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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
The development and application of high-critical-speed nose inlets
No Description digital.library.unt.edu/ark:/67531/metadc279653/
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 I : unification and extension of present-day results
No Description digital.library.unt.edu/ark:/67531/metadc279666/
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/
NACA Mach number indicator for use in high-speed tunnels
No Description digital.library.unt.edu/ark:/67531/metadc279639/
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/
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/
Profile-drag coefficients of conventional and low-drag airfoils as obtained in flight
No Description digital.library.unt.edu/ark:/67531/metadc279640/
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/
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/
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/
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/
The Effect of Inlet Pressure and Temperature on the Efficiency of a Single Stage Impulse Turbine Having an 11.0-Inch Pitch-Line Diameter Wheel
Efficiency tests have been conducted on a single-stage impulse engine having an 11-inch pitch-line diameter wheel with inserted buckets and a fabricated nozzle diaphragm. The tests were made to determine the effect of inlet pressure, Inlet temperature, speed, and pressure ratio on the turbine efficiency. An analysis is presented that relates the effect of inlet pressure and temperature to the Reynolds number of the flow. The agreement between the analysis and the experimental data indicates that the changes in turbine efficiency with Inlet pressure and temperature may be principally a Reynolds number effect. digital.library.unt.edu/ark:/67531/metadc61859/
A correlation of the effects of compression ratio and inlet-air temperature on the knock limits of aviation fuels in a CFR engine I
No Description digital.library.unt.edu/ark:/67531/metadc62295/
Correlation of Wright Aeronautical Corporation cooling data on the R-3350-14 intermediate engine and comparison with data from the Langley 16-foot high-speed tunnel
No Description digital.library.unt.edu/ark:/67531/metadc62698/
Wind-tunnel investigation of a high-critical-speed fuselage scoop including the effects of boundary layer
No Description digital.library.unt.edu/ark:/67531/metadc61665/
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/
Variation of peak pitching-moment coefficients for six airfoils as affected by compressibility
No Description digital.library.unt.edu/ark:/67531/metadc61478/
Wind-tunnel data on the aerodynamic characteristics of airplane control surfaces
No Description digital.library.unt.edu/ark:/67531/metadc61566/
Wind-Tunnel Investigation of Shielded Horn Balances and Tabs on a 0.7-Scale Model of XF6F Vertical Tail Surface
Results of subject tests indicate the difficulty of obtaining closely balanced rudder surfaces for most tail assemblies with shielded horns and maintaining a near zero rate-of-change of hinge-moment coefficient without an additional balancing device. A comparison is made between shielded and unshielded horn test results. Pressure distribution and tuft tests of flow over different shaped horns showed higher critical speed for medium-taper nosed horn. The trim tab nose shape had little effect on tab test results. digital.library.unt.edu/ark:/67531/metadc61579/
An analysis of jet-propulsion systems making direct use of the working substance of a thermodynamic cycle
No Description digital.library.unt.edu/ark:/67531/metadc62462/
Comparison of calculated and experimental propeller characteristics for four-, six-, and eight-blade single-rotating propellers
No Description digital.library.unt.edu/ark:/67531/metadc62159/
Comparison of fixed-stabilizer, adjustable- stabilizer and all-movable horizontal tails
No Description digital.library.unt.edu/ark:/67531/metadc61649/
Completed Tabulation in the United States of Tests of 24 Airfoils at High Mach Numbers (Derived from Interrupted Work at Guidonia, Italy in the 1.31- by 1.74-Foot High-Speed Tunnel)
Two-dimensional data were obtained in Mach range of from 0.40 to 0.94 and Reynolds Number range of (3.4 - 4.2) X 10 Degrees. Results indicate that thickness ratio is dominating shape parameter at high Mach numbers and that aerodynamic advantages are attainable by using thinnest possible sections. Effects of jet boundaries, Reynolds Number, and Data presented are free from jet-boundary and humidity effects. digital.library.unt.edu/ark:/67531/metadc61347/
Comparison of yaw characteristics of a single-engine airplane model with single-rotating and dual-rotating propellers
No Description digital.library.unt.edu/ark:/67531/metadc62165/
A comparison at high speed of the aerodynamic merits of models of medium bombers having thickened wing roots and having wings with nacelles
No Description digital.library.unt.edu/ark:/67531/metadc61167/
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/
Considerations of wake-excited vibratory stress in a pusher propeller
No Description digital.library.unt.edu/ark:/67531/metadc62151/
An interim report on the stability and control of tailless airplanes
No Description digital.library.unt.edu/ark:/67531/metadc60946/
Simple curves for determining the effects of compressibility on pressure drop through radiators
No Description digital.library.unt.edu/ark:/67531/metadc62021/
A simple method for estimating terminal velocity including effect of compressibility on drag
No Description digital.library.unt.edu/ark:/67531/metadc61252/
Scale-effect tests in a turbulent tunnel of the NACA 65(sub 3)-418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap
No Description digital.library.unt.edu/ark:/67531/metadc61404/
Scale and Turbulence Effects on the Lift and Drag Characteristics of the NACA 65(Sub 3)-418, A=1.0 Airfoil Section
Wind-tunnel tests, investigating low drag wing performance in small-scale tests, showed a large increase in minimum drag coefficient, and a decrease of maximum lift coefficient occurred with decreasing Reynolds Number above certain designated values. The lift-curve slope varied up to 6% between high and low turbulence levels. Low Reynolds Number test data are unreliable for low drag airfoils either to estimate full-scale characteristics or to determine merits of airfoils for higher Reynolds numbers. digital.library.unt.edu/ark:/67531/metadc61402/
Effect of a trailing-edge extension on the characteristics of a propeller section
No Description digital.library.unt.edu/ark:/67531/metadc61477/
The theory of propellers III : the slipstream contraction with numerical values for two-blade and four-blade propellers
No Description digital.library.unt.edu/ark:/67531/metadc62140/
The theory of propellers II : method for calculating the axial interference velocity
No Description digital.library.unt.edu/ark:/67531/metadc62138/
The theory of propellers IV : thrust, energy, and efficiency formulas for single- and dual-rotating propellers with ideal circulation distribution
No Description digital.library.unt.edu/ark:/67531/metadc62141/
The theory of propellers I : determination of the circulation function and the mass coefficient for dual-rotating propellers
No Description digital.library.unt.edu/ark:/67531/metadc62137/
Supersonic-tunnel tests of projectiles in Germany and Italy
No Description digital.library.unt.edu/ark:/67531/metadc62434/
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/
Experimental constriction effects in high-speed wind tunnels
No Description digital.library.unt.edu/ark:/67531/metadc62421/
Flight Investigation at High Speeds of Profile Drag of Wing of a P-47D Airplane Having Production Surfaces Covered with Camouflage Paint
Wing section outboard of flap was tested by wake surveys in Mach range of 0.25 - 0.78 and lift coefficient range 0.06 - 0.69. Results indicated that minimum profile-drag coefficient of 0.0097 was attained for lift coefficients from 0.16 to 0.25 at Mach less than 0.67. Below Mach number at which compressibility shock occurred, variations in Mach of 0.2 had negligible effect on profile drag coefficient. Shock was not evident until critical Mach was exceeded by 0.025. digital.library.unt.edu/ark:/67531/metadc61323/
Summary of data relating to the effects of wing machine-gun and cannon installations on the aerodynamic characteristics of airplanes
No Description digital.library.unt.edu/ark:/67531/metadc62430/
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/
Flight tests of an all-movable vertical tail on the Fairchild XR2K-1 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61509/
Flight investigation of boundary-layer control by suction slots on an NACA 35-215 low-drag airfoil at high Reynolds numbers
No Description digital.library.unt.edu/ark:/67531/metadc61322/
Flight investigation of boundary-layer transition and profile drag of an experimental low-drag wing installed on a fighter-type airplane
No Description digital.library.unt.edu/ark:/67531/metadc61735/
Flight tests of dive-recovery flaps on an XP-51 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61739/
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