Search
Search U.S. government technical reports digitized or harvested by TRAIL.
Keyword Search
14045 results returnedSearch results
- Thirty-Ninth Annual Report of the National Advisory Committee for Aeronautics: Administrative Report Including Technical Reports Nos. 1111 to 1157
- An Evaluation of a Rolleron-Roll-Rate-Stabilization System for a Canard Missile Configuration at Mach Numbers From 0.9 to 2.3
- An Evaluation of the Roll-Rate Stabilization System of the Sidewinder Missile at Mach Numbers from 0.9 to 2.3
- Ditching Investigation of a 1/11-Scale Model of the Chance Vought F7U-3 Airplane, TED NO. NACA DE 360
- Ditching Investigation of a 1/20-Scale Model of the Boeing Stratocruiser Airplane (C-97)
- Apparatus for Measurements of Time and Space Correlation
- Low-Lift Drag of the Grumman F9F-9 Airplane as Obtained by a 1/7.5-Scale Rocket-Boosted Model and by Three 1/45.85-Scale Equivalent-Body Models Between Mach Numbers of 0.8 and 1.3, Ted No. NACA DE 391
- Qualitative Results from a Flight Investigation to Determine Aileron Effectiveness of Two Rocket-Propelled 1/20-Scale Models of the MX-76 Missile
- Chemical and Physical Properties of Hi-Cal-2
- Component Performance Investigation of J71 Type II Turbines 5 - Internal Flow Conditions of J71 Type IIA Turbine
- Component Performance Investigation of J71 Type II Turbines 3 - Overall Performance of J71 Type IIA Turbine
- Altitude-Test-Chamber Investigation of the Endurance and Performance Characteristics of the J65-W-7 Engine at a Mach Number of 2.0
- Aerodynamic Loads on an External Store Adjacent to a 45 Degree Sweptback Wing at Mach Numbers From 0.70 to 1.96, Including an Evaluation of Techniques Used
- High-Speed Cascade Tests of the NACA 65-(12A(sub 10))10 and NACA 65-(12A(sub 2)I(sub 8b))10 Compressor Blade Sections
- Injection Principles from Combustion Studies in a 200-Pound-Thrust Rocket Engine Using Liquid Oxygen and Heptane
- NACA Conference on Aerodynamics of High-Speed Aircraft
- An Investigation of the Maximum Lift of Wings at Supersonic Speeds
- Investigation in the Langley Free-Flight Tunnel of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model Simulating the Convair F-102A Airplane
- Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of the Sidewinder Missile at Mach Numbers from 1.2 to 2.1
- Aerodynamic Design of Axial-flow Compressors 6 - Experimental Flow in Two-Dimensional Cascades
- Supplementary Investigation in the Langley Free-Spinning Tunnel of a 1/20-Scale Model of the Douglas XF4D-1 Airplane Including Spin-Recovery Parachute Tests of the Model Loaded to Simulate the Douglas F5D-1 Airplane
- Preliminary Results of the Determination of Inlet-Pressure Distortion Effects on Compressor Stall and Altitude Operating Limits of the J57-P-1 Turbojet Engine
- Free-Spinning Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane, TED No. NACA AD 395
- Free-Stream Boundaries of Turbulent Flows
- Analysis and Calculation by Integral Methods of Laminar Compressible Boundary-Layer With Heat Transfer and With and Without Pressure Gradient
- Experimental investigation of a body flare for obtaining pitch stability and a body flap for obtaining pitch control in hypersonic flight
- Performance of Inconel 550 Turbine Blades in a Turbojet Engine and Effects of Different Forging Temperatures and Heat Treatments
- Preliminary Investigation of a Technique of Producing a Heated Core in a Supersonic Wind-Tunnel Stream
- Experimental Static Aerodynamic Forces and Moments at Low Speed on a Canard Missle During Simulated Launching From the Midsemispan and Wing-Tip Locations of a 45 Degree Sweptback Wing-Fuselage Combination
- Experimental Static Aerodynamic Forces and Moments at Low Speed on a Missile Model During Simulated Launching From the 25-Percent-Semispan and Wing-Tip Location of a 45 Degree Sweptback Wing-Fuselage Combination
- An Experimental Investigation of the Flow Phenomena Over Bodies at High Angles of Attack at a Mach Number of 2.01
- Exploratory Investigation at Mach Number 4.06 of an Airplane Configuration Having a Wing of Trapezoidal Plan Form: Longitudinal and Lateral Control Characteristics
- Flight and Preflight Tests of a Ram Jet Burning Magnesium Slurry Fuel and Utilizing a Solid-Propellant Gas Generator for Fuel Expulsion
- Exploratory Tests of Transpiration Cooling on a Porous 8 Degree Cone at M = 2.05 Using Nitrogen Gas, Helium Gas, and Water as the Coolants
- Experimental Investigation of the Zero-Lift Wave Drag of Seven Pairs of Delta Wings With Constant and Varying Thickness Ratios at Mach Numbers of 1.62, 1.93, and 2.41
- Temperature Recovery Factors on a Slender 12 Degree Cone-Cylinder at Mach Numbers From 3.0 to 6.3 and Angles of Attack Up to 45 Degrees
- Some Effects of Configuration Variables on Store Loads at Supersonic Speeds
- Some Effects of Fluid in Pylon-Mounted Tanks on Flutter
- Some Measurements of Boiling Burn-Out
- Stabilization Techniques for Ramp-Type Side Inlets at Supersonic Speeds
- Preliminary Results From Flight Measurements in Gradual-Turn Maneuvers of the Wing Loads and the Distribution of Load Among the Components of a Boeing B-47A Airplane
- Preliminary Results of an Investigation at Transonic Speeds to Determine the Effects of a Heated Propulsive Jet on the Drag Characteristics of a Related Series of Afterbodies
- Theoretical and Experimental Investigation of the Effect of Yaw on Heat Transfer to Circular Cylinders in Hypersonic Flow
- Transport of Radioactivity by Liquid Sodium in a Stainless Steel Circulation System
- Transonic Flutter Investigation of a Fighter-Airplane Wing Model and Comparison With a Systematic Plan-Form Series
- The Unsteady Normal-Force Characteristics of Selected NACA Profiles at High Subsonic Mach Numbers
- Turbulent Convective Heat-Transfer Coefficients Measured From Flight Tests of Four Research Models (NACA RM-10) at Mach Numbers From 1.0 to 3.6
- Rotating-Stall and Rotor-Blade-Vibration Survey of a 13-Stage Axial-Flow Compressor in a Turbojet Engine
- Some Recent Experimental Data on Three-Dimensional Oscillating Air Forces
- Theoretical Investigation of Laminar Heat Transfer on Yawed Infinite Cylinders in Supersonic Flow and a Comparison With Experimental Data