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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
An acceleration schedule control for accelerating a turbojet engine and its use with a speed control
No Description digital.library.unt.edu/ark:/67531/metadc63981/
An acceleration schedule control for accelerating a turbojet engine and its use with a speed control
Accelerating-limiting controls for turbojet engines. digital.library.unt.edu/ark:/67531/metadc52973/
Accelerations in fighter-airplane crashes
No Description digital.library.unt.edu/ark:/67531/metadc63594/
An active particle diffusion theory of flame quenching for laminar flames / Dorothy M. Simon and Frank E. Belles
An equation for quenching distance based on the destruction of chain carriers by the surface is derived. The equation expresses the quenching distance in terms of the diffusion coefficients and partial pressures of the chain carriers and gas phase molecules, the efficiency of the surface as a chain breaker, the total pressure of the mixture, and a constant which depends on the geometry of the quenching surface. Quenching distances measured by flashback for propane-air flames are shown to be consistent with the mechanism. The derived equation is used with the lean inflammability limit and a rate constant calculated from burning velocity data to estimate quenching distances for propane-air (hydrocarbon lean) flames satisfactorily. digital.library.unt.edu/ark:/67531/metadc59077/
Adaptation of a Cascade Impactor to Flight Measurement of Droplet Size in Clouds
A cascade impactor, an instrument for obtaining: the size distribution of droplets borne in a low-velocity air stream, was adapted for flight cloud droplet-size studies. The air containing the droplets was slowed down from flight speed by a diffuser to the inlet-air velocity of the impactor. The droplets that enter the impactor impinge on four slides coated with magnesium oxide. Each slide catches a different size range. The relation between the size of droplet impressions and the droplet size was evaluated so that the droplet-size distributions may be found from these slides. The magnesium oxide coating provides a permanent record. of the droplet impression that is not affected by droplet evaporation after the. droplets have impinged. digital.library.unt.edu/ark:/67531/metadc53539/
Adaptation of Combustion Principles to Aircraft Propulsion, Volume 2, Combustion in Air-Breathing Jet Engines
This volume continues the NACA study of combustion principles for aircraft propulsion. The various aspects of combustion pertinent to jet engines are organized and interpreted with quite extensive information, particularly for basic or fundamental. subject matter. The report concerns only air-breathing engines and hydrocarbon fuels, and not rocket engines and high-energy fuels. Since the references have been selected to illustrate important points, the bibliographies, while thorough, are not complete. This volumes describes the observed performance and design problems of engine combustors of the principal types. These include combustor-inlet conditions; starting, acceleration, combustion limits, combustion efficiency, coke deposits, and smoke formation in turbojets; ram-jet performance; and afterburner performance and design. digital.library.unt.edu/ark:/67531/metadc63711/
Adaptation of Combustion Principles to Aircraft Propulsion, Volume I, Basic Considerations in the Combustion of Hydrocarbon Fuels with Air
The report summarizes source material on combustion for flight-propulsion engineers. First, several chapters review fundamental processes such as fuel-air mixture preparation, gas flow and mixing, flammability and ignition, flame propagation in both homogenous and heterogenous media, flame stabilization, combustion oscillations, and smoke and carbon formation. The practical significance and the relation of these processes to theory are presented. A second series of chapters describes the observed performance and design problems of engine combustors of the principal types. An attempt is made to interpret performance in terms of the fundamental processes and theories previously reviewed. Third, the design of high-speed combustion systems is discussed. Combustor design principles that can be established from basic considerations and from experience with actual combustors are described. Finally, future requirements for aircraft engine combustion systems are examined. digital.library.unt.edu/ark:/67531/metadc61037/
Additional abstracts pertaining to seaplanes
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Additional comparisons between computed and measured transonic drag-rise coefficients at zero lift for wing-body-tail configurations
No Description digital.library.unt.edu/ark:/67531/metadc61416/
Additional experimental heat-transfer and durability data on several forced-convection, air-cooled, strut-supported turbine blades of improved design
No Description digital.library.unt.edu/ark:/67531/metadc60906/
Additional experiments with flat-top wing- body combinations at high supersonic speeds
Flat top wing body configuration effects on aerodynamic characteristics of supersonic aircraft. digital.library.unt.edu/ark:/67531/metadc53065/
Additional fatigue tests on effects of design details in 355-T6 sand-cast aluminum alloy
No Description digital.library.unt.edu/ark:/67531/metadc59956/
Additional free-flight tests of the rolling effectiveness of several wing-spoiler arrangements at high subsonic, transonic, and supersonic speeds
No Description digital.library.unt.edu/ark:/67531/metadc58001/
Additional measurements of the low-speed static stability of a configuration employing three triangular wing panels and a body of equal length
No Description digital.library.unt.edu/ark:/67531/metadc63845/
Additional results in a free-flight investigation of control effectiveness of full-span, 0.2-chord plain ailerons at high subsonic, transonic, and supersonic speeds to determine some effects of wing sweepback, aspect ratio, taper, and section thickne
No Description digital.library.unt.edu/ark:/67531/metadc58183/
Additional results of an investigation at transonic speeds to determine the effects of a heated propulsive jet on the drag characteristics of a series of related afterbodies
No Description digital.library.unt.edu/ark:/67531/metadc62574/
Additional Results on the Static Longitudinal and Lateral Stability Characteristics of a 0.05-Scale Model of the Convair F2Y-1 Airplane at High Subsonic Speeds
Additional results on the static longitudinal and lateral stability characteristics of a 0.05-scale model of the Convair F2Y-1 water-based fighter airplane were obtained in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.50 to 0.92. The maximum angle-of-attack range (obtained at the lower Mach numbers) was from -2 degrees to 25 degrees. The sideslip-angle range investigated was from -4 degrees to 12 degrees. The investigation included effects of various arrangements of wing fences, leading-edge chord-extensions, and leading-edge notches. Various fuselage fences, spoilers, and a dive brake also were investigated. From overall considerations of lift, drag, and pitching moments, it appears that there were two modifications somewhat superior to any of the others investigated: One was a configuration that employed a full-chord fence and a partial-chord fence located at 0.63 semispan and 0.55 semispan, respectively. The second was a leading-edge chord-extension that extended from 0.68 semispan to 0.85 semispan in combination with a leading-edge notch located at 0.68 semispan. With plus or minus 10 degrees aileron, the estimated wing-tip helix angle was reduced from 0.125 at a Mach number of 0.50 to 0.088 at a Mach number of 0.92, with corresponding rates of roll of 4.0 and 5.2 radians per second. The upper aft fuselage dive brake, when deflected 30 degrees and 60 degrees, reduced the rudder effectiveness about 10 to 20 percent and about 35 to 50 percent, respectively. digital.library.unt.edu/ark:/67531/metadc65304/
Additional Studies of the Stability and Controllability of an Unswept-Wing Vertically Rising Airplane Model in Hovering Flight Including Studies of Various Tethered Landing Techniques
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The adhesion of molten boron oxide to various materials
No Description digital.library.unt.edu/ark:/67531/metadc64004/
Adhesive and protective characteristics of ceramic coating A-417 and its effect on engine life of forged Refractaloy-26 (AMS 5760) and cast stellite 21 (AMS 5385) turbine blades
The adhesive and protective characteristics of National Bureau of Standards Coating A-417 were investigated, as well as the effect of the coating on the life of forged Refractaloy 26 and cast Stellite 21 turbine blades. Coated and uncoated blades were run in a full-scale J33-9 engine and were subjected to simulated service operations consisting of consecutive 20-minute cycles (15 min at rated speed and approximately 5 min at idle). The ceramic coating adhered well to Refractaloy 26 and Stellite 21 turbine blades operated at 1500 degrees F. The coating also prevented corrosion of the Refractaloy 26, a corrosion-sensitive nickel-base alloy, and of the Stellite 21, a relatively corrosion-resistant cobalt-base alloy. Although the coating prevented corrosion of both alloys, it had no apparent effect on blade life. digital.library.unt.edu/ark:/67531/metadc59641/
Aerodynamic and hydrodynamic characteristics of a deck-inlet multijet water-based-aircraft configuration designed for supersonic flight
No Description digital.library.unt.edu/ark:/67531/metadc62900/
Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing
No Description digital.library.unt.edu/ark:/67531/metadc63527/
Aerodynamic and hydrodynamic characteristics of models of some aircraft-towed mine-sweeping devices : TED No. NACA AR 8201
No Description digital.library.unt.edu/ark:/67531/metadc62388/
Aerodynamic and inlet-flow-field characteristics at a free-stream Mach number of 3.0 for airplanes with circular fuselage cross sections and for two engine locations
No Description digital.library.unt.edu/ark:/67531/metadc64014/
Aerodynamic and lateral-control characteristics of a 1/28-scale model of the Bell X-1 airplane wing-fuselage combination : transonic-bump method
No Description digital.library.unt.edu/ark:/67531/metadc58563/
Aerodynamic characteristics and pressure distributions of a 6-percent-thick 49 degree sweptback wing with blowing over half-span and full-span flaps
No Description digital.library.unt.edu/ark:/67531/metadc61390/
Aerodynamic characteristics at a Mach number of 1.25 of a 6-percent-thick triangular wing and 6- and 9-percent-thick triangular wings in combination with a fuselage : wing aspect ratio 2.31, biconvex airfoil sections
No Description digital.library.unt.edu/ark:/67531/metadc58471/
Aerodynamic characteristics at a Mach number of 1.38 of four wings of aspect ratio 4 having quarter-chord sweep angles of 0 degrees, 35 degrees, 45 degrees, and 60 degrees
No Description digital.library.unt.edu/ark:/67531/metadc58552/
Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One with Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One with a Flared Afterbody and All-Movable Controls
No Description digital.library.unt.edu/ark:/67531/metadc53265/
Aerodynamic characteristics at a Mach number of 6.8 of two hypersonic missile configurations, one with low-aspect-ratio cruciform fins and trailing-edge flaps and one with a flared afterbody and all-movable controls
No Description digital.library.unt.edu/ark:/67531/metadc64170/
Aerodynamic characteristics at high and low subsonic Mach numbers of four NACA 6-series airfoil sections at angles of attack from -2 to 31 degrees
No Description digital.library.unt.edu/ark:/67531/metadc59710/
Aerodynamic Characteristics at High and Low Subsonic Mach Numbers of the NACA 0012, 64(sub 2)-015, and 64(sub 3)-018 Airfoil Sections at Angles of Attack from -2 Degrees to 30 Degrees
An investigation has been made in the Langley low-turbulence pressure tunnel of the aerodynamic characteristics of the NACA 0012, 64(sub 2)-015, and 64(sub 3)-018 airfoil sections. Data were obtained at Mach numbers from 0.3 to that for tunnel choke, at angles of attack from -2deg to 30deg, and with the surface. of each airfoil smooth-and with roughness applied at the leading edge.The Reynolds numbers of the tests ranged from 0.8 x 10(exp 6) to 4.4 x 10(exp 6). The results are presented as variations of lift, drag, and quarter-chord pitching-moment coefficients with Mach number. digital.library.unt.edu/ark:/67531/metadc64237/
Aerodynamic characteristics at high speeds of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller
No Description digital.library.unt.edu/ark:/67531/metadc57659/
Aerodynamic characteristics at high speeds of full-scale propellers having Clark Y blade sections
No Description digital.library.unt.edu/ark:/67531/metadc64614/
Aerodynamic Characteristics at High Speeds of Full-Scale Propellers having Different Shank Designs
Tests of two 10-foot-diameter two-blade propellers which differed only in shank design have been made in the Langley 16-foot high-speed tunnel. The propellers are designated by their blade design numbers, NACA 10-(5)(08)-03, which had aerodynamically efficient airfoil shank sections, and NACA l0-(5)(08)-03R which had thick cylindrical shank sections typical of conventiona1 blades, The propellers mere tested on a 2000-horsepower dynamometer through a range of blade-angles from 20deg to 55deg at various rotational speeds and at airspeeds up to 496 miles per hour. The resultant tip speeds obtained simulate actual flight conditions, and the variation of air-stream Mach number with advance ratio is within the range of full-scale constant-speed propeller operation. Both propellers were very efficient, the maximum envelope efficiency being approximately 0,95 for the NACA 10-(5)(08)-03 propeller and about 5 percent less for the NACA 10-(5)(08)-03R propeller. Based on constant power and rotational speed, the efficiency of the NACA 10-(05)(08)-03 propeller was from 2.8 to 12 percent higher than that of the NACA 10-(5)(08)-03R propeller over a range of airspeeds from 225 to 450 miles per hour. The loss in maximum efficiency at the design blade angle for the NACA 10-(5)(08)-03 and 10-(5)(08)-03R propellers vas about 22 and 25 percent, respectively, for an increase in helical tip Mach number from 0.70 to 1.14. digital.library.unt.edu/ark:/67531/metadc64248/
Aerodynamic characteristics at Mach number 4.04 of a rectangular wing of aspect ratio 1.33 having a 6-percent-thick circular-arc profile and a 30-percent-chord full-span trailing-edge flap
No Description digital.library.unt.edu/ark:/67531/metadc59736/
Aerodynamic characteristics at Mach number of 2.01 of two cruciform missile configurations having 70 degree delta wings with length-diameter ratios of 14.8 and 17.7 with several canard controls
No Description digital.library.unt.edu/ark:/67531/metadc60740/
Aerodynamic characteristics at Mach number of 4.06 of a typical supersonic airplane model using body and vertical-tail wedges to improve directional stability
No Description digital.library.unt.edu/ark:/67531/metadc63668/
Aerodynamic characteristics at Mach numbers 2.36 and 2.87 of an airplane configuration having a cambered arrow wing with a 75 degree swept leading edge
No Description digital.library.unt.edu/ark:/67531/metadc64269/
Aerodynamic characteristics at Mach numbers from 0.7 to 1.75 of a four-engine swept-wing airplane configuration as obtained from a rocket-propelled model test
No Description digital.library.unt.edu/ark:/67531/metadc62214/
Aerodynamic characteristics at Mach numbers from 2.5 to 3.5 of a canard bomber configuration designed for supersonic cruise flight
No Description digital.library.unt.edu/ark:/67531/metadc64406/
Aerodynamic characteristics at Mach numbers of 1.61 and 2.01 of various tip controls on the wing panel of a 0.05-scale model of a Martin XASM-N-7 (Bullpup) missile : TED No. NACA AD 3106
No Description digital.library.unt.edu/ark:/67531/metadc62380/
Aerodynamic characteristics at subcritical and supercritical Mach numbers of two airfoil sections having sharp leading edges and extreme rearward positions of maximum thickness
No Description digital.library.unt.edu/ark:/67531/metadc58030/
Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 I : maximum thickness at 20 percent of the chord
No Description digital.library.unt.edu/ark:/67531/metadc57967/
Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 II : maximum thickness at midchord
The lift, drag, and pitching-moment characteristics of a triangular wing, having an aspect ratio of 2 and a symmetrical double-wedge profile of 5-percent-chord maximum thickness at midchord, have been evaluated from wind-tunnel tests at Mach numbers from 0.50 to 0.975 and from 1.09 to 1.49 and at Reynolds numbers ranging from 0.67 to 0.85 million. The lift, drag, and pitching-moment coefficients of the triangular wing with a leading-edge sweepback of approximately 63 degrees did not exhibit the irregular variations with Mach number at high subsonic and low supersonic Mach numbers that are characteristic of unswept wings. The lift-curve slope increased steadily with Mach number below unity and declined slowly beyond the Mach number of 1.13. A substantial rise in the minimum drag coefficient occurred between Mach numbers of 0.95 and 1.20 with an associated reduction in the maximum lift-drag ratio. The aerodynamic center shifted rearward toward the centroid of area of the wing with increasing Mach number below 0.975; whereas above 1.09 it coincided with the centroid. digital.library.unt.edu/ark:/67531/metadc64583/
Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness
No Description digital.library.unt.edu/ark:/67531/metadc57819/
Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effect at M = 2.01 of nacelle shape and position on the aerodynamic characteristics in
No Description digital.library.unt.edu/ark:/67531/metadc64976/
Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch
No Description digital.library.unt.edu/ark:/67531/metadc59859/
Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the static lateral stability characteris
No Description digital.library.unt.edu/ark:/67531/metadc59769/
Aerodynamic characteristics at transonic and supersonic speeds of a rocket-propelled airplane configuration having a 52.5 degree delta wing and a low, swept horizontal tail
No Description digital.library.unt.edu/ark:/67531/metadc60270/