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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Year: 1932
 Collection: National Advisory Committee for Aeronautics Collection
Accurate calculation of multispar cantilever and semicantilever wings with parallel webs under direct and indirect loading

Accurate calculation of multispar cantilever and semicantilever wings with parallel webs under direct and indirect loading

Date: March 1932
Creator: Sanger, Eugen
Description: In the present report the computation is actually carried through for the case of parallel spars of equal resistance in bending without direct loading, including plotting of the influence lines; for other cases the method of calculation is explained. The development of large size airplanes can be speeded up by accurate methods of calculation such as this.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of a model wing having a split flap deflected downward and moved to the rear

The aerodynamic characteristics of a model wing having a split flap deflected downward and moved to the rear

Date: May 1, 1932
Creator: Weick, Fred E & Harris, Thomas E
Description: Tests were made on a model wing with three different sized split trailing-edged flaps, in the NACA 7 by 10 foot wind tunnel. The flaps were formed of the lower rear portion of the wing and were rotated downward about axes at their front edges. The lift, drag, and center of pressure were measured with the axis in its original position and also with it moved back in even steps to the trailing edge of the main wing, giving in effect an increase in area. The split flaps when deflected about their original axis locations gave slightly higher maximum lift coefficients than conventional trailing-edge flaps, and the lift coefficients were increased still further by moving the axes toward the rear. The highest value of C(sub L max), which was obtained with the largest flap hinged at 90 per cent of the chord from the leading edge, was 2.52 as compared with 1.27 for the basic wing.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of a slotted Clark y wing as affected by the auxiliary airfoil position

The aerodynamic characteristics of a slotted Clark y wing as affected by the auxiliary airfoil position

Date: January 1, 1932
Creator: Wenzinger, Carl J & Shortal, Joseph A
Description: Aerodynamic force tests on a slotted Clark Y wing were conducted in a vertical wind tunnel to determine the best position for a given auxiliary airfoil with respect to the main wing. A systematic series of 100 changes in location of the auxiliary airfoil were made to cover all the probable useful ranges of slot gap, slot width, and slot depth. The results of the investigation may be applied to the design of automatic or controlled slots on wings with geometric characteristics similar to the wing tested. The best positions of the auxiliary airfoil were covered by the range of the tests, and the position for desired aerodynamic characteristics may easily be obtained from charts prepared especially for the purpose.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of airfoils at negative angles of attack

The aerodynamic characteristics of airfoils at negative angles of attack

Date: March 1, 1932
Creator: Anderson, Raymond F
Description: A number of airfoils, including 14 commonly used airfoils and 10 NACA airfoils, were tested through the negative angle-of-attack range in the NACA variable-density wind tunnel at a Reynolds Number of approximately 3,000,000. The tests were made to supply data to serve as a basis for the structural design of airplanes in the inverted flight condition. In order to make the results immediately available for this purpose they are presented herein in preliminary form, together with results of previous tests of the airfoils at positive angles of attack. An analysis of the results made to find the variation of the ratio of the maximum negative lift coefficient to the maximum positive lift coefficient led to the following conclusions: 1) For airfoils of a given thickness, the ratio -C(sub L max) / +C(sub L max) tends to decrease as the mean camber is increased. 2) For airfoils of a given mean camber, the ratio -C(sub L max) / +C(sub L max) tends to increase as the thickness increases.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of circular-arc airfoils at high speeds

Aerodynamic characteristics of circular-arc airfoils at high speeds

Date: January 1, 1932
Creator: Briggs, L. J. & Dryden, H. L.
Description: The aerodynamic characteristics of eight circular-arc airfoils at speeds of 0.5, 0.8, 0.95, and 1.08 times the speed of sound have been determined in an open-jet air stream 2 inches in diameter, using models of 1-inch chord. The lower surface of each airfoil was plane; the upper surface was cylindrical. As compared with the measurements described in NACA-TR-319, the circular-arc airfoils at speeds of 0.95 and 1.08 times the speed of sound are more efficient than airfoils of the R. A. F. or Clark Y families. At a speed of 0.5 times the speed of sound, the thick circular-arc sections are extremely inefficient, but thin sections compare favorably with those of the R. A. F. family. A moderate round of the sharp edges changes the characteristics very little and is in many instances beneficial. The results indicate that the section of the blades of propellers intended for use at high tip-speeds should be of the circular-arc form for the outer part of the blade and should be changed gradually to the R. A. F. or Clark Y form as the hub is approached.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of eight very thick airfoils from tests in the variable density wind tunnel

The aerodynamic characteristics of eight very thick airfoils from tests in the variable density wind tunnel

Date: January 1, 1932
Creator: Jacobs, Eastman N
Description: Report presents the results of wind tunnel tests on a group of eight very thick airfoils having sections of the same thickness as those used near the roots of tapered airfoils. The tests were made to study certain discontinuities in the characteristic curves that have been obtained from previous tests of these airfoils, and to compare the characteristics of the different sections at values of the Reynolds number comparable with those attained in flight. The discontinuities were found to disappear as the Reynolds number was increased. The results obtained from the large-scale airfoil, a symmetrical airfoil having a thickness ratio of 21 per cent, has the best general characteristics.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic safety of airplanes

The aerodynamic safety of airplanes

Date: September 1, 1932
Creator: Kahn, Louis
Description: This report presents several hypotheses regarding airplane safety, mainly concerning the nondimensional coefficient of air, speed, acceleration, and wing area on aerodynamic considerations of safety.
Contributing Partner: UNT Libraries Government Documents Department
Airplane flight in the stratosphere

Airplane flight in the stratosphere

Date: February 1, 1932
Creator: De Caria, Ugo
Description: This brief survey of the problems encountered in high-altitude flight deals in particular with the need for high lift coefficient in the wings, large aspect ratios in the wings, and also the problem of hermetically sealing the cabin.
Contributing Partner: UNT Libraries Government Documents Department
Airplane stability in taxying

Airplane stability in taxying

Date: September 1, 1932
Creator: Anderlik, E
Description: The stability analysis of an airplane while rolling is much more simplified to the extent that it can be obtained for numerical data which can be put to practical use in the design of landing gear dimensions. Every landing gear type attains to a critical ground friction coefficient that decides the beginning of instability, i.e., nosing over. This study has, in addition, a certain interest for the use of wheel brakes.
Contributing Partner: UNT Libraries Government Documents Department
Airship model tests in the variable density wind tunnel

Airship model tests in the variable density wind tunnel

Date: January 1, 1932
Creator: Abbott, Ira H
Description: This report presents the results of wind tunnel tests conducted to determine the aerodynamic characteristics of airship models. Eight Goodyear-Zeppelin airship models were tested in the original closed-throat tunnel. After the tunnel was rebuilt with an open throat a new model was tested, and one of the Goodyear-Zeppelin models was retested. The results indicate that much may be done to determine the drag of airships from evaluations of the pressure and skin-frictional drags on models tested at large Reynolds number.
Contributing Partner: UNT Libraries Government Documents Department
Annual report of the National Advisory Committee for Aeronautics (17th).administrative report including Technical Report nos. 365 to 400

Annual report of the National Advisory Committee for Aeronautics (17th).administrative report including Technical Report nos. 365 to 400

Date: January 1, 1932
Creator: unknown
Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the president, congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Contributing Partner: UNT Libraries Government Documents Department
Application of the theory of free jets

Application of the theory of free jets

Date: April 1, 1932
Creator: Betz, A & Petersohn, E
Description: Based upon Kirchoff's theory of free jets the flow through different screen arrangements of flat plates, as chiefly encountered with turbines in the cavitation zone is defined. It is shown by experiments that these theoretical results are very well representative in most cases of the conditions of discharge from water in air and consequently by cavitation. In addition, the experiments reveal a picture of the discrepancies between the actual flow and the theory of discharge of air in air (of water in water without cavitation). These discrepancies are explained qualitatively by the mingling processes between the jets and the dead air zones.
Contributing Partner: UNT Libraries Government Documents Department
Approximate calculation of multispar cantilever and semicantilever wings with parallel ribs under direct and indirect loading

Approximate calculation of multispar cantilever and semicantilever wings with parallel ribs under direct and indirect loading

Date: August 1, 1932
Creator: Sanger, Eugen
Description: A method is presented for approximate static calculation, which is based on the customary assumption of rigid ribs, while taking into account the systematic errors in the calculation results due to this arbitrary assumption. The procedure is given in greater detail for semicantilever and cantilever wings with polygonal spar plan form and for wings under direct loading only. The last example illustrates the advantages of the use of influence lines for such wing structures and their practical interpretation.
Contributing Partner: UNT Libraries Government Documents Department
Armstrong-Whitworth A.W. XV "Atlanta" airplane (British) : a commercial multiplace cantilever monoplane

Armstrong-Whitworth A.W. XV "Atlanta" airplane (British) : a commercial multiplace cantilever monoplane

Date: August 1, 1932
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Armstrong Whitworth A.W. XVI military Airplane (British) : a single-seat biplane

The Armstrong Whitworth A.W. XVI military Airplane (British) : a single-seat biplane

Date: January 1, 1932
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Automatic stability of airplanes

Automatic stability of airplanes

Date: December 1, 1932
Creator: Haus, FR
Description: It is endeavored in this report to give a full outline of the problem of airplane stability and to classify the proposed solutions systematically. Longitudinal stability, which can be studied separately, is considered first. The combination of lateral and directional stabilities, which cannot be separated, will be dealt with later.
Contributing Partner: UNT Libraries Government Documents Department
The automotive ignition coil

The automotive ignition coil

Date: January 1, 1932
Creator: Darnell, T. H.
Description: This report gives the results of a series of measurements on the secondary voltage induced in an ignition coil of typical construction under a variety of operating conditions. These results show that the theoretical predictions hitherto made as to the behavior of this type of apparatus are in satisfactory agreement with the observed facts. The large mass of data obtained is here published both for the use of other investigators who may wish to compare them with other theoretical predictions and for the use of automotive engineers who will here find definite experimental results showing the effect of secondary capacity and resistance on the crest voltage produced by ignition apparatus.
Contributing Partner: UNT Libraries Government Documents Department
The Avro 631 training airplane (British) : a two-seat light biplane

The Avro 631 training airplane (British) : a two-seat light biplane

Date: May 1, 1932
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Bleriot 137 military airplane (French) : a twin-engine multiplace monoplane

The Bleriot 137 military airplane (French) : a twin-engine multiplace monoplane

Date: August 1, 1932
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Boulton and Paul P.64 mail-carrier : a two-engine all-metal biplane

The Boulton and Paul P.64 mail-carrier : a two-engine all-metal biplane

Date: April 1, 1932
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Breda 32 commercial airplane (Italian) : a three-engine all-metal low-wing monoplane

The Breda 32 commercial airplane (Italian) : a three-engine all-metal low-wing monoplane

Date: August 1, 1932
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Breguet 410 and 411 Military Airplanes (French): Multiplace Sesquiplane Fighters

The Breguet 410 and 411 Military Airplanes (French): Multiplace Sesquiplane Fighters

Date: May 1, 1932
Creator: Leglise, Pierre
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The C.A.M.S. 80 amphibian (French) : an observation monoplane

The C.A.M.S. 80 amphibian (French) : an observation monoplane

Date: March 1, 1932
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculation of potential flow past airship bodies in yaw

Calculation of potential flow past airship bodies in yaw

Date: July 1, 1932
Creator: Lotz, I
Description: An outline of Von Karman's method of computing the potential flow of airships in yaw by means of partially constant dipolar superposition on the axis of the body is followed by several considerations for beginning and end of the superposition. Then this method is improved by postulating a continuous, in part linearly variable dipolar superposition on the axis. The second main part of the report brings the calculation of the potential flow by means of sources and sinks, arranged on the surface of the airship body. The integral equation which must satisfy this surface superposition is posed, and the core reduced to functions developed from whole elliptical normal integrals. The functions are shown diagrammatically. The integration is resolvable by iteration. The consequence of the method is good. The formulas for computing the velocity on the surface and of the potential for any point conclude the report.
Contributing Partner: UNT Libraries Government Documents Department
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