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National Advisory Committee for Aeronautics Collection
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National Advisory Committee for Aeronautics Collection
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NACA Research Memorandums
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National Advisory Committee for Aeronautics Collection
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Aerodynamic Characteristics of a Number of Modified NACA Four-Digit-Series Airfoil Sections
Aerodynamic characteristics of several flap-type trailing-edge controls on a trapezoidal wing at Mach numbers of 1.61 and 2.01
Aerodynamic Forces and Moments on a Large Ogive-Cylinder Store at Various Locations Below the Fuselage Center Line of a Swept-Wing Bomber Configuration at a Mach Number of 1.61
Aerodynamic heating of aircraft components
Aircraft compass characteristics
Airfoil Pressure Distribution Investigation in the Variable Density Wind Tunnel
Altitude operational characteristics of prototype J40-WE-8 turbojet engine
Analysis of coolant-flow requirements for an improved, internal-strut-supported, air-cooled turbine-rotor blade
Analysis of cooling limitations and effect of engine-cooling improvements on level-flight cruising performance of four-engine heavy bomber
An analysis of the factors that determine the periodic twist of an autogiro rotor blade, with a comparison of predicted and measured results
Analytical evaluation of effect of equivalence ratio inlet-air temperature and combustion pressure on performance of several possible ram-jet fuels
Application of Radial-Equilibrium Condition to Axial-Flow Turbomachine Design Including Consideration of Change of Entropy With Radius Downstream of Blade Row
Aspects of internal-flow-system design for helicopter propulsive units
Basic pressure measurements on a fuselage and a 45 degrees sweptback wing-fuselage combination at transonic speeds in the slotted test section of the Langley 8-foot high-speed tunnel
Blower Cooling of Finned Cylinders
Bodies of revolution having minimum drag at high supersonic airspeeds
Canopy loads investigation for the F6F-3 airplane
Combustion efficiency performance of a MIL-F-5624 type fuel and monomethylnapthalene in a single vaporizing combustor
A Comparison of the Spanwise Loading Calculated by Various Methods With Experimental Loadings Obtained on a 45 Degree Sweptback Wing of Aspect Ratio 8.02 at a Reynolds Number of 4.0 X 10(6)
A comparison of theoretical and experimental loading on a 63 degrees swept-back wing at supersonic speeds
Component performance investigation of J71 experimental turbine 7: effect of first-stator adjustment; over-all performance of J71 turbine with 87-percent-design stator area
Concluding Report on Free-Spinning and Recovery Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane, TED No. NACA AD 395
Control Hinge-Moment and Effectiveness Characteristics of a 60 Degree Half-Delta Tip Control on a 60 Degree Delta Wing at Mach Numbers of 1.41 and 1.96
Critical Compressive Stress for Outstanding Flanges
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