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  Partner: UNT Libraries Government Documents Department
 Collection: National Advisory Committee for Aeronautics Collection
Two-Dimensional Irrotational Transonic Flows of a Compressible Fluid
The methods of NACA TN No. 995 have been slightly modified and extended in include flows with circulation by considering the alteration of the singularities of the incompressible solution due to the presence of the hypergeometric functions in the analytic continuation of the solution. It was found that for finite Mach numbers the only case in which the nature of the singularity can remain unchanged is for a ratio of specific heats equal to -1. From a study of two particular flows it seems that the effect of geometry cannot be neglected, and the conventional "pressure-correction" formulas are not valid, even in the subsonic region if the body is thick, especially if there is a supersonic region in the flow. digital.library.unt.edu/ark:/67531/metadc172480/
Bending Tests of Metal Monocoque Fuselage Construction
Study of the bending stress in smooth skin, aluminum alloy, true monocoque fuselage sections of varying ratio of diameter to thickness. digital.library.unt.edu/ark:/67531/metadc172433/
Performance of B. M. W. 185-Horsepower Airplane Engine
No Description digital.library.unt.edu/ark:/67531/metadc172405/
Aerodynamic Investigation of a Cup Anemometer
Results of an investigation wherein the change of the normal force coefficient with Reynolds Number was obtained statically for a 15.5-centimeter hemispherical cup. digital.library.unt.edu/ark:/67531/metadc172432/
Tables and Charts of Flow Parameters Across Oblique Shocks
Shock-wave equations have been evaluated for a range of Mach number in front of the shock from 1.05 to 4.0. Mach number behind the shock, pressure ratio, derivation of flow, and angle of shock are presented on charts. Values are also included for density ratio and change in entropy. digital.library.unt.edu/ark:/67531/metadc172508/
A Comparison of Theory and Experiment for High-Speed Free-Molecule Flow
Comparison of free-molecule-flow theory with the results of wind-tunnel tests performed to determine the drag and temperature-rise characteristics of a transverse circular cylinder. digital.library.unt.edu/ark:/67531/metadc172515/
Two-Dimensional Subsonic Compressible Flows Past Arbitrary Bodies by the Variational Method
Instead of solving the nonlinear differential equation which governs the compressible flow, an approximate method of solution by means of the variational method is used. The general problem of steady irrotational flow past an arbitrary body is formulated. Two examples were carried out, namely, the flow past a circular cylinder and the flow past a thin curved surface. The variational method yields results of velocity and pressure distributions which compare excellently with those found by existing methods. These results indicate that the variational method will yield good approximate solution for flow past both thick and thin bodies at both high and low Mach numbers. digital.library.unt.edu/ark:/67531/metadc172521/
Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades
Heat-transfer investigation conducted on cooled as well heated impulse-type turbine blades in a static cascade to determine the effect of direction of heat flow on convective heat-transfer coefficients. digital.library.unt.edu/ark:/67531/metadc100824/
Charts for the Computation of Equilibrium Composition of Chemical Reactions in the Carbon-Hydrogen-Nitrogen System at Temperatures from 2000 to 5000 Degrees K
Charts are provided for the estimation and progressive adjustment of two independent variables on which the calculations are based. Additional charts are provided for the graphical calculation of the composition. digital.library.unt.edu/ark:/67531/metadc100821/
Tables for the Computation of Wave Drag of Arrow Wings of Arbitrary Airfoil Section
Tables and computing instructions for the rapid evaluation of the wave drag of delta wings and of arrow wings having a ration of the tangent of the trailing-edge sweep angle to the tangent of the leading-edge sweep angle in the range from -1.0 to 0.8. The tables cover a range of both subsonic and supersonic leading edges. digital.library.unt.edu/ark:/67531/metadc100822/
Summary of 65-Series Compressor-Blade Low-Speed Cascade Data by Use of the Carpet-Plotting Technique
Carpet plots included permit the selection of the blade camber and the design angle of attack required to fulfill a design vector diagram. Other carpet plots provide means for the prediction of off-design turning angles. digital.library.unt.edu/ark:/67531/metadc100823/
An investigation of aircraft heaters IX : measured and predicted performance of two exhaust gas-air heat exchangers and an apparatus for evaluating exhaust gas-air heat exchangers
No Description digital.library.unt.edu/ark:/67531/metadc279620/
Nieuport-Delage 590 Military airplane (French) : a two-place high-wing cantilever monoplane
No Description digital.library.unt.edu/ark:/67531/metadc279623/
The Bernard 82 military airplane (French) : a long-range monoplane
No Description digital.library.unt.edu/ark:/67531/metadc279677/
The S.P.C.A. 30 M.4 military airplane (French) : a multiplace low-wing airplane
No Description digital.library.unt.edu/ark:/67531/metadc279658/
The Lagrangian Multiplier Method of Finding Upper and Lower Limits to Critical Stresses of Clamped Plates
The theory of Lagrangian multipliers is applied to the problem of finding both upper and lower limits to the true compressive buckling stress of a clamped rectangular plate. The upper and lower limits thus bracket the truss, which cannot be exactly found by the differential-equation approach. The procedure for obtaining the upper limit, which is believed to be new, presents certain advantages over the classical Raleigh-Rite method of finding upper limits. The theory of the lower-limit procedure has been given by Trefftz but, in the present application, the method differs from that of Trefftz in a way that makes it inherently more quickly convergent. It is expected that in other buckling problems and in some vibration problems problems the Lagrangian multiplier method finding upper and lower limits may be advantageously applied to the calculation of buckling stresses and natural frequencies. digital.library.unt.edu/ark:/67531/metadc279603/
The S.P.C.A. 40 T commercial airplane (French) : an all-metal cantilever monoplane
No Description digital.library.unt.edu/ark:/67531/metadc279607/
The Breda 32 commercial airplane (Italian) : a three-engine all-metal low-wing monoplane
No Description digital.library.unt.edu/ark:/67531/metadc279669/
Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data
No Description digital.library.unt.edu/ark:/67531/metadc279644/
Morane-Saulnier 180 light airplane (French) : a single-seat training monoplane
Equipped with a 40 HP Salmson engine, it is a single seat parasol type construction. digital.library.unt.edu/ark:/67531/metadc279673/
A Concise Theoretical Method for Profile-Drag Calculation; Advance Report
In this report a method is presented for the calculation of the profile drag of airfoil sections. The method requlres only a knowledge of the theoretical velocity distribution and can be applied readily once this dlstribution is ascertained. Comparison of calculated and experimental drag characteristics for several airfoils shows a satisfactory agreement. Sample calculatlons are included. digital.library.unt.edu/ark:/67531/metadc279600/
Spin tests of two models of a low-wing monoplane to investigate scale effect in the model test range
No Description digital.library.unt.edu/ark:/67531/metadc279675/
Westland "Wessex" commercial airplane (British) : a high-wing semicantilever monoplane
No Description digital.library.unt.edu/ark:/67531/metadc279638/
Breguet 390 T commercial airplane (French) : a ten-seat all-steel sesquiplane
No Description digital.library.unt.edu/ark:/67531/metadc279625/
The S.A.B.C.A. "S.XI" commercial airplane (Belgian) : a high-wing semicantilever monoplane
No Description digital.library.unt.edu/ark:/67531/metadc279656/
Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system
No Description digital.library.unt.edu/ark:/67531/metadc279610/
Ditching tests with 1/10-size model of the Army A-20A airplane I : calm-water tests in NACA tank no.2
No Description digital.library.unt.edu/ark:/67531/metadc279645/
The Armstrong Whitworth A.W. XVI military Airplane (British) : a single-seat biplane
No Description digital.library.unt.edu/ark:/67531/metadc279647/
The "I.A.R." pursuit airplane (Roumanian) : a one-place cantilever low-wing monoplane
No Description digital.library.unt.edu/ark:/67531/metadc279651/
The use of geared spring tabs for elevator control
No Description digital.library.unt.edu/ark:/67531/metadc279612/
The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow
No Description digital.library.unt.edu/ark:/67531/metadc279634/
Lift theory of supporting surfaces : second article
No Description digital.library.unt.edu/ark:/67531/metadc279655/
Nieuport-Delage 640 (French) : commercial high-wing monoplane
The Nieuport Delage 640 is a single engine commercial high-wing monoplane of all wood construction, including the fuselage and tail. It's landing gear is hinged in two parts. digital.library.unt.edu/ark:/67531/metadc279648/
Liore-Olivier airplane : type 12 night-bomber or type 20 commercial
No Description digital.library.unt.edu/ark:/67531/metadc279601/
An investigation of a thermal ice-prevention system for a C-46 cargo airplane IV : results of flight tests in dry-air and natural-icing conditions
No Description digital.library.unt.edu/ark:/67531/metadc279606/
Flight measurements of the effect of various amounts of aileron droop on the low-speed lateral-control characteristics of an observation airplane
No Description digital.library.unt.edu/ark:/67531/metadc279604/
The D.H. 85 "Leopard Moth" airplane (British) : a three-seat cabin high-wing monoplane
No Description digital.library.unt.edu/ark:/67531/metadc279636/
Performance of an exhaust-gas "blowdown" turbine on a nine-cylinder radial engine
No Description digital.library.unt.edu/ark:/67531/metadc279622/
The A.N.E.C. IV "Missel Thrush" light airplane
A product of the Air Navigation Engineering Co., the Missel Thrush is a light airplane suitable for private ownership. It is a two seat tractor fuselage biplane with single I interplane struts designed by J. Bewsher. digital.library.unt.edu/ark:/67531/metadc279637/
Determination of general relations for the behavior of turbulent boundary layers
No Description digital.library.unt.edu/ark:/67531/metadc279609/
The development and application of high-critical-speed nose inlets
No Description digital.library.unt.edu/ark:/67531/metadc279653/
The Stieger ST. 4 light airplane (British) : a twin-engine four-seat low-wing cabin monoplane
No Description digital.library.unt.edu/ark:/67531/metadc279679/
D.H. 86 "Express Air Liner" (British) : a four-engine biplane
No Description digital.library.unt.edu/ark:/67531/metadc279667/
An experimental study of five annular air inlet configurations at subsonic and transonic speeds
No Description digital.library.unt.edu/ark:/67531/metadc279680/
The De Havilland 61 "Canberra" (British) : a 6-8 passenger airplane
Made for an Australian buyer, the Canberra is capable of carrying a payload of 1900 lbs. with a top speed of 126 M.P.H. At 105-110 M.P.H. it has a range of about 475 miles. It has a single Jupiter VI engine. digital.library.unt.edu/ark:/67531/metadc279646/
Les Mureaux "130.A2" observation airplane (French) : a high-wing two-seat monoplane
No Description digital.library.unt.edu/ark:/67531/metadc279661/
The Francois Villiers marine pursuit airplane
A traditional biplane design allows this craft to function with the speed and maneuverability necessary to perform as a pursuit aircraft while also being able to land on water. It featured retractable landing gear for water landings. It was powered with a 450 HP. Lorraine-Dietrich engine. digital.library.unt.edu/ark:/67531/metadc279671/
Thermodynamic design of double-panel, air-heated windshields for ice prevention
No Description digital.library.unt.edu/ark:/67531/metadc279628/
Wind-tunnel investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability characteristics of a complete-model swept-wing configuration at high subsonic speeds
No Description digital.library.unt.edu/ark:/67531/metadc279650/
An experimental investigation of rectangular exhaust-gas ejectors applicable for engine cooling
No Description digital.library.unt.edu/ark:/67531/metadc279654/
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