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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Restricted Report
 Collection: National Advisory Committee for Aeronautics Collection
The effect of compressibility on two-dimensional tunnel-wall interference for a symmetrical airfoil
Summary: The effective change in the velocity of flow past a wing section, caused by the presence of wind-tunnel walls, is known for potential flow. This theory is extended by investigation of the two-dimensional compressible flow past a thin Rankine Oval. It is shown that for a symmetrical section at zero angle of attack the velocity increment due to the tunnel walls in the incompressible case must be multiplied by the factor 1/1-M^2 to take account of compressibility effects. The Mach number, M, corresponds to conditions in the wind-tunnel test section with the model removed (p. 1.). digital.library.unt.edu/ark:/67531/metadc279468/
Principles of moment distribution applied to stability of structures composed of bars or plates
Principles of the cross method of moment distribution, which have previously been applied to the stability of structures composed of bars under axial load, are applied to the stability of structures composed of long plates under longitudinal load. digital.library.unt.edu/ark:/67531/metadc66198/
Effect of wing leading-edge slots on the spin and recovery characteristics of airplanes
No Description digital.library.unt.edu/ark:/67531/metadc61237/
Free-flight-tunnel investigation of the effect of the fuselage length and the aspect ratio and size of the vertical tail on lateral stability and control
No Description digital.library.unt.edu/ark:/67531/metadc61026/
An investigation of aircraft heaters XI : measured and predicted performance of a slotted-fin exhaust gas and air heat exchanger
No Description digital.library.unt.edu/ark:/67531/metadc61690/
Formulas for propellers in yaw and charts of the side-force derivative
No Description digital.library.unt.edu/ark:/67531/metadc62130/
Free-spinning-tunnel tests of a model of a canard airplane
No Description digital.library.unt.edu/ark:/67531/metadc62556/
Full-scale tunnel investigation of the pressure distribution over the tail of the P-47B airplane
No Description digital.library.unt.edu/ark:/67531/metadc61585/
An instrument for the determination of rain densities in flight
No Description digital.library.unt.edu/ark:/67531/metadc62396/
Jet-boundary corrections for reflection-plane models in rectangular wind tunnels
No Description digital.library.unt.edu/ark:/67531/metadc61171/
Lead susceptibility of paraffins, cycloparaffins, and olefins
No Description digital.library.unt.edu/ark:/67531/metadc62337/
Method of calculating performance of dual-rotating propellers from airfoil characteristics
No Description digital.library.unt.edu/ark:/67531/metadc62155/
Tests of exhaust propulsion nozzles
No Description digital.library.unt.edu/ark:/67531/metadc62459/
The use of a retractable planing flap instead of a fixed step on a seaplane
No Description digital.library.unt.edu/ark:/67531/metadc62561/
The effect of dead rise upon the high-angle porpoising characteristics of two planing surfaces in tandem
No Description digital.library.unt.edu/ark:/67531/metadc60898/
Effect of wing loading and altitude on lateral stability and control characteristics of an airplane as determined by tests of a model in the free-flight tunnel
No Description digital.library.unt.edu/ark:/67531/metadc61008/
Experimental determination of the yawing moment due to yawing contributed by the wing, fuselage, and vertical tail of a midwing airplane model
No Description digital.library.unt.edu/ark:/67531/metadc60937/
Flight tests of various tail modifications on the Brewster XSBA-1 airplane I : measurements of flying qualities with original tail surfaces
No Description digital.library.unt.edu/ark:/67531/metadc61511/
Mechanical tests of macerated phenolic molding material
No Description digital.library.unt.edu/ark:/67531/metadc62221/
Preliminary tank tests with planing-tail seaplane hulls
No Description digital.library.unt.edu/ark:/67531/metadc61784/
Recommended test procedure for aircraft engine turbosupercharger power plants
No Description digital.library.unt.edu/ark:/67531/metadc62077/
Some systematic model experiments on the porpoising characteristics of flying-boat hulls
No Description digital.library.unt.edu/ark:/67531/metadc62672/
Wind-tunnel investigation of control-surface characteristics XIV : NACA 0009 airfoil with a 20-percent-chord double plain flap
No Description digital.library.unt.edu/ark:/67531/metadc61541/
Wind-tunnel investigation of effect of yaw on lateral-stability characteristics V : symmetrically tapered wing with a circular fuselage having a horizontal and a vertical tail
No Description digital.library.unt.edu/ark:/67531/metadc61017/
Wind-tunnel vibration tests of a four-blade single rotating pusher propeller
No Description digital.library.unt.edu/ark:/67531/metadc62132/
Design, selection, and installation of aircraft heat exchangers
No Description digital.library.unt.edu/ark:/67531/metadc61934/
Effect of turbulence on air-flow measurements behind orifice plates
No Description digital.library.unt.edu/ark:/67531/metadc62563/
Knocking tendency of an air-cooled aircraft-engine cylinder with one and with two spark plugs
No Description digital.library.unt.edu/ark:/67531/metadc62045/
Measurements of friction coefficients in a pipe for subsonic and supersonic flow of air
No Description digital.library.unt.edu/ark:/67531/metadc62675/
On a function-theory method for obtaining potential-flow patterns of a compressible fluid
No Description digital.library.unt.edu/ark:/67531/metadc62604/
Porpoising: a comparison of theory with experiment
No Description digital.library.unt.edu/ark:/67531/metadc60896/
Relation of preignition and knock to allowable engine temperatures
No Description digital.library.unt.edu/ark:/67531/metadc61862/
Some yawing tests of a 1/30-scale model of the hull of the XPB2M-1 flying boat
No Description digital.library.unt.edu/ark:/67531/metadc62669/
Theory of self-excited mechanical oscillations of hinged rotor blades
No Description digital.library.unt.edu/ark:/67531/metadc62585/
Wind-tunnel tests of four full-scale seaplane floats
No Description digital.library.unt.edu/ark:/67531/metadc61713/
Working charts for the computation of propeller thrust throughout the take-off range
No Description digital.library.unt.edu/ark:/67531/metadc62157/
Determination of the damping moment in yawing for tapered wings with partial-span flaps
No Description digital.library.unt.edu/ark:/67531/metadc61258/
Development of thermal ice-prevention equipment for the B-17F airplane
No Description digital.library.unt.edu/ark:/67531/metadc61807/
The Effect of Mass Distribution on the Lateral Stability and Control Characteristics of an Airplane as Determined by Tests of a Model in the Free-Flight Tunnel
The effects of mass distribution on lateral stability and control characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rolling and yawing movements of inertia were increased from normal values to values up to five times normal. For each moment-of-inertia condition, combinations of dihedral and vertical-tail area representing a variety of airplane configurations were tested. The results of the flight tests of the model were correlated with calculated stability and control characteristics and, in general, good agreement was obtained. The tests showed the following effects of increased rolling and yawing moments of inertia: no appreciable change in spiral stability; reductions in oscillatory stability that were serious at high values of dihedral; a reduction in the sensitivity of the model to gust disturbances; and a reduction in rolling acceleration provided by the ailerons, which caused a marked increase in time to reach a given angle of bank. The general flight behavior of the model became worse with increasing moments of inertia but, with combinations of small effective dihedral and large vertical-tail area, satisfactory flight characteristics were obtained at all moment-of-inertia conditions. digital.library.unt.edu/ark:/67531/metadc60939/
De-icing of an aircraft-engine induction system
No Description digital.library.unt.edu/ark:/67531/metadc61806/
Improved baffle designs for air-cooled engine cylinders
No Description digital.library.unt.edu/ark:/67531/metadc61903/
An investigation of aircraft heaters XII : performance of a formed-plate crossflow exhaust gas and air heat exchanger
No Description digital.library.unt.edu/ark:/67531/metadc62695/
An investigation of aircraft heaters XIII : performance of corrugated and noncorrugated fluted type exhaust gas-air heat exchangers
No Description digital.library.unt.edu/ark:/67531/metadc61694/
A method of estimating the knock rating of hydrocarbon fuel blends
No Description digital.library.unt.edu/ark:/67531/metadc62267/
Wind-tunnel investigation of a full-span retractable flap in combination with full-span plain and internally balanced ailerons on a tapered wing
No Description digital.library.unt.edu/ark:/67531/metadc61420/
Aerodynamic and hydrodynamic tests of a family of models of flying-boat hulls derived from a streamline body : NACA model 84 series
No Description digital.library.unt.edu/ark:/67531/metadc61711/
Protection of nonmetallic aircraft from lighting I : general analysis
No Description digital.library.unt.edu/ark:/67531/metadc62470/
Representative operating charts of propellers tested in the NACA 20-foot propeller-research tunnel
Report presents the results of tests of full-scale propellers made in the 20-foot propeller-research tunnel (PRT) at the Langley Memorial Aeronautical Laboratory. The power coefficients of all dual-rotating propellers in the report represent the sum of the power coefficients of the front and rear propellers and are for the test conditions in which blade angles of the front and rear propellers were set to absorb approximately equal power at peak efficiency only. digital.library.unt.edu/ark:/67531/metadc65700/
Some analyses of systematic experiments on the resistance and porpoising characteristics of flying-boat hulls
No Description digital.library.unt.edu/ark:/67531/metadc61773/
Theory of mechanical oscillations of rotors with two hinged blades
No Description digital.library.unt.edu/ark:/67531/metadc62589/
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