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National Advisory Committee for Aeronautics Collection
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Technical Report Archive and Image Library
- Wing-body combinations with wings of very low aspect ratio at supersonic speeds
- No Description digital.library.unt.edu/ark:/67531/metadc62824/
- Wing-body interference at supersonic speeds with an application to combinations with rectangular wings
- No Description digital.library.unt.edu/ark:/67531/metadc56991/
- Wing characteristics as affected by protuberances of short span
- The drag and interference caused by short-span protuberances from the surface of an airfoil have been investigated in the NACA variable-density wind tunnel at a Reynolds number of approximately 3,100,000, based on the chord length of the airfoil. The effects of variations of protuberance span length, span position, and shape were measured by determining how the wing characteristics were affected by the addition of the various protuberances. digital.library.unt.edu/ark:/67531/metadc66106/
- Wing-dropping characteristics of some straight and swept wings at transonic speeds as determined with rocket-powered models
- No Description digital.library.unt.edu/ark:/67531/metadc58429/
- Wing-flow investigation of the characteristics of seven unswept, untapered airfoils of aspect ratio 8.0
- No Description digital.library.unt.edu/ark:/67531/metadc58865/
- Wing-flow measurements of longitudinal stability and control characteristics of a canard airplane configuration with a 45 degree sweptback wing and a triangular all-movable control surface
- No Description digital.library.unt.edu/ark:/67531/metadc58579/
- Wing-flow measurements of longitudinal stability and control characteristics of a supersonic airplane configuration having a 42.8 degree sweptback circular arc wing with aspect ratio 4.0, taper ratio 0.50, and sweptback tail surfaces
- No Description digital.library.unt.edu/ark:/67531/metadc58540/
- Wing-flow tests of a triangular wing of aspect ratio two I : effectiveness of several types of trailing-edge flaps on flat-plate models
- No Description digital.library.unt.edu/ark:/67531/metadc58153/
- Wing-fuselage interference comparison of conventional and airfoil-type-fuselage combinations
- No Description digital.library.unt.edu/ark:/67531/metadc61155/
- Wing-fuselage interference, tail buffeting, and air flow about the tail of a low-wing monoplane
- This report presents the results of wind tunnel tests on a Mcdonnell Douglas airplane to determine the wing-fuselage interference of a low-wing monoplane. The tests included a study of tail buffeting and the air flow in the region of the tail. The airplane was tested with and without the propeller slipstream, both in the original condition and with several devices designed to reduce or eliminate tail buffeting. The devices used were wing-fuselage fillets, a NACA cowling, reflexed trailing edge of the wing, and stub auxiliary airfoils. digital.library.unt.edu/ark:/67531/metadc66139/
- Wing load distribution on a swept wing airplane in flight at Mach numbers up to 1.11, and comparison with theory
- No Description digital.library.unt.edu/ark:/67531/metadc59109/
- Wing-load measurements at supersonic speeds of the Douglas D-558-II research airplane
- No Description digital.library.unt.edu/ark:/67531/metadc61517/
- Wing-load measurements of the Bell X-5 research airplane at a sweep angle of 58.7 degrees
- No Description digital.library.unt.edu/ark:/67531/metadc61204/
- Wing loads and load distributions throughout the lift range of the Douglas X-3 research airplane at transonic speeds
- No Description digital.library.unt.edu/ark:/67531/metadc64164/
- Wing loads on the Bell X-1 research airplane (10 percent thick wing) as determined by pressure-distribution measurements in flight at subsonic and transonic speeds
- No Description digital.library.unt.edu/ark:/67531/metadc59667/
- Wing-nacelle-propeller interference for wings of various spans force and pressure-distribution tests
- Report presents the results of an experimental investigation made in the NACA full-scale wind tunnel to determine the effect of wing span on nacelle-propeller characteristics and, reciprocally, the lateral extent of nacelle and propeller influence on a monoplane wing. The results provide a check on the validity of the previous research on nacelles and propellers with 15-foot-span wings tested in the 20-foot wind tunnel and reported in technical reports 415, 462, 505, 506, and 507. digital.library.unt.edu/ark:/67531/metadc66227/
- Wing-Nacelle-Propeller Tests - Comparative Tests of Liquid-Cooled and Air-Cooled Engine Nacelles
- This report gives the results of measurements of the lift, drag, and propeller characteristics of several wing and nacelle combinations with a tractor propeller. The nacelles were so located that the propeller was about 31% of the wing chord directly ahead of the leading edge of the wing, a position which earlier tests (NASA Report No. 415) had shown to be efficient. The nacelles were scale models of an NACA cowled nacelle for a radial air-cooled engine, a circular nacelle with the V-type engine located inside and the radiator for the cooling liquid located inside and the radiator for the type, and a nacelle shape simulating the housing which would be used for an extension shaft if the engine were located entirely within the wing. The propeller used in all cases was a 4-foot model of Navy No. 4412 adjustable metal propeller. The results of the tests indicate that, at the angles of attack corresponding to high speeds of flight, there is no marked advantage of one type of nacelle over the others as far as low drag is concerned, since the drag added by any of the nacelles in the particular location ahead of the wing is very small. The completely cowled nacelle for a radial air-cooled engine appears to have the highest drag, the liquid-cooled engine appears to have the highest drag, the liquid-cooled engine nacelle with external radiator slightly less drag. The liquid-cooled engine nacelle with radiator in the cowling hood has about half the drag of the cowled radial air-cooled engine nacelle. The extension-shaft housing shows practically no increase in drag over that of the wing alone. A large part of the drag of the liquid-cooled engine nacelle appears to be due to the external radiator. The maximum propulsive efficiency for a given propeller pitch setting is about 2% higher for the liquid-cooled engine nacelle with the radiator in the cowling hood than that for the other cowling arrangements. digital.library.unt.edu/ark:/67531/metadc65101/
- Wing-on and wing-off longitudinal characteristics of an airplane configuration having an thin unswept tapered wing of aspect ratio 3, as obtained from rocket-propelled models at Mach numbers from 0.8 to 1.4
- No Description digital.library.unt.edu/ark:/67531/metadc58657/
- Wing plan forms for high-speed flight
- It is pointed out that, in the case of an airfoil of infinite aspect ratio moving at an angle of sideslip, the pressure distribution is determined solely by that component of the motion in a direction normal to the leading edge. It follows that the attachment of plane waves to the airfoil at near-sonic or supersonic speeds (Ackeret theory) may be avoided and the pressure drag may be reduced by the use of plan forms in which the angle of sweepback is greater than the Mach angle. The analysis indicates that for aerodynamic efficiency, wings designed for flight at supersonic speeds should be swept back at an angle greater than the Mach angle, and the angle of sweepback should be such that the component of velocity normal to the leading edge is less than the critical speed of the airfoil sections. This principle may also be applied to wings designed for subsonic speeds near the speed of sound, for which the induced velocities resulting from the thickness might otherwise be sufficiently great to cause shock waves. digital.library.unt.edu/ark:/67531/metadc60163/
- Wing plan forms for high-speed flight
- No Description digital.library.unt.edu/ark:/67531/metadc55311/
- Wing pressure distribution and rotor-blade motion of an autogiro as determined in flight
- This report presents the results of tests in which the pressure distribution over the fixed wing of an autogiro was determined in both steady and accelerated flight. In the steady-flight condition, the rotor-blade motion was also measured. These data show that in steady flight the rotor speed as a function of the air speed is largely affected by the variation of the division of load between the rotor and the wing; as the load on the wing increases, the rotor speed decreases. In steady flight the presence of the slipstream increased both the wing lift at a given air speed and the maximum lift coefficient of the wing above the corresponding values without the slipstream. In abrupt high-speed turns, the wing attained a normal force coefficient of unity at almost the initial value of the air speed and experienced its maximum load before maximum acceleration occurred. digital.library.unt.edu/ark:/67531/metadc66132/
- Wing pressure-distribution measurements up to 0.866 Mach number in flight on a jet-propelled airplane
- No Description digital.library.unt.edu/ark:/67531/metadc55313/
- Wing pressure distributions over the lift range of the Convair XF-92A delta-wing airplane at subsonic and transonic speeds
- No Description digital.library.unt.edu/ark:/67531/metadc61544/
- Wing pressure distributions over the lift range of the convair xf-92a delta-wing airplane at subsonic and transonic speeds
- No Description digital.library.unt.edu/ark:/67531/metadc53093/
- Wing resistance near the ground
- In the present treatise, a convenient method will be indicated, which makes it possible to determine the polar curve of an airplane at short distances from the ground by a simple short calculation, when the polar curve is known for flight in unlimited space. digital.library.unt.edu/ark:/67531/metadc54179/
- Wing spar stress charts and wing truss proportions
- In order to simplify the calculation of beams continuous over three supports, a series of charts have been calculated giving the bending moments at all the critical points and the reactions at all supports for such members. Using these charts as a basis, calculations of equivalent bending moments, representing the total stresses acting in two bay-wing trusses of proportions varying over a wide range, have been determined, both with and without allowance for column effect. This leads finally to the determination of the best proportions for any particular truss or the best strut locations in any particular airplane. The ideal proportions are found to vary with the thickness of the wing section used, the aspect ratio, and the ratio of gap to chord. digital.library.unt.edu/ark:/67531/metadc65866/
- Wing-tunnel investigation at high subsonic speeds of the lateral-control characteristics of an aileron and a stepped spoiler on a wing with leading edge swept back 51.3 degrees
- No Description digital.library.unt.edu/ark:/67531/metadc58204/
- Wing-tunnel investigation at low transonic speeds of the effects of number of wings on the lateral-control effectiveness of an RM-5 test vehicle
- No Description digital.library.unt.edu/ark:/67531/metadc58413/
- Wing-tunnel investigation at Mach numbers from 0.50 to 1.29 of an all-movable triangular wing of aspect ratio 4 alone and with a body
- No Description digital.library.unt.edu/ark:/67531/metadc58401/
- Wing-tunnel investigation of effects of forward movements of transition on section characteristics of a low-drag airfoil with a 0.24-chord sealed plain aileron
- No Description digital.library.unt.edu/ark:/67531/metadc55768/
- Wing-tunnel investigation of effects of various aerodynamic balance shapes and sweepback on control-surface characteristics of semispan tail surfaces with NACA 0009, 0015, 66-009, 66(215)-014, and circular-arc airfoil sections
- No Description digital.library.unt.edu/ark:/67531/metadc55844/
- The wing with a pointed tip
- In airplane construction generally one finds an almost exclusive use of wing tips that are practically square end but occasionally those with large rounded tips. For use as a cantilever wing, however, a wing with pointed tips may contain valuable aerodynamic advantages. digital.library.unt.edu/ark:/67531/metadc55794/
- Wings with nozzle-shaped slots
- Even before the publication of the results of the Gottingen experiments on the removal of the boundary layer by suction, experiments with nozzle-slotted wings were begun. A report of those experiments will be given here. Taken collectively, the experiments show that, as regards increasing the lift values, the effect of the air flowing from the nozzle-shaped slots is similar to the effect produced in the case of ordinary slotted wings. The high lift values are attained, however, at the smaller angles of attack employed in ordinary flight. digital.library.unt.edu/ark:/67531/metadc65371/
- Wire cloth as porous material for transpiration-cooled walls
- The permeability characteristics and tensile strength of a porous material developed from stainless-steel corduroy wire cloth for use in transpiration-cooled walls where the primary stresses are in one direction were investigated. The results of this investigation are presented and compared with similar results obtained with porous sintered metal compacts. A much wider range of permeabilities is obtainable with the wire cloth than with the porous metal compacts considered and the ultimate tensile strength in the direction of the primary stresses for porous materials produced from three mesh sizes of wire cloth are from two to three times the ultimate tensile strengths of the porous metal compacts. digital.library.unt.edu/ark:/67531/metadc59042/
- Wire suspensions in wind tunnel experiments
- The elimination of the rigid supports for models and their replacement by wires constitute a great improvement by rendering negligible the interactions of support. There are disadvantages to wire, namely, the aerodynamic resistance is very large and their use is rather difficult because the whole suspension lacks rigidity and easily becomes distorted. We will here investigate the nature of these distortions, evaluate the errors they entail and describe the methods for taking account of or avoiding them. digital.library.unt.edu/ark:/67531/metadc65145/
- Wood versus metal in airplane construction
- The aim of this article is to present, in broad outline, a scientific method for solving the problem, "Wood or Metal." It will be shown that structural methods have by no means reached their final perfection. The strength of the different materials is discussed as well as different construction methods. digital.library.unt.edu/ark:/67531/metadc56078/
- Working charts for the computation of propeller thrust throughout the take-off range
- No Description digital.library.unt.edu/ark:/67531/metadc62157/
- Working charts for the determination of propeller thrust at various air speeds
- A set of propeller performance charts, based on a torque speed coefficient has been constructed from full-sized metal propeller data obtained in the NACA propeller-research tunnel. digital.library.unt.edu/ark:/67531/metadc66138/
- Working charts for the determination of the lift distribution between biplane wings
- In this report are presented empirical working charts from which the distribution of lift between wings, that is the fraction of the total lift borne by each, can be determined in the positive lift range for any ordinary biplane cellule whose individual wings have the same profile. The variables taken directly into account include airfoil section, stagger, gap/chord ratio, decalage, chord ratio, and overhang. It is shown that the influence of unequal sweepback and unequal dihedral in upper and lower wings may be properly provided for by utilizing the concepts of average stagger and average gap/chord ratio, respectively. The effect of other variables is discussed, but they have not been included in the charts either because their influence was obviously small or because insufficient data existed to make possible a complete determination of their influence. All available pertinent biplane data were analyzed in establishing the charts, and in some cases theoretical relationships were utilized to establish qualitative tendencies. digital.library.unt.edu/ark:/67531/metadc66102/
- Working charts for the selection of aluminum alloy propellers of a standard form to operate with various aircraft engines and bodies
- Working charts are given for the convenient selection of aluminum alloy propellers of a standard form, to operate in connection with six different engine-fuselage combinations. The charts have been prepared from full-scale test data obtained in the 20-foot propeller research tunnel of the National Advisory Committee for Aeronautics. An example is also given showing the use of the charts. digital.library.unt.edu/ark:/67531/metadc66002/
- Working charts for the stress analysis of elliptic rings
- This report presents charts which reduce the stress analysis of circular and elliptic rings of uniform cross section subjected to balanced systems of concentrated loads from a statically indeterminate problem to a statically determinate one. To demonstrate the use of the charts in the stress analysis of elliptic rings, an illustrative problem is included. digital.library.unt.edu/ark:/67531/metadc54100/
- The world's air transportation services : data as to passengers, mail, and goods carried by American and European transportation services
- This report presents detailed descriptions, statistics, and graphs on European and American air transport. The European countries listed are Belgium, Czecho-Slovakia, Denmark, France, Germany, Great Britain, Holland, and Italy. digital.library.unt.edu/ark:/67531/metadc55672/
- Wrinkling of reinforced plates subjected to shear stresses
- An analysis is made here of the problem of long plates with transverse stiffeners subject to shear. A typical example would be a long Wagner beam. The shear stress is calculated at which the web wrinkles and shear stress becomes a maximum. The equation is solved for both a condition of free support and rigidity of support on the edges. digital.library.unt.edu/ark:/67531/metadc63635/
- Wrinkling phenomena of thin flat plates subjected to shear stresses
- This report covers a series of tests on thin flat elastic strips restrained at two parallel edges and subjected to shear by conversely directed stresses. Theoretical treatments, particularly those of Lilly, Southwell and Skan, and Timoshenko are briefly outlined. The problem to be solved by these tests was to find out whether, and to what extent the conditions and assumptions upon which the calculations are based are complied with in the tests. Three materials were used: celluloid, duralumin, brass. Owing to the high elastic deformability of celluloid, it was not only possible to observe the beginning but also to ascertain the type of deflection. The test data on celluloid was affirmed by the experiments with duralumin and brass. digital.library.unt.edu/ark:/67531/metadc63636/
- X-ray diffraction by bent crystal lamellae
- No Description digital.library.unt.edu/ark:/67531/metadc55904/
- X-ray diffraction investigation of minor phases of 20 high-temperature alloys
- No Description digital.library.unt.edu/ark:/67531/metadc54566/
- X-Ray Diffraction Study of the Internal Structure of Supercooled Water
- A Bragg X-ray spectrometer equipped with a volume-sensitive Geiger counter and Soller slits and employing filtered molybdenum Ka radiation was used to obtain a set of diffracted intensity curves as a Punction of angle for supercooled water. Diffracted intensity curves in the temperature region of 21 to -16 C were obtained. The minimum between the two main diffraction peaks deepened continuously with lowering temperature, indicating a gradual change in the internal structure of the water. No discontinuity in this trend was noted at the melting point. The internal structure of supercooled water was concluded to become progressively more ice-like as the temperature is lowered. digital.library.unt.edu/ark:/67531/metadc53469/
- X-ray instrumentation for density measurements in a supersonic flow field
- No Description digital.library.unt.edu/ark:/67531/metadc56587/
- XC-35 gust research project analysis of gust measurements
- No Description digital.library.unt.edu/ark:/67531/metadc61106/
- XC-35 gust research project characteristics of vertical drafts and associated vertical gust velocities within convective type clouds
- No Description digital.library.unt.edu/ark:/67531/metadc61108/