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- Correlation of Supersonic Convective Heat-Transfer Coefficients From Measurements of the Skin Temperature of a Parabolic Body of Revolution (NACA RM-10)
- Buffeting-Load Measurements on a Jet-Powered Bomber Airplane With Reflexed Flaps
- Aerodynamic Characteristics of Tapered Wings Having Aspect Ratios of 4, 6, and 8, Quarter-Chord Lines Swept Back 45 Degrees, and NACA 63(Sub 1)a012 Airfoil Sections: Transonic-Bump Method
- Aerodynamic Characteristics of Four Wings of Sweepback Angles 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees, NACA 65A006 Airfoil Section, Aspect Ratio 4, and Taper Ratio 0.6 in Combination With a Fuselage at High Subsonic Mach Numbers and at a Mach Number of 1.2
- Aerodynamic Characteristics of Four Bodies of Revolution Showing Some Effects of Afterbody Shape and Fineness Ratio at Free-Stream Mach Numbers From 1.50 to 1.99
- Average Skin-Friction Coefficients From Boundary-Layer Measurements in Flight on a Parabolic Body of Revolution (NACA RM-10) at Supersonic Speeds and at Large Reynolds Numbers
- Interferometer With Large Working Field Utilizing Schlieren Optics
- Low-Speed Investigation of Several Types of Split Flap on a 47.7 Degree Sweptback-Wing - Fuselage Combination of Aspect Ratio 5.1 at a Reynolds Number of 6.0 X 10(Exp 6)
- Low-Speed Investigation of the Effects of Single Slotted and Double Slotted Flaps on a 47.7 Degree Sweptback-Wing: Fuselage Combination at a Reynolds Number of 6.0 X 10(Exp 6)
- Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 50 Degrees 38 Minutes Sweptback Wing of Aspect Ratio 2.98: Transonic-Bump Method
- Investigation of Low-Speed Lateral Control and Hinge-Moment Characteristics of a 20-Percent-Chord Plain Aileron on a 47.7 Degrees Sweptback Wing of Aspect Ratio 5.1 at a Reynolds Number of 6.0 X 10(Exp 6)
- Flight Investigation of the Effect of Sideslip on the Pressure at the Static Orifices of the Boeing B-29 Airplane
- Flight Investigation of the Drag of Round-Nosed Bodies of Revolution at Mach Numbers From 0.6 to 1.5 Using Rocket-Propelled Test Vehicles
- Instrumentation for Recording Transient Performance of Gas-Turbine Engines and Control Systems
- Investigation of Minimum Drag and Maximum Lift-Drag Ratios of Several Wing-Body Combinations Including a Cambered Triangular Wing at Low Reynolds Numbers and at Supersonic Speeds
- An Investigation of the Hydrodynamic Characteristics of a Jet-Powered Dynamic Model of the DR 56 Flying Boat: TED No. NACA DE 328
- An Investigation of Flow Characteristics at Mach Number 4.04 Over 6- and 9-Percent-Thick Symmetrical Circular-Arc Airfoils Having 30-Percent-Chord Trailing-Edge Flaps
- Lateral Control Characteristics and Dihedral Effect of a Wing-Body Combination With a Variable Incidence Triangular Wing and Wing-Tip Ailerons at a Mach Number of 1.52
- An Analytic Determination of the Flow Behind a Symmetrical Curved Shock in a Uniform Stream
- Free-Flight Investigation of the Longitudinal Stability and Control of a Rocket-Propelled Missile Model Having Cruciform, Triangular, Interdigitated Wings and Tails
- Horizontal-Tail Effectiveness and Downwash Surveys for Two 47.7 Degree Sweptback Wing-Fuselage Combinations With Aspect Ratios of 5.1 and 6.0 at a Reynolds Number of 6.0 X 10(Exp 6)
- Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Measurements of the Distribution of the Aerodynamic Load Among the Wing, Fuselage, and Horizontal Tail at Mach Numbers Up to 0.87
- Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Static Longitudinal Stability and Control Characteristics at Mach Numbers Up to 0.87
- Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Dynamic Lateral Stability
- Investigation at Supersonic Speeds of Some of the Factors Affecting the Flow Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap
- An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Force Characteristics of the Complete Configuration and Its Various Components at Mach Numbers of 1.40 and 1.59
- Experimental investigation of tail-pipe-burner design variables
- Investigations on Wings With and Without Sweepback at High Subsonic Speeds
- On the Turbulent Friction Layer for Rising Pressure
- On the recording of turbulent longitudinal and transverse fluctuations
- Flight-Determination of the Low-Lift Drag and Longitudinal Stability of a 1/10-Scale Rocket-Powered Model of the Douglas XF4D-1 Airplane at Mach Numbers from 0.7
- Preliminary Transient Performance Data for Afterburner Operation of Westinghouse Electronic Power Regulator on XJ34-WE-32 Turbojet Engine in Altitude Wind Tunnel
- On Ionization and Luminescence in Flames
- Deplacement Effect of the Laminar Boundary Layer and the Pressure Drag
- Supplementary Ditching Investigation of a 1/18-Scale Model of the North American B-45 Airplane
- A Thermodynamic Study of the Turbine-Propeller Engine
- Yawed-Landing Investigation of a Model of the Convair Y2-2 Airplane, TED No. NACA DE 363
- On Motion of Fluid in Boundary Layer Near Line of Intersection of Two Planes
- Preliminary Results of a Flight Investigation of 1/6-Scale Rocket-Powered Models of the Bell MX-776 to Determine Aileron Rolling Effectiveness and Total Drag
- Investigation of Turbulent Flow in a Two-Dimensional Channel
- The Design of Variable Mach Number Asymmetric Super-Sonic Nozzles by Two Procedures Employing Inclined and Curved Sonic Lines
- Effect of Angle of Incidence of Second-Stage Vane Assembly on Third-Stage Compressor-Blade Vibration and Engine Performance
- Annual Report of the National Advisory Committee for Aeronautics (38th). Administrative Report Including Technical Report Nos. 1059 to 1110
- Annual Report of the National Advisory Committee for Aeronautics (36th). Administrative Report Including Technical Report Nos. 951 to 1002
- Annual Report of the National Advisory Committee for Aeronautics (34th). Administrative Report Including Technical Report Nos. 892 to 921
- Annual Report of the National Advisory Committee for Aeronautics (35th). Administrative Report Including Technical Report Nos. 922 to 950
- Ditching Investigation of a 1/14-Scale Model of the XC-123 Airplane
- Factors Affecting the Starting Characteristics of Gas-Turbine Engines
- NACA Conference on Aircraft Structures
- Coolant-Flow Calibrations of Three Simulated Porous Gas-Turbine Blades