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- Performance characteristics of several types of axially symmetric nose inlets at Mach number 3.85
- Some factors affecting automatic control of airplanes
- Reflection of shock waves from slotted walls at Mach number 1.62
- Investigation of liquid fluorine and hydrazine-ammonia mixture in 100-pound-thrust rocket engine
- Analytical procedures for rapid selection of coolant passage configurations for air-cooled turbine rotor blades and for evaluation of heat-transfer, strength, and pressure-loss characteristics
- The effect of bluntness on the drag of spherical-tipped truncated cones of fineness ratio 3 at Mach numbers 1.2 to 7.4
- Turbojet combustor efficiency with ceramic-coated liners and with mechanical control of fuel wash on walls
- Relations between fuel properties and combustion carbon deposition
- Investigation of effects of additives on storage properties of fuming nitric acids
- Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : an investigation at large Reynolds numbers of the low-speed characteristics of several wing-body combinations
- Effects on the weight-flow range and efficiency of a typical axial-flow compressor inlet stage that result from the use of a decreased blade camber or decreased guide-vane turning
- Pressure drop in coolant passages of two air-cooled turbine-blade configurations
- Transonic free-flight investigation of the total drag and of the component drags (cowl pressure, additive, base, friction, and internal) encountered by a 16-inch-diameter ram-jet engine for Mach numbers from 0.80 to 1.43
- Performance of supersonic scoop inlets
- Investigation at high and low subsonic Mach numbers of two symmetrical 6-percent-thick airfoil sections designed to have high maximum lift coefficients at low speeds
- Investigation at low speed of the downwash, sidewash, and wake characteristics behind a large-scale triangular wing, including the effects of yaw, full-span trailing-edge flaps, and two leading-edge modifications
- Investigation at high subsonic speeds of bodies mounted from the wing of an unswept-wing-fuselage model, including measurements of body loads
- Effect of free methyl radicals on slow oxidation of propane and ethane
- Distribution of fissionable material in thermal reactors of spherical geometry for uniform power generation
- Effect of camber and twist on the stability characteristics of models having a 45 degree swept wing as determined by the free-fall method at transonic speeds
- Facilities and methods used in full-scale airplane crash-fire investigation
- Cooling characteristics of an experimental tail-pipe burner with an annular cooling-air passage
- Experimental investigation of the stability, control, and induced rolling moments of a canard missile airframe at a Mach number of 1.7
- Experimental investigation of the static aerodynamic and dynamic damping-in-roll characteristics of an 8-cm aircraft rocket with solid and slotted fins
- An experimental investigation of the zero-lift pressure distribution over a wedge airfoil in closed, slotted, and open-throat tunnels at transonic Mach numbers
- Dynamic corrosion of a stainless-steel specimen by water at 500 F using a toroid circulating apparatus /c Leland G. Desmon, Don R. Mosher
- Free-flight investigation of longitudinal stability and control of a rocket-propelled missile model having cruciform, triangular, inline wings and tails
- Chordwise pressure distribution at high subsonic speeds near midsemispan of a tapered 35 degree sweptback wing of aspect ratio 4 having NACA 65A006 airfoil sections and equipped with various spoiler ailerons
- Investigation of the hydrodynamic stability and resistance of two streamline fuselages
- The effects on the aerodynamic characteristics of varying the wing thickness ratio of a triangular wing-body configuration at transonic speeds from tests by the NACA wing-flow method
- Effects of simulated skin wrinkles on the wing surface on the aerodynamic characteristics of two wing-body combinations employing wings of low aspect ratio at subsonic and supersonic speeds
- Lift, drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane tapered wing of aspect ratio 3.1 with 3-percent-thick rounded-nose section
- Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Twisted and cambered triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution
- Low-speed longitudinal aerodynamic characteristics of a twisted and cambered wing of 45 degree sweepback and aspect ratio 8 with and without high-lift and stall-control devices and a fuselage at Reynolds numbers from 1.5 x 10(exp 6) to 4.8 x 10(exp 6
- Studies of the flow field behind a large scale 47.5 degree sweptback wing having circular-arc airfoil sections and equipped with drooped-nose and plain flaps
- A unified two-dimensional approach to the calculation of three-dimensional hypersonic flows, with application to bodies of revolution
- Effect of vertical location of a horizontal tail on the static longitudinal stability characteristics of a 45 degree sweptback-wing-fuselage combination of aspect ratio 8 at a Reynolds number of 4.0 x 10(exp 6)
- Theoretical performance of liquid ammonia, hydrazine and mixture of liquid ammonia and hydrazine as fuels with liquid oxygen biflouride as oxidant for rocket engines 1: mixture of liquid ammonia and hydrazine
- Some effects of side-wall modifications on the drag and pressure recovery of an NACA submerged inlet at transonic speeds
- Low-speed aerodynamic characteristics of a large-scale 60 degree swept-back wing with high lift devices
- Pressure distribution and pressure drag for a hemispherical nose at Mach numbers 2.05, 2.54, and 3.04
- Internal-film-cooling experiments with 2- and 4-inch smooth-surface tubes and gas temperatures to 2000 degrees Fahrenheit
- Flight calibration of angle-of-attack and sideslip detectors on the fuselage of a 35 degree swept-wing fighter airplane
- Small-scale transonic investigation of the effects of twist and camber on the aerodynamic characteristics of a 60 degrees 42' sweptback wing of aspect ratio 1.94
- Free-flight measurements of some effects of aileron span, chord, and deflection and of wing flexibility on the rolling effectiveness of ailerons on sweptback wings at Mach numbers between 0.8 and 1.6
- Summary of some effective aerodynamic twisting-moment coefficients of various wing-control configurations at Mach numbers from 0.6 to 1.7 as determined from rocket-powered models
- A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees
- Reciprocity relations in aerodynamics
- Simple Graphical Solution of Heat Transfer and Evaporation From Surface Heated to Prevent Icing
- A Probability Analysis of the Meteorological Factors Conducive to Aircraft Icing in the United States