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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
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/
Performance of an exhaust-gas "blowdown" turbine on a nine-cylinder radial engine
No Description digital.library.unt.edu/ark:/67531/metadc279622/
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/
NACA Mach number indicator for use in high-speed tunnels
No Description digital.library.unt.edu/ark:/67531/metadc279639/
On the flow of a compressible fluid by the hodography method I : unification and extension of present-day results
No Description digital.library.unt.edu/ark:/67531/metadc279666/
Profile-drag coefficients of conventional and low-drag airfoils as obtained in flight
No Description digital.library.unt.edu/ark:/67531/metadc279640/
Experiments on drag of revolving disks, cylinders and streamline rods at high speeds
No Description digital.library.unt.edu/ark:/67531/metadc279467/
On the flow of a compressible fluid by the hodography method II : fundamental set of particular flow solutions of the Chaplygin differential equation
No Description digital.library.unt.edu/ark:/67531/metadc279417/
The propeller and cooling-air-flow characteristics of a twin-engine airplane model equipped with NACA D(sub S)-type cowlings and with propellers of NACA 16-series airfoil sections
No Description digital.library.unt.edu/ark:/67531/metadc279496/
Notes on the effect of surface distortions on the drag and critical Mach number of airfoils
No Description digital.library.unt.edu/ark:/67531/metadc279442/
NACA Investigation of a Jet-Propulsion System Applicable to Flight
Following a brief history of the NACA investigation of jet-propulsion, a discussion is given of the general investigation and analyses leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight-performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made. It was found that the main fire could be restricted to an intense, small, and short annular blue flame burning steadily and under control in the intended combustion space. With these readily obtainable combustion conditions, the combustion chamber the nozzle walls and the surrounding structure could be maintained at normal temperatures. The system investigated was found to be capable of burning one-half the intake air up the fuel rates of 3 pounds per second. Calculations were shown to agree well with experiment. It was concluded that the basic features of the jet-propulsion system investigation in the ground-test mock-up were sufficiently developed to be considered applicable to flight installation. Calculations indicated that an airplane utilizing this jet-propulsion system would have unusual capabilities in the high-speed range above the speeds of conventional aircraft and would, in addition, have moderately long cruising ranges if only the engine were used. digital.library.unt.edu/ark:/67531/metadc279418/
Investigation of flow in an axially symmetrical heated jet of air
The work done under this contract falls essentially into two parts: the first part was the design and construction of the equipment and the running of preliminary tests on the 3-inch jet, carried out by Mr. Carl Thiele in 1940; the second part consisting in the measurement in the 1-inch jet flow in an axially symmetrical heated jet of air. (author). digital.library.unt.edu/ark:/67531/metadc65451/
Physical data on certain alloys for high temperature applications
No Description digital.library.unt.edu/ark:/67531/metadc62224/
High temperature characteristics of 17 alloys at 1200 and 1350 F
No Description digital.library.unt.edu/ark:/67531/metadc62226/
Data for Design of Entrance Vanes from Two-Dimensional Tests of Airfoils in Cascade
As a part of a program of the NACA directed toward increasing the efficiency of compressors and turbines, data were obtained for application to the design of entrance vanes for axfax-flow compressors or turbines. A series of blower-blade sections with relatively high critical speeds have been developed for turning air efficiently from 0 deg to 80 deg starting with an axial direction. Tests were made of five NACA 65-series blower blades (modified NACA 65(216)-010 airfoils) and of four experimentally designed blower blades in a stationary cascade at low Mach numbers. The turning effectiveness and the pressure distributions of these blade sections at various angles of attack were evaluated over a range of solidities near 1. Entrance-vane design charts are presented that give a blade section and angle of attack for any desired turning angle. The blades thus obtained operate with peak-free pressure distributions. Approximate critical Mach numbers were calculated from the pressure distributions. digital.library.unt.edu/ark:/67531/metadc63062/
An analytical investigation of the effects of elevator-fabric distortion on the longitudinal stability and control of an airplane
No Description digital.library.unt.edu/ark:/67531/metadc60987/
Effect of tilt of the propeller axis on the longitudinal-stability characteristics of single-engine airplanes
No Description digital.library.unt.edu/ark:/67531/metadc60951/
The Supersonic Axial-Flow Compressor
An investigation has been made to explore the possibilities of axial-flow compressors operating with supersonic velocities into the blade rows. Preliminary calculations showed that very high pressure ratios across a stage, together with somewhat increased mass flows, were apparently possible with compressors which decelerated air through the speed of sound in their blading. The first phase of the investigation was the development of efficient supersonic diffusers to decelerate air through the speed of sound. The present report is largely a general discussion of some of the essential aerodynamics of single-stage supersonic axial-flow compressors. As an approach to the study of supersonic compressors, three possible velocity diagrams are discussed briefly. Because of the encouraging results of this study, an experimental single-stage supersonic compressor has been constructed and tested in Freon-12. In this compressor, air decelerates through the speed of sound in the rotor blading and enters the stators at subsonic speeds. A pressure ratio of about 1.8 at an efficiency of about 80 percent has been obtained. digital.library.unt.edu/ark:/67531/metadc60311/
Determination of the Stability and Control Characteristics of a Tailless All-Wing Airplane Model with Sweepback in the Langley Free-Flight Tunnel
Force and flight tests were performance on an all-wing model with windmilling propellers. Tests were conducted with deflected and retracted flaps, with and without auxiliary vertical tail surfaces, and with different centers of gravity and trim coefficients. Results indicate serious reduction of stick-fixed longitudinal stability because of wing-tip stalling at high lift coefficient. Directional stability without vertical tail is undesirably low. Low effective dihedral should be maintained. Elevator and rudder control system is satisfactory. digital.library.unt.edu/ark:/67531/metadc60992/
An additional investigation of the high-speed lateral-control characteristics of spoilers
No Description digital.library.unt.edu/ark:/67531/metadc60955/
Correlation of the drag characteristics of a P-51B airplane obtained from high-speed wind-tunnel and flight tests
No Description digital.library.unt.edu/ark:/67531/metadc60838/
Extension of Useful Operating Range of Axial-Flow Compressors by Use of Adjustable Stator Blades
A theory has been developed for resetting the blade angles of an axial-flow compressor in order to improve the performance at speeds and flows other than the design and thus extend the useful operating range of the compressor. The theory is readily applicable to the resetting of both rotor and stator blades or to the resetting of only the stator blades and is based on adjustment of the blade angles to obtain lift coefficients at which the blades will operate efficiently. Calculations were made for resetting the stator blades of the NACA eight-stage axial-flow compressor for 75 percent of design speed and a series of load coefficients ranging from 0.28 to 0.70 with rotor blades left at the design setting. The NACA compressor was investigated with three different blade settings: (1) the design blade setting, (2) the stator blades reset for 75 percent of design speed and a load coefficient of 0.48, and (3) the stator blades reset for 75 percent of design speed and a load coefficient of 0.65. digital.library.unt.edu/ark:/67531/metadc60225/
An interim report on the stability and control of tailless airplanes
No Description digital.library.unt.edu/ark:/67531/metadc60946/
Effects of mean-line loading on the aerodynamic characteristics of some low-drag airfoils
No Description digital.library.unt.edu/ark:/67531/metadc61373/
Wind-tunnel investigation of control-surface characteristics XIII : various flap overhangs used with a 30-percent-chord flap in an NACA 66-009 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61537/
The NACA impact basin and water landing tests of a float model at various velocities and weights
No Description digital.library.unt.edu/ark:/67531/metadc61795/
Correlation of flight data on limit pressure coefficients and their relation to high-speed burbling and critical tail loads
No Description digital.library.unt.edu/ark:/67531/metadc61282/
Wind-tunnel investigation of control-surface characteristics XV : various contour modifications of a 0.30-airfoil-chord plain flap on an NACA 66(215)-014 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61545/
Occurrence of iron oxides on cast-iron engine surfaces after operation
No Description digital.library.unt.edu/ark:/67531/metadc61910/
Cooling Characteristics of a Pratt and Whitney R-2800 Engine Installed in an NACA Short-Nose High-Inlet-Velocity Cowling
An investigation was made of the cooling characteristics of a P and W R-2800 engine with NACA short-nose high inlet-velocity cowling. The internal aerodynamics of the cowling were studied for ranges of propeller-advance ratio and inlet-velocity ratio obtained by deflection of cowling flaps. Tests included variations of engine power, fuel/air ratio and cooling-air pressure drop. Engine cooling data are presented in the form of cooling correlation curves, and an example for calculation of cooling requirements in flight is included. digital.library.unt.edu/ark:/67531/metadc61985/
Flight tests of an all-movable vertical tail on the Fairchild XR2K-1 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61509/
A flight investigation of NACA aileron modifications for the improvement of the lateral control characteristics of a high-speed fighter airplane
No Description digital.library.unt.edu/ark:/67531/metadc61647/
Comparison of fixed-stabilizer, adjustable- stabilizer and all-movable horizontal tails
No Description digital.library.unt.edu/ark:/67531/metadc61649/
A summary of drag results from recent Langley full scale tunnel tests of Army and Navy airplanes
No Description digital.library.unt.edu/ark:/67531/metadc61174/
Summary of measurements in Langley full-scale tunnel of maximum lift coefficients and stalling characteristics of airplanes
No Description digital.library.unt.edu/ark:/67531/metadc61175/
A simple method for estimating terminal velocity including effect of compressibility on drag
No Description digital.library.unt.edu/ark:/67531/metadc61252/
Experimental study of the coating found on scuffed cast-iron piston rings during operation in nitrided-steel cylinders
No Description digital.library.unt.edu/ark:/67531/metadc61991/
Experimental study of the coating formed on nitrided-steel piston rings during operation in nitrided-steel cylinders
No Description digital.library.unt.edu/ark:/67531/metadc61990/
An electron-diffraction examination of cast-iron piston rings from single-cylinder aircraft engine tests
No Description digital.library.unt.edu/ark:/67531/metadc61999/
High-speed investigation of low-drag wing inlets
No Description digital.library.unt.edu/ark:/67531/metadc61335/
Effect of Compressibility on the Pressure and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20-Chord Flap
An investigation has been conducted in the Langley rectangular high-speed tunnel to determine the effect of compressibility on the pressure distribution for a modified NACA 65,3-019 airfoil having a 0.20-chord flap. The investigation was made for an angle-of-attack range extending from -2 to 12 deg at .20 flap deflections from 0 to -12 deg. Test data were obtained for Mach numbers from 0.28 to approximately 0.74. The results show that the effectiveness of the trailing-edge-type control surface rapidly decreased and approached zero as the Mach number increased above the critical value. digital.library.unt.edu/ark:/67531/metadc61397/
Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap
Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil section to determine drag, lift, and pitching-moment characteristics for a range of flap deflections. Results indicate that combination of a low-drag airfoil and a double-slotted flap, of which the two parts moved as a single unit, gave higher maximum lift coefficients than have been obtained with plain, split, or slotted flaps on low-drag airfoils. Pitching moments were comparable to those obtained with other high-lift devices on conventional airfoils for similar lift coefficients. digital.library.unt.edu/ark:/67531/metadc61398/
Two-dimensional wind-tunnel investigation of 0.20-airfoil-chord plain ailerons of different contour on an NACA 65(sub 1)-210 airfoil section
No Description digital.library.unt.edu/ark:/67531/metadc61394/
Effects of specific types of surface roughness on boundary-layer transition
No Description digital.library.unt.edu/ark:/67531/metadc61337/
The effects of roughness at high Reynolds numbers on the lift and drag characteristics of three thick airfoils
No Description digital.library.unt.edu/ark:/67531/metadc61334/
Wind-tunnel investigation of an NACA 66-series 16-percent-thick low-drag tapered wing with Fowler and split flaps
No Description digital.library.unt.edu/ark:/67531/metadc61410/
Wind tunnel tests of ailerons at various speeds IV : ailerons of 0.20 airfoil chord and true contour with 0.35 aileron-chord extreme blunt-nose balance on the NACA 23012 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61629/
Wind-tunnel tests of ailerons at various speeds III : ailerons of 0.20 airfoil chord and true contour with 0.35-aileron-chord Frise balance on the NACA 23012 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61626/
A method for the rapid estimation of turbulent boundary-layer thickness for calculating profile drag
No Description digital.library.unt.edu/ark:/67531/metadc61265/
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