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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Tests and approximate analysis of bending stresses due to torsion in a D-section box
No Description digital.library.unt.edu/ark:/67531/metadc62211/
Tests at Mach number 1.62 of a series of missile configurations having tandem cruciform lifting surfaces
No Description digital.library.unt.edu/ark:/67531/metadc59243/
Tests for determining the effect of a rotating cylinder fitted into the leading edge of an airplane wing
Experiments were performed with a wing model, to which a rotary cylinder had been fitted. The rotation of the cylinder had a remarkable effect on the aerodynamic properties of the wing. digital.library.unt.edu/ark:/67531/metadc65163/
Tests for the determination of the stress condition in tension fields
The present experiments treat the stress of actual tension fields within the elastic range. They give the magnitude of the flexural stresses due to wrinkling. They also disclose, particularly by slightly exceeded buckling load, the marked unloading - as compared with the tension-field theory - of the uprights as a result of the flexural stiffness of the web plate. The test sheets were clamped at the edges and brought to buckling through shearing and compressive stresses applied in the direction of the long sides. digital.library.unt.edu/ark:/67531/metadc63395/
Tests for the elimination of tail flutter
On various low-wing monoplanes the horizontal tail surfaces flutter in flight at large angles of attack and occasionally in curvilinear flight. This flutter leads to torsional vibrations of the rear end of the fuselage, as manifested by vibrations of the control stick. According to the earlier DVL investigations tail flutter is due to the influence, on horizontal tail surfaces, of eddies or vortices shed at large angles of attack by the upper surface of the wing root. The cause of tail flutter on a low-wing monoplane and the means of preventing it are investigated in the present report. digital.library.unt.edu/ark:/67531/metadc63539/
Tests in the 19-foot pressure tunnel of a 1/2.75-scale model of the F4U-1 airplane with several balanced elevators, full-span flaps, and droppable gas tank
No Description digital.library.unt.edu/ark:/67531/metadc62595/
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with a variable-incidence triangular wing and an all-movable horizontal tail
No Description digital.library.unt.edu/ark:/67531/metadc59606/
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : lateral characteristics
No Description digital.library.unt.edu/ark:/67531/metadc59909/
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : longitudinal characteristics
No Description digital.library.unt.edu/ark:/67531/metadc58757/
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 3 triangular wing and an all-movable horizontal tail : longitudinal and lateral characteristics
No Description digital.library.unt.edu/ark:/67531/metadc59487/
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 4 triangular wing and an all-movable horizontal tail - longitudinal characteristics
No Description digital.library.unt.edu/ark:/67531/metadc59006/
Tests in the Ames 40- by 80-foot wind tunnel of an airplane model with an aspect ratio 4 triangular wing and an all-movable horizontal tail - high-lift devices and lateral controls
No Description digital.library.unt.edu/ark:/67531/metadc59454/
Tests in the Ames 40- by 80-foot wind tunnel of the aerodynamic characteristics of airplane models with plain spoiler ailerons
No Description digital.library.unt.edu/ark:/67531/metadc60805/
Tests in the Ames 40- by 80-foot wind tunnel of the effects of varying wing modifications on the longitudinal characteristics of two-triangular wing airplane models with and without horizontal tails
No Description digital.library.unt.edu/ark:/67531/metadc60481/
Tests in the Ames 40- by 80-foot wind tunnel of two airplane models having aspect ratio 2 trapezoidal wings of taper ratios 0.33 and 0.20
No Description digital.library.unt.edu/ark:/67531/metadc59493/
Tests in the gust tunnel of a model of the XBM-1 airplane
No Description digital.library.unt.edu/ark:/67531/metadc55059/
Tests in the NACA two-dimensional low-turbulence tunnel of airfoil sections designed to have small pitching moments and high lift-drag ratios
No Description digital.library.unt.edu/ark:/67531/metadc61371/
Tests in the Variable-Density Tunnel of Seven Tapered Wings Having N.A.C.A. 230 Mean Lines, Special Report
At the request of the Materiel Division of the Army Air Corps, seven tapered wings having sections based on the N.A,C.A. 230 mean line were tested in the variable-density wind tunnel, The characteristics of the wings are given. digital.library.unt.edu/ark:/67531/metadc65156/
Tests in the variable-density wind tunnel of related airfoils having the maximum camber unusually far forward
A family of related airfoils having the position of maximum camber unusually far forward was investigated in the variable-density tunnel as an extension of the study recently completed of a large number of related airfoils. The new airfoils gave improved characteristics over those previously investigated, especially in regard to the pitching moment. Some of the new sections are markedly superior to well-known and commonly used sections and should replace them in applications requiring a slightly cambered section of moderate thickness having a small pitching-moment coefficient. digital.library.unt.edu/ark:/67531/metadc66193/
Tests in the variable-density wind tunnel of the NACA 23012 airfoil with plain and split flaps
Section characteristics for use in wing design are presented for the NACA 23012 airfoil with plain and split flaps of 20 percent wing chord at a value of the effective Reynolds number of about 8,000,000. The flap deflections covered a range from 60 degrees upward to 75 degrees downward for the plain flap and from neutral to 90 degrees downward for the split flap. The split flap was aerodynamically superior to the plain flap in producing high maximum lift coefficients and in having lower profile-drag coefficients at high lift coefficients. digital.library.unt.edu/ark:/67531/metadc66319/
Tests in the Variable Density Wind Tunnel to Investigate the Effects of Scale and Turbulence on Airfoil Characteristics
The effect of scale and turbulence on the lift and drag of five airfoils the NACA 0006, the NACA 0021, the Clark Y and the USA 35-A, and the USN PS6, have been investigated in the Variable Density Wind Tunnel of the NACA. Tests were made over a wide scale range for only two different conditions of turbulence. digital.library.unt.edu/ark:/67531/metadc54044/
Tests of 10-inch 24S-T aluminum-alloy shear panels with 1-1/2-inch holes I
No Description digital.library.unt.edu/ark:/67531/metadc62245/
Tests of 10 inch 24S-T aluminum-alloy shear panels with 1-1/2 inch holes II : panels having holes with notched edges
No Description digital.library.unt.edu/ark:/67531/metadc62248/
Tests of 16 related airfoils at high speed
In order to provide information that might lead to the development of better propeller section, 13 related symmetrical airfoils were tested in the NACA high-speed wind tunnel for a study of the effect of thickness form on the aerodynamic characteristics. The thickness-form variables studies were the value of the maximum thickness, the position along the chord at which the maximum thickness occurs, and the value of the leading-edge radius. The tests were conducted through the low angle-of-attack range for speeds extending from 35 percent of that of sound to slightly in excess of the speed at which a compressibility burble, or breakdown of flow, occurs. The corresponding Reynolds number range is 350,000 to 750,000. digital.library.unt.edu/ark:/67531/metadc66149/
Tests of a 0.30 scale semispan model of the Douglas XTB2D-1 airplane wing and fuselage combination in the NACA 19-foot pressure tunnel I : full-span flap and air-brake investigation
No Description digital.library.unt.edu/ark:/67531/metadc61205/
Tests of a 0.30-scale semispan model of the Douglas XTB2D-1 airplane wing and fuselage combination in the NACA 19-foot pressure tunnel II : roll-flap positioning and lateral-control investigation
No Description digital.library.unt.edu/ark:/67531/metadc61208/
Tests of a 0.1475c aileron with a tab on low-drag section for Curtiss XP-60 airplane in the low-turbulence tunnel
No Description digital.library.unt.edu/ark:/67531/metadc61640/
Tests of a 1/7-scale powered model of the Kaiser tailless airplane in the Langley full-scale tunnel
No Description digital.library.unt.edu/ark:/67531/metadc61218/
Tests of a 1/7-Scale Semispan Model of the XB-35 Airplane in the Langley 19-Foot Pressure Tunnel
A 1/7 scale semispan model of the XB-35 airplane was tested in the Langley 10 foot pressure tunnel, primarily for the purpose of investigating the effectiveness of a leading-edge slot for alleviation of stick-fixed longitudinal instability at high angles of attack caused by early tip stalling and a device for relief of stick-free instability caused by elevon up-floating tendencies at high angles of attack. Results indicated that the slot was not adequate to provide the desired improvement in stick-fixed stability. The tab-flipper device provided improvement in stick-free stability abd two of the linkage combinations tested gave satisfactory variations of control force with airspeed for all conditions except that in which the wing-tip "pitch-control" flap was fully deflected. However, the improvement in control force characteristics was accompanied by a detrimental effect on stick-fixed stability because of the pitching moments produced by the elevon tab deflection. digital.library.unt.edu/ark:/67531/metadc64054/
Tests of a 1/14-scale powered model of the XB-36 airplane in the Langley 19-foot pressure tunnel I : stalling characteristics and aileron effectiveness of several wing and flap arrangements
No Description digital.library.unt.edu/ark:/67531/metadc61189/
Tests of a 1/17-scale model of the XBDR-1 airplane in the NACA gust tunnel
No Description digital.library.unt.edu/ark:/67531/metadc61102/
Tests of a 1/40-scale wing-hull model and a 1/10-scale float-strut model of the Hughes-Kaiser cargo airplane in the two-dimensional low-turbulence pressure tunnel
No Description digital.library.unt.edu/ark:/67531/metadc60857/
Tests of a 45 degree sweptback-wing model in the Langley gust tunnel
No Description digital.library.unt.edu/ark:/67531/metadc54511/
Tests of a centering spring used as an artificial feel device on the elevator of a fighter airplane
No Description digital.library.unt.edu/ark:/67531/metadc59301/
Tests of a contra-propeller for aircraft
Tests of an 8-blade contra-propeller of 32-inch diameter in combination with a 4-inch, 36-inch diameter adjustable pitch, metal propeller at pitch setting of 15, 25, 35, and 45 degrees at 0.75 R were made. The tests showed a significant increase in effective thrust of the combination over that of the propeller alone for value V/nD somewhat below those for maximum efficiency and without a corresponding increase of power absorbed. From 1/2 percent to 2-1/2 percent in propulsive efficiency was thus gained in this range. In all but one case, however, the peak propulsive efficiency of the combination was found to be from 1 to 2 percent less than that of the propeller alone. Counter torque on the contra-propeller amounted to about 50 percent of the propeller torque. digital.library.unt.edu/ark:/67531/metadc54515/
Tests of a dynamic model in NACA tank number 1 to determine the effect of length of afterbody, angle of afterbody keel, gross load, and a pointed step on landing and planning stability
No Description digital.library.unt.edu/ark:/67531/metadc60839/
Tests of a full-scale horizontal tail surface in the Langley 16-foot high-speed tunnel
No Description digital.library.unt.edu/ark:/67531/metadc54982/
Tests of a Full-Scale Model of the Republic XF-91 Airplane in the Ames 40- by 80-Foot Wind Tunnel. Force and Moment Data
Wind-tunnel tests of a full-scale model of the Republic XF-91 airplane having swept-back wings and a vee tail were conducted to determine both the stability and control characteristics of the model longitudinally, laterally, and directionally. Configurations of the model were investigated involving such variables as external fuel tanks, a landing gear, trailing-edge flaps, leading-edge slats, and a range of wing incidences and tail incidences. digital.library.unt.edu/ark:/67531/metadc65586/
Tests of a gust-alleviating flap in the gust tunnel
Tests were made to determine the effectiveness of a long-period dynamically overbalanced flap in reducing airplane accelerations due to atmospheric gusts. For two gust shapes, one gust velocity, one forward velocity, and one wing loading, a series of flights was made with the flap locked and was then repeated with the flap free to operate. The records were evaluated by routine methods. The results indicate that the flap reduced the maximum acceleration increment 39 percent for a severe gust but with a representative gust shape (a sharp-edge gust), the reduction was only 3 percent. The results also indicate that the flap tended to reduce the longitudinal stability of the airplane. Computations made of the effectiveness and the action of the flap were in good agreement with the experimental results. digital.library.unt.edu/ark:/67531/metadc54546/
Tests of a gust-alleviating wing in the gust tunnel
Tests were made in the NACA gust tunnel to determine the effectiveness of a torsionally flexible wing with the torsion axis ahead of the locus of the section aerodynamic centers in reducing airplane accelerations due to atmospheric gusts. For three gust shapes, a series of flights was made with the airplane model equipped with either a torsionally flexible or a rigid wing. The results indicated that the torsionally flexible wing reduced the maximum acceleration increment 5 percent for the sharp-edge gust and about 17 percent for gust shapes with gradient distances of 6.8 and 15 chord lengths. The analysis indicated that the effectiveness of this method of gust alleviation was independent of the gust velocity and that, for the same total load increment, the torsionally flexible wing would have 10 percent less bending-moment increment at the root section of the wing than a rigid wing in all but the sharpest gusts. The results also indicated that the torsionally flexible wing slightly increased the longitudinal stability of the airplane model in a gust. digital.library.unt.edu/ark:/67531/metadc53667/
Tests of a heated low-drag airfoil
No Description digital.library.unt.edu/ark:/67531/metadc53383/
Tests of a Hermes A-2 Missile Body at Mach Number 4.04
Force tests on a proposed body shape of the Hermes A-2 missile with and without longitudinal spoilers were made at Mach number 4.04. Values of normal force coefficient, pitching-moment coefficient, and center-of-pressure position were obtained. digital.library.unt.edu/ark:/67531/metadc64679/
Tests of a Highly Cambered Low-Drag-Airfoil Section with a Lift-Control Flap, Special Report
Tests were made in the NACA two-dimensional low turbulence pressure tunnel of a highly cambered low-drag airfoil (NACA 65,3-618) with a plain flap designed for lift control. The results indicate that such a combination offers attractive possibilities for obtaining low profile-drag coefficients over a wide range of lift coefficients without large reductions of critical speed. digital.library.unt.edu/ark:/67531/metadc65162/
Tests of a Horizontal-Tail Model through the Transonic Speed Range by the NACA Wing-Flow Method
A 1/12-scale model of a horizontal tail of a fighter airplane was tested through the transonic speeds in the high-speed flow over an airplane wing, the surface of which served as a reflection plane for the model. Measurements of lift, elevator-hinge moment, angle of attack, and elevator angle were made in the Mach number range from 0.75 to 1.04 for elevator deflections ranging from 10 degrees to minus 10 degrees, and for angles of attack of minus 1.2 degrees, 0.4 degrees, and 3.4 degrees. The equipment used to measure the hinge moments of the model proved to be unsatisfactory, and for this reason the hinge-moment data are considered to be only qualitative. digital.library.unt.edu/ark:/67531/metadc63801/
Tests of a Large Boiler Fired with Powdered Coal at the Lakeside Station, Milwaukee
No Description digital.library.unt.edu/ark:/67531/metadc12420/
Tests of a large spherical turret and a modified turret on a typical bomber fuselage
No Description digital.library.unt.edu/ark:/67531/metadc62426/
Tests of a linked differential flap system designed to minimize the reduction in effective dihedral caused by power
No Description digital.library.unt.edu/ark:/67531/metadc61543/
Tests of a model horizontal tail of aspect ratio 4.5 in the Ames 12-foot pressure wind tunnel I : quarter-chord line swept back 35 degrees
No Description digital.library.unt.edu/ark:/67531/metadc58274/
Tests of a Northrop XSSM-A-3 Missile in the Ames 40- by 80-Foot Wind Tunnel: Stability and Control
This report presents the results of wind-tunnel force tests which were conducted to determine the low-speed stability and control characteristics of a full-scale Northrop XSSM-A-3 missile. Tests were made through a range of angles of attack, sideslip, and control deflection, and at various Reynolds numbers. Characteristics of the complete missile are compared with the characteristics of the missile with the landing skids extended, with the vertical tail removed, and with the fuselage alone. No analysis of the data has been made in order to make the results available as soon as possible. digital.library.unt.edu/ark:/67531/metadc64101/
Tests of a Powdered-Coal Plant: A Report of Investigations at the Power Plant of the St. Joseph Lead Co., Rivermines, Missouri
Technical paper issued by the Bureau of Mines over tests conducted at the powdered-coal plant in Rivermines, Missouri. The results of boiler tests, dryer tests, and mill tests are discussed. This report includes tables, and illustrations. digital.library.unt.edu/ark:/67531/metadc66386/