie 250 (1942), S. 202-203 
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    Zeitschrift für anorganische Chemie 250 (1942), S. 204-206 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
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    Zeitschrift für anorganische Chemie 250 (1942), S. 223-225 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
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    Zeitschrift für anorganische Chemie 250 (1942), S. 207-222 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 1. Die Nickelkomplexe des Salicylaldiimins, Salicylaldehydmethylimins, -äthylendiimins- und o-phenylendiimins sind diamagnetisch und damit plan gebaute Durchdringungskomplexe. Rei der Methyliminverbindung läßt sich außerdem ein paramagnetischer Zustand herstellen. Beim Aldiimin wurden zwei Formen beobachtet (grüngelb und orangerot), bei denen es sich wahrscheinlich um cis-trans-Isomerie handelt.
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    Zeitschrift für anorganische Chemie 250 (1942), S. 226-228 
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    Zeitschrift für anorganische Chemie 250 (1943), S. 229-229 
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    Zeitschrift für anorganische Chemie 250 (1943), S. 230-235 
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    Keywords: Chemistry ; Inorganic Chemistry
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    Zeitschrift für anorganische Chemie 251 (1943), S. 341-354 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Auf Grund umfangreichen Materials werden die Gründe angeführt, weshalb die bisher als Einlagerungsverbindungen formulierten komplexen Azide Cu(N3)2 (NH3)2 und CU(N3)2(C5H5N)2 als Nichtelektrolyte angesehen werden müssen.
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    Zeitschrift für anorganische Chemie 250 (1943), S. 268-276 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die höheren Isologen der Sulfoxyde und Aminoxyde, d. h. die Selenoxyde, Telluroxyde, Phosphinoxyde und Arsinoxyde, haben sehr große Dipolmomente und enthalten deshalb eine semipolare Bindung. Dasselbe gilt den Verbindungen (C6H5)3PS, (C6H5)3PSe, (C6H5)3· PNC6H5 und (C6H5)3SbS. Ein abweichendes Verhalten zeigt das Tri-p-tolylstibinoxyd.
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    Zeitschrift für anorganische Chemie 250 (1943), S. 245-256 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Mit Hilfe von Dipolmessungen wurde die Konstitution der Verbindungen vom Typus R2SX2, R2SeX2 und R2TeX2 (X = Halogen) untersucht. Die Ergebnisse sind in Übereinstimmung mit der Annahme, daß die Halogenatome gleichwertig sind. Die Bindungen zwischen dem Zentralatom und den Halogenatomen dürften jedoch stark polar sein, was am besten durch Resonanzformeln (III - V, vgl. S. 246) ausgedrückt wird. Die Elektronendichte dieser Bindungen beträgt wahrscheinlich nur etwa 1 Elektron. Die räumliche Konfiguration dieser Verbindungen ist vermutlich die einer trigonalen Doppelpyramide mit den beiden Halogenatomen an den Spitzen (Formel VII, S. 247).
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    Zeitschrift für anorganische Chemie 250 (1943), S. 277-286 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Durch eine magnetochemische Messung nach der Methode von Freed und Kasper wurde gezeigt, daß die Dissoziation von Hexacyclohexyl-diplumban zu paramagnetischem Tricyclohexylblei in 0,5-1%iger Lösung 10% nicht übersteigen kann. Dies steht im Gegensatz zu den kryoskopischen Messungen, wonach die Dissoziation größer ist.
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    Zeitschrift für anorganische Chemie 250 (1943), S. 304-311 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es wird die Darstellung folgender wasserfreier Tetramethylammoniumverbindungen beschrieben und ihr Verhalten im Sulfitosystem der Verbindungen untersucht.
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    Zeitschrift für anorganische Chemie 250 (1943), S. 312-320 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es wird ein neues Analysenverfahren zur quantitativen Bestimmung von Phosphorwasserstoff in Luft beschrieben. Das Verfahren beruht auf der Absorption des Gases in Quecksilberchloridlösung und Oxydation der hierbei gebildeten Phosphor-Quecksilberdoppelverbindung zu Phosphorsäure durch gemessene Jodlösung.
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    Zeitschrift für anorganische Chemie 250 (1943), S. 257-267 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Molekularpolarisation der Verbindungen (C6H5)3SbCl2 und (C6H5)3BiCl2 (in benzolischer Lösung) ist unabhängig von der Temperatur; die Verbindungen haben demnach das Dipolmoment Null, in Übereinstimmung mit der Annahme, daß die Moleküle die Konfiguration einer trigonalen Doppelpyramide besitzen.
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    Zeitschrift für anorganische Chemie 250 (1943), S. 287-303 
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    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Das verflüssigte Schwefeldioxyd ist ein nichtwäßriges, aber „wasserähnliches“ Lösungsmittel. Wie das Wasser vermag es eine große Reihe anorganischer und organischer Stoffe aufzulösen. Die Auflösungen leiten wie wäßrige Losungen vielfach den elektrischen Strom, während das verflüssigte Schwefeldioxyd für sich allein ebensowenig leitet wie reines Wasser. Die aufgelösten Substanzen liegen also als Elektrolyte vor. Das für die geringe Eigenleitfähigkeit verantwortliche Dissoziationsschema läßt in verflüssigtem Schwefeldioxyd nicht nur „neutralisationsanaloge“ Reaktionen zwischen „säureanalogen“ Thionylverbindungen und „basenanalogen“ Sulfiten oder die Erscheinungen der Solvolyse erwarten, sondern auch  -  analog dem Verhalten einiger amphoterer Hydroxyde wie Zink-, Aluminium- oder Antimon(III)-hydroxyd in Wasser  -  das Vorhandensein amphoterer Sulfite. Als solche amphoteren Sulfite in verflüssigtem Schwefeldioxyd erwiesen sich nun, wie die vorstehend mitgeteilten Untersuchungen lehrten, die Sulfite bzw. Oxyd- Solvate unbestimmter Zusammensetzung des Aluminiums, des 4-wertigen Zinns, des Siliciums, des drei- und fünfwertigen Antimons und des Galliums. Ihre Chloride sind in verflüssigtem Schwefeldioxyd löslich, durch Zugabe von basenanalogem Tetramethylammoniumsulfit fallen die schwer löslichen Sulfite der genannten Metalle aus, durch einen Überschuß des Fällungsreagenses gehen sie, wenn sie nicht gealtert sind, als Sulfitoaluminate, -stamate, -silikate, -antimonite, -antimonate und -gallate wieder in Lösung. Durch konduktometrische Titrationen konnten die hier obwaltenden Verhältnisse weitgehend geklärt werden. Metallisches Zinn geht in einer Auflösung von basenanalogem Tetramethylammoniumsulfit in verflüssigtem Schwefeldioxyd als Sulfitostannat in Lösung. Der Reaktionsmechanismus dieses Auflösungsvorganges wird näher untersucht und dargestellt.
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