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- Maximum-Lift Investigation at Mach Numbers From 0.05 to 1.20 of a Wing With Leading Edge Swept Back 42 Degrees
- Longitudinal Trim and Drag Characteristics of Rocket-Propelled Models Representing Two Airplane Configurations
- The Longitudinal Stability, Control Effectiveness, and Control Hinge Moment Characteristics Obtained From a Flight Investigation of a Canard Missile Configuration at Transonic and Supersonic Speeds
- Low-Speed Investigation of the Aerodynamic Loads on the Droop-Nose Flap of a Wing With Leading Edge Swept Back 47.5 Degrees and Having Symmetrical Circular-Arc Airfoil Sections at a Reynolds Number of 4.3 X 10 (Exp 6)
- Low-Speed Investigation of the Effect of Several Flap and Spoiler Ailerons on the Lateral Characteristics of a 47.5 Degree Sweptback-Wing-Fuselage Combination at a Reynolds Number of 4.4. X 10(6)
- Low-Speed Investigation of Deflectable Wing-Tip Elevators on a Low-Aspect-Ratio Untapered 45 Degree Sweptback Semispan Wing With and Without an End Plate
- Low-Speed Pressure-Distribution Measurements at Reynolds Number of 3.5 X 10(Exp 6) on a Wing With Leading-Edge Sweepback Decreasing From 45 Degrees at the Root to 20 Degrees at the Tip
- Investigation of Blade-Row Flow Distributions in Axial-Flow-Compressor Stage Consisting of Guide Vanes and Rotor-Blade Row
- Flight Investigation of the Pressure Distributions and Loads on a Front and Rear Sliding Canopy
- Flight Investigation of the Effect of Thickening the Aileron Trailing Edge on Control Effectiveness for Sweptback Tapered Wings Having Sharp-and Round-Nose Sections
- Flight Investigation of the Aileron Characteristics of the Douglas D-558-I Airplane (BuAero No. 37972) at Mach Numbers Between 0.6 and 0.89
- Flight Investigation of Longitudinal Stability and Control Characteristics and Stalling Characteristics of a C-54D Airplane
- Full-Scale Investigation of Boundary-Layer Control by Suction Through Leading-Edge Slots on a Wing-Fuselage Configuration Having 47.5 Degree Leading-Edge Sweep With and Without Flaps
- Longitudinal Stability and Control Characteristics at High Subsonic Speeds of Two Models of a Transonic Research Airplane With Wings and Horizontal Tails of Aspect Ratios 4.2 and 2
- Measurements of Aerodynamic Characteristics of a 35 Degree Sweptback NACA 65-009 Airfoil Model With 1/4-Chord Bevelled-Trailing-Edge Flap and Trim Tab by the NACA Wing-Flow Method
- Measurements of Aerodynamic Characteristics of a 35 Degree Sweepback NACA 65-009 Airfoil Model With 1/4 Chord Flap Having 31 Percent Flap Chord Overhang Balance by the NACA Wing Flow Method
- Investigation of the Dynamic Longitudinal Stability of Two Equal Size Models Coupled in Tandem with a Single Joint: Preliminary Model Flight Tests
- Investigation of Operating Pressure Ratio of a Supersonic Wind Tunnel Utilizing Distributed Boundary-Layer Suction in Test Section
- An Investigation of the Longitudinal Characteristics of the X-3 Configuration Using Rocket-Propelled Models: Preliminary Results at Mach Numbers From 0.65 to 1.25
- Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Low-Speed Stalling and Lift Characteristics
- Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Measurements of the Buffet Boundary and Peak Airplane Normal-Force Coefficients at Mach Numbers Up to 0.90
- Flight Tests at Supersonic Speeds to Determine the Effect of Taper on the Zero-Lift Drag of Sweptback Low-Aspect-Ratio Wings
- Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Static Lateral and Directional Stability Characteristics as Measured in Sideslips at Mach Numbers Up to 0.87
- Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Measurements of Wing Loads at Mach Numbers Up to 0.87
- Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Lateral Control Characteristics as Measured in Abrupt Aileron Rolls at Mach Numbers Up to 0.86
- Flight Measurements of the Pressure Distribution on the Wing of the X-1 Airplane (10 Percent Thick Wing) Over a Chordwise Station Near the Midspan, in Level Flight at Mach Numbers From 0.79 to 1.00 and in a Pull Up at a Mach Number of 0.98
- An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Static Lateral Control Characteristics at Mach Numbers of 1.40 and 1.59
- Investigation of a Shrouded and an Unshrouded Axial-Flow Supersonic Compressor
- Investigation at Mach Number 1.62 of the Pressure Distribution Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap
- Investigation of a 42.7 Degree Sweptback Wing Model to Determine the Effects of Trailing-Edge Thickness on the Aileron Hinge-Moment and Flutter Characteristics at Transonic Speeds
- Experimental Investigation of Spreading Characteristics of Choked Jets Expanding into Quiescent Air
- Rough-Water Tests of Models of the Vosper and Plum Planing Boats
- Preliminary Results From Fatigue Tests With Reference to Operational Statistics
- Equations of Motion of a Rocket
- Two-Dimensional Symmetrical Inlets With External Compression
- Range Performance of Bombers Powered by Turbine-Propeller Power Plants
- Time Histories of Horizontal-Tail Loads, Elevator Loads, and Deformations on a Jet-Powered Bomber Airplane During Abrupt Pitching Maneuvers at Approximately 20,000 Feet
- Vibration of a Wing of Finite Span in a Supersonic Flow
- Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds: Several Combinations of the Tail With Each of Two Foreshortened Body Segments
- A Wind-Tunnel Investigation of the Effects of Thrust-Axis Inclination on Propeller First-Order Vibration
- Investigation of the Model Me 210 in the Spin Wind Tunnel of the DVL: Fourth Partial Report - Model With Long Fuselage and With a Vee Tail
- The Zero-Lift Drag of Several Configurations of the XAAM-N-2 Pilotless Aircraft, TED No. NACA DE332
- Subsonic Gas Flow Past A Wing Profile
- Tests of a Hermes A-2 Missile Body at Mach Number 4.04
- Preliminary Results Obtained from Flight Test of a Rocket Model Having the Tail Only of the Grumman XF10F Airplane Configuration, TED No. NACA DE 354
- Summary of Investigations of Mark 25 Aerial-Torpedo Turbine
- Exact Solutions of Equations of Gas Dynamics
- Hydrodynamic Properties of Planing Surfaces and Flying Boats
- The Boundary Layers in Fluids with Little Friction
- The Effect of the Inlet Mach Number and Inlet-Boundary-Layer Thickness on the Performance of a 23 Degree Conical-Diffuser-Tail-Pipe Combination