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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
Addition of heat to a compressible fluid in motion
No Description digital.library.unt.edu/ark:/67531/metadc62512/
An additional investigation of the high-speed lateral-control characteristics of spoilers
No Description digital.library.unt.edu/ark:/67531/metadc60955/
Analysis of available data on control surfaces having plain-overhang and Frise balances
No Description digital.library.unt.edu/ark:/67531/metadc61487/
Analysis of available data on the effectiveness of ailerons without exposed overhang balance
No Description digital.library.unt.edu/ark:/67531/metadc61635/
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/
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/
An analytical investigation of thermal-electric means of preventing ice formations on a propeller blade
No Description digital.library.unt.edu/ark:/67531/metadc62488/
Approximate formulas for the computation of turbulent boundary-layer momentum thicknesses in compressible flows
No Description digital.library.unt.edu/ark:/67531/metadc62569/
Bibliography and review of information relating to the hydrodynamics of seaplanes
No Description digital.library.unt.edu/ark:/67531/metadc62558/
Blade design data for axial-flow fans and compressors
No Description digital.library.unt.edu/ark:/67531/metadc62634/
A Brief Study of the Speed Reduction of Overtaking Airplanes by Means of Air Brakes, Special Report
As an aid to airplane designers interested in providing pursuit airplanes with decelerating devices intended to increase the firing time when overtaking another airplane, formulas are given relating the pertinent distances and speeds in horizontal flight to the drag increase required. Charts are given for a representative parasite-drag coefficient from which the drag increase, the time gained, and the closing distance may be found. The charts are made up for three values of the ratio of the final speed of the pursuing airplane to the speed of the pursued airplane and for several values of the ratio of the speed of the pursued airplane to the initial speed of the pursuing airplane. Charts are also given indicating the drag increases obtainable with double split flaps and with conventional propellers. The use of the charts is illustrated by an example in which it is indicated that either double split flaps or, under certain ideal conditions, reversible propellers should provide the speed reductions required. digital.library.unt.edu/ark:/67531/metadc65165/
Calculated and measured turning performance of a Navy F2A-3 airplane as affected by the use of flaps
No Description digital.library.unt.edu/ark:/67531/metadc61133/
Cascade investigation of buckets for a modern aircraft turbosupercharger
No Description digital.library.unt.edu/ark:/67531/metadc62080/
Charts for determining propeller efficiency
No Description digital.library.unt.edu/ark:/67531/metadc62143/
Charts for estimation of the characteristics of a helicopter rotor in forward flight I : profile drag-lift ratio for untwisted rectangular blades
No Description digital.library.unt.edu/ark:/67531/metadc61833/
Charts for helicopter-performance estimation
No Description digital.library.unt.edu/ark:/67531/metadc61830/
Charts for the determination of wing torsional stiffness required for specified rolling characteristics or aileron reversal speed
No Description digital.library.unt.edu/ark:/67531/metadc61277/
Climb and high-speed tests of a Curtiss number 714-1C2-12 four-blade propeller on the Republic P-47C airplane
No Description digital.library.unt.edu/ark:/67531/metadc62125/
Collection of balanced-aileron test data
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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/
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/
Comparison of Pitching Moments Produced by Plain Flaps and by Spoilers and Some Aerodynamic Characteristics of an NACA 23012 Airfoil with Various Types of Aileron
Sectional characteristics of airfoil having retractable slotted flap with plain, slot-lip, or retractable ailerons are presented for a large range of aileron deflections. The analysis indicated that pitching moments produced by spoilers were less positive than those produced by plain flaps of equal effectiveness, also that pitching moments created by the spoiler increased less with the Mach number than similar moments produced by plain flaps. Positive values of pitching moment decreased as devices were located nearer airfoil leading edge. digital.library.unt.edu/ark:/67531/metadc61345/
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/
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/
Compressibility Effects in Aeronautical Engineering
Compressible-flow research, while a relatively new field in aeronautics, is very old, dating back almost to the development of the first firearm. Over the last hundred years, researches have been conducted in the ballistics field, but these results have been of practically no use in aeronautical engineering because the phenomena that have been studied have been the more or less steady supersonic condition of flow. Some work that has been done in connection with steam turbines, particularly nozzle studies, has been of value, In general, however, understanding of compressible-flow phenomena has been very incomplete and permitted no real basis for the solution of aeronautical engineering problems in which.the flow is likely to be unsteady because regions of both subsonic and supersonic speeds may occur. In the early phases of the development of the airplane, speeds were so low that the effects of compressibility could be justifiably ignored. During the last war and immediately after, however, propellers exhibited losses in efficiency as the tip speeds approached the speed of sound, and the first experiments of an aeronautical nature were therefore conducted with propellers. Results of these experiments indicated serious losses of efficiency, but aeronautical engineers were not seriously concerned at the time became it was generally possible. to design propellers with quite low tip. speeds. With the development of new engines having increased power and rotational speeds, however, the problems became of increasing importance. digital.library.unt.edu/ark:/67531/metadc64993/
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/
Considerations of wake-excited vibratory stress in a pusher propeller
No Description digital.library.unt.edu/ark:/67531/metadc62151/
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/
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/
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/
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/
Critical Mach Numbers of Thin Airfoil Sections with Plain Flaps
Critical Mach number as function of lift coefficient is determined for certain moderately thick NACA low-drag airfoils. Results, given graphically, included calculations on same airfoil sections with plain flaps for small flap deflections. Curves indicate optimum critical conditions for airfoils with flaps in such form that they can be compared with corresponding results for zero flap deflections. Plain flaps increase life-coefficient range for which critical Mach number is in region of high values characteristic of low-drag airfoils. digital.library.unt.edu/ark:/67531/metadc61295/
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/
Determination of Flight Paths of an SBD-1 Airplane in Simulated Diving Attacks, Special Report
An investigation has been made to determine the motions of and the flight paths describe by a Navy dive-bombing airplane in simulated diving attacks. The data necessary to evaluate these items, with the exception of the atmospheric wind data, were obtained from automatic recording instruments installed entirely within the airplane. The atmospheric wind data were obtained from the ground by the balloon-theodolite method. The results of typical dives at various dive angles are presented in the form of time histories of the motion of the airplane as well as flight paths calculated with respect to still air and with respect to the ground. digital.library.unt.edu/ark:/67531/metadc65195/
Determination of general relations for the behavior of turbulent boundary layers
No Description digital.library.unt.edu/ark:/67531/metadc279609/
The determination of span load distribution at high speeds by use of high-speed wind-tunnel section data
No Description digital.library.unt.edu/ark:/67531/metadc61274/
Determination of the effect of horizontal-tail flexibility on longitudinal control characteristics
No Description digital.library.unt.edu/ark:/67531/metadc61496/
Determination of the stability and control characteristics of a straight-wing, tailless fighter-airplane model in the Langley free-flight tunnel
No Description digital.library.unt.edu/ark:/67531/metadc61003/
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/
The development and application of high-critical-speed nose inlets
No Description digital.library.unt.edu/ark:/67531/metadc279653/
Development of Wing Inlets
Lift, drag, internal flow, and pressure distribution measurements were made on a low-drag airfoil incorporating various air inlet designs. Two leading-edge air inlets are developed which feature higher lift coefficients and critical Mach than the basic airfoil. Higher lift coefficients and critical speeds are obtained for leading half of these inlet sections but because of high suction pressures near exist, slightly lower critical speeds are obtained for the entire inlet section than the basic airfoil. digital.library.unt.edu/ark:/67531/metadc61340/
Effect of a trailing-edge extension on the characteristics of a propeller section
No Description digital.library.unt.edu/ark:/67531/metadc61477/
Effect of Compressibility on Pressure Distribution over an Airfoil with a Slotted Frise Aileron
Pressure distribution measurements were made over an airfoil with slotted Frise aileron up to 0.76 Mach at various angles of attack and aileron defections. Section characteristics were determined from these pressure data. Results indicated loss of aileron rolling power for deflections ranging from -12 Degrees to -19 Degrees. High stick forces for non-differential deflections incurred at high speed, which were due to overbalancing tendency of up-moving aileron, may precipitate serious control difficulties. Detailed results are presented graphically. digital.library.unt.edu/ark:/67531/metadc61472/
The Effect of Compressibility on the Growth of the Laminar Boundary Layer on Low-Drag Wings and Bodies
The development of the laminar boundary layer in a compressible fluid is considered. Formulas are given for determining the boundary-layer thickness and the ratio of the boundary-layer Reynolds number to the body Reynolds number for airfoils and bodies of revolution. It i s shown that the effect of compressibility will profoundly alter the Reynolds number corresponding to the upper limit of the range of the low-drag coefficients . The available data indicate that for low-drag and high critical compressibility speed airfoils and bodies of revolution, this effect is favorable. digital.library.unt.edu/ark:/67531/metadc65159/
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/
Effect of Helicopter Performance of Modifications in Profile-Drag Characteristics of Rotor-Blade Airfoil Sections
Rough conventional, smooth conventional, and laminar-flow or low-drag sections were tested. The items covered are rotor thrust for fixed power in hovering, range and endurance at cruising speed, and power required at high-forward speed. Calculations indicated that a smooth conventional section gives marked performance gains. Smaller gains are obtainable by using a low-drag section. At high speeds or loads the low-drag section is inferior to the smooth conventional section. digital.library.unt.edu/ark:/67531/metadc62530/
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/
Effect of leakage past aileron nose on aerodynamic characteristics of plain and internally balanced ailerons on NACA 66(215)-216, a = 1.0 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61639/
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