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 Decade: 1940-1949
 Year: 1941
 Collection: National Advisory Committee for Aeronautics Collection
The additional-mass effect of plates as determined by experiments

The additional-mass effect of plates as determined by experiments

Date: January 1, 1941
Creator: Gracey, William
Description: The apparent increase in the inertia properties of a body moving in a fluid medium has been called the additional-mass effect. This report presents a resume of test procedures and results of experimental determinations of the additional-mass effect of flat plates. In addition to data obtained from various foreign sources and from a NACA investigation in 1933, the results of tests recently conducted by the National Advisory Committee for Aeronautics are included.
Contributing Partner: UNT Libraries Government Documents Department
Additional power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps

Additional power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps

Date: October 1, 1941
Creator: Lowry, John G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a slot-lip aileron and slotted flap for dive brakes

Aerodynamic characteristics of a slot-lip aileron and slotted flap for dive brakes

Date: April 1, 1941
Creator: Rogallo, F M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic factors affecting the ability of a pilot to return an airplane to level from a banked attitude by use of the rudder alone and without change of heading

Aerodynamic factors affecting the ability of a pilot to return an airplane to level from a banked attitude by use of the rudder alone and without change of heading

Date: October 1, 1941
Creator: Harmon, S M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamics of a wind-tunnel fan

The aerodynamics of a wind-tunnel fan

Date: January 1, 1941
Creator: Corson, Blake W
Description: The vortex blade-element theory modified to apply to an axial fan working in a duct is reviewed. Thrust and power coefficients for a fan are identified with the corresponding coefficients for airplane propellers. The relation of pressure produced by the fan to the blade-element coefficients is developed. The distribution of axial velocity of fluid through a fan is assumed to be controlled by the fan itself. The radial distribution of tangential velocity imported by the fan to fluid moving through the fan is shown to be independent of the axial-velocity distribution. A nondimensional coefficient, designated the rotation constant, is introduced. This constant is based solely upon design information. The use of the rotation constant in simplifying the design of a fan for a specific operating condition is demonstrated. Based on the use of the rotation constant, a graphical method is outlined by which the performance of a given fan in a given wind tunnel may be predicted and by which the distributions of axial velocity of the fluid through the fan under various operating conditions may be established.
Contributing Partner: UNT Libraries Government Documents Department
Air transport by gliders : some technical observations

Air transport by gliders : some technical observations

Date: June 1, 1941
Creator: Stepniewski, Wieslaw
Description: This short analysis may be useful in determining the real tactical possibilities of "glider trains" and in adopting the course to be followed in possible studies of these questions. In this analysis most prominent are: (a) the power required for the train in level flight; (b) its speed; (c) climb; and (d) the type of airplane best suited for towing as well as design requirements for transport gliders.
Contributing Partner: UNT Libraries Government Documents Department
Aluminum-zinc-magnesium-copper casting alloys

Aluminum-zinc-magnesium-copper casting alloys

Date: July 1941
Creator: Kempf, L. W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis and prediction of longitudinal stability of airplanes

Analysis and prediction of longitudinal stability of airplanes

Date: January 1, 1941
Creator: Gilruth, R R & White, M D
Description: An analysis has been made of the longitudinal stability characteristics of 15 airplanes as determined in flight. In the correlation of satisfactory and unsatisfactory characteristics with determined values, the derivative that expresses the ratio of static-restoring moments to elevator-control moments was found to represent most nearly the stability characteristics appreciated by the pilots. The analysis was extended to study the effects of various design features on the observed stability characteristics. Design charts and data are included that show the effects on longitudinal stability of relative positions of wing and tail, fuselage size and location, engine nacelles, and horizontal-tail arrangements.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of ground effect on the lifting airscrew

Analysis of ground effect on the lifting airscrew

Date: December 1, 1941
Creator: Knight, Montgomery & Hegner, Ralph A
Description: A study is presented of ground effect as applied to the lifting airscrew of the type used in modern gyroplane and helicopters. The mathematical analysis of the problem has been verified by tests made of three rotor models in the presence of a large circular "ground plane." A method of approximating the decelerating effect during vertical approach to the ground has been devised. The results of the study are presented in the form of convenient charts.
Contributing Partner: UNT Libraries Government Documents Department
An analysis of the stability of an airplane with free controls

An analysis of the stability of an airplane with free controls

Date: January 1, 1941
Creator: Jones, Robert T & Cohen, Doris
Description: Report presents the results of an investigation made of the essentials to the stability of an airplane with free control surfaces. Calculations are based on typical airplane characteristics with certain factors varied to cover a range of current designs. Stability charts are included to show the limiting values of the aerodynamic hinge moments and the weight hinge moments of the control surfaces for various positions of the center of gravity of the airplane and for control systems with various moments of inertia. The effects of reducing the chord and of eliminating the floating tendency of the surface, of changing the wing loading, and of decreasing the radius of gyration of the airplane are also indicated. An investigation has also been made of the nature of the motion of the airplane with controls free and of the modes of instability that may occur.
Contributing Partner: UNT Libraries Government Documents Department
Analytical determination of control system pulley-axis angles

Analytical determination of control system pulley-axis angles

Date: September 1, 1941
Creator: Driggs, H I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analytical study of wing and tail loads associated with an elevator deflection

An analytical study of wing and tail loads associated with an elevator deflection

Date: June 1, 1941
Creator: Garvin, J B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Annual report of the National Advisory Committee for Aeronautics (26th).administrative report including Technical Report nos. 681 to 703

Annual report of the National Advisory Committee for Aeronautics (26th).administrative report including Technical Report nos. 681 to 703

Date: January 1, 1941
Creator: unknown
Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Contributing Partner: UNT Libraries Government Documents Department
An apparatus for measuring rates of discharge of a fuel-injection system

An apparatus for measuring rates of discharge of a fuel-injection system

Date: January 1, 1941
Creator: Dutee, Francis J
Description: A portable apparatus for rapidly determining rates of discharge of a fuel-injection system is described. Satisfactory operation of this apparatus with injection-pump speeds up to 2400 r.p.m was obtained. Rate-of-discharge tests were made with several cam-plunger-valve injection systems with long injection tubes. A check valve designed to reduce secondary discharges was tested. This check valve was operated with injection-pump speeds up to 2400 r.p.m without the occurrence of large secondary discharges.
Contributing Partner: UNT Libraries Government Documents Department
Boundary layer removal by suction

Boundary layer removal by suction

Date: April 1, 1941
Creator: Schrenk, O
Description: Flight-test data and wind-tunnel data on suction profiles are substantially in agreement. The lift values found in the model test can be actually flown and used as a basis for the design. To visualize the action of the suction, the flow conditions with and without suction on the upper surface were photographed; figures 12 to 15 are sections of the film.
Contributing Partner: UNT Libraries Government Documents Department
Buckling tests on eccentrically loaded beam columns

Buckling tests on eccentrically loaded beam columns

Date: October 1, 1941
Creator: Cassens, J
Description: Formulas are obtained for computing the buckling load of rods eccentrically loaded at each end, the computation being extended in particular to the inelastic range. The test results are graphically presented on three sets of curves. Two of these, at least for the elastic range, are independent of the material tested. The third set, which is independent of the material, possesses greater clearness and is therefore used for comparing the test results with the theoretical.
Contributing Partner: UNT Libraries Government Documents Department
The calculation of span LCAD distributions of swept-back wings

The calculation of span LCAD distributions of swept-back wings

Date: December 1, 1941
Creator: Mutterperl, William
Description: Span load distributions of swept-back wings have been calculated. The method used was to replace the wing with a bound vortex at the quarter-chord line and to calculate the downwash due to the system of bound and trailing vortices to conform at the three-quarter-chord line to the slope of the flat-plate wing surface. Results are given for constant-chord and 5:1 tapered plan forms, for sweep-back angles of 0 degrees, 30 degrees, and 45 degrees, and for aspect ratios of 3, 6, and 9. Some comments on the stalling of swept-back wings are included.
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of NACA 4400R Series Rectangular and Tapered Airfoils, Including the Effect of Split Flaps

Characteristics of NACA 4400R Series Rectangular and Tapered Airfoils, Including the Effect of Split Flaps

Date: January 1, 1941
Creator: Greenberg, Harry
Description: No abstract available.
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of NACA 4400R Series Rectangular and Tapered Airfoils, Including the Effect of Split Flaps

Characteristics of NACA 4400R Series Rectangular and Tapered Airfoils, Including the Effect of Split Flaps

Date: January 1941
Creator: Greenberg, Harry
Description: At the request of the Bureau of Aeronautics, Navy Department, tests were made in the variable-density wind tunnel of a tapered wing of 3-10-18 plan form and based on the NACA 4400R series sections. The wing was also tested with 0.2 chord spit flaps, deflected 60 deg span ratios of 0.3, 0.5, 0.7 and 1.0 respectively. In order to get data from which to calculate the characteristics of the flapped wing, the investigation was extended to include tests of the four rectangular airfoils of the NACA 4400R series (4409R, 4412R, 4415R, and 4418R) with full-span 0.2 chord, trailing edge split flaps deflected 60 deg.
Contributing Partner: UNT Libraries Government Documents Department
Combined beam-column stresses of aluminum-alloy channel sections

Combined beam-column stresses of aluminum-alloy channel sections

Date: September 1, 1941
Creator: Hutton, J O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of automatic control systems

Comparison of automatic control systems

Date: February 1, 1941
Creator: Oppelt, W
Description: This report deals with a reciprocal comparison of an automatic pressure control, an automatic rpm control, an automatic temperature control, and an automatic directional control. It shows the difference between the "faultproof" regulator and the actual regulator which is subject to faults, and develops this difference as far as possible in a parallel manner with regard to the control systems under consideration. Such as analysis affords, particularly in its extension to the faults of the actual regulator, a deep insight into the mechanism of the regulator process.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Intercooler Characteristics

Comparison of Intercooler Characteristics

Date: May 1, 1941
Creator: Reuter, J. George & Valerino, Michael F.
Description: A method is presented of comparing the performance, weight, and general dimensional characteristics of inter-coolers. The performance and dimensional characteristics covered in the comparisons are cooling effectiveness, pressure drops and weight flows of the charge and cooling air, power losses, volume, frontal area, and width. A method of presenting intercooler data is described in which two types of charts are plotted; (1) A performance chart setting forth all the important characteristics of a given intercooler and (2) a replot of these characteristics for a number of intercoolers intended to assist in making a selection to satisfy a given set of installation conditions. The characteristics of commercial intercoolers obtained from manufacturers' data and of some computed designs are presented on this basis. A standard test procedure and instrumentation are suggested whereby comparable data may be obtained by different testing organizations.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of stress-strain curves obtained by single-thickness and pack methods

Comparison of stress-strain curves obtained by single-thickness and pack methods

Date: August 1, 1941
Creator: Paul, D A; Howell, F M & Grieshaber, H E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Vee-Type and Conventional Tail Surfaces in Combination with Fuselage and Wing in the Variable-Density Tunnel

Comparison of Vee-Type and Conventional Tail Surfaces in Combination with Fuselage and Wing in the Variable-Density Tunnel

Date: July 1, 1941
Creator: Greenberg, Harry
Description: The pitching and the yawing moments of a vee-type and a conventional type of tail surface were measured. The tests were made in the presence of a fuselage and a wing-fuselage combination in such a way as to determine the moments contributed by the tail surfaces. The results showed that the vee-type tail tested, with a dihedral angle of 35.3 deg, was about 71 percent as effective in pitch as the conventional tail and had a yawing-moment to pitching-moment ratio of 0.3. The conventional tail, the panels of which were all congruent to those of the vee-type tail, had a yawing-moment to pitching-moment ratio of 0.48. These ratios are in fair agreement with values calculated by methods shown in this and previous reports. The values of the measured moments were reduced from 15 to 25 percent of the calculated value by fuselage interference.
Contributing Partner: UNT Libraries Government Documents Department
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