Browse TRAIL Inventories

Investigation of a Systematic Group of NACA 1-Series Cowling With and Without Spinners

Some Flight Measurements of Pressure-Distribution and Boundary-Layer Characteristics in the Presence of Shock

General handling-qualities results obtained during acceptance flight tests of the Bell XS-1 airplane

Theoretical analysis of the motions of an aircraft stabilized in roll by a displacement-response, flicker-type automatic pilot

Factors Affecting Lateral Stability and Controllability

Limited measurements of static longitudinal stability in flight of Douglas D-558-1 airplane (BuAero No. 37971)

Aerodynamic Characteristics of a Number of Modified NACA Four-Digit-Series Airfoil Sections

Aerodynamic Properties of Slender Wing-Body Combinations at Subsonic, Transonic, and Supersonic Speeds

Aerodynamics characteristics of 24 NACA 16-series airfoils at Mach numbers between 0.3 and 0.8

Analysis and Preliminary Design of an Optical Instrument for the Measurement of Drop Size and Free-Water Content of Clouds

Analysis of accuracy of gas-filled bellows for sensing gas density

Full-Scale Investigation of the Blade Motion of the PV-2 Helicopter Rotor

Present status of research on boundary-layer control

Investigations at supersonic speeds of 22 triangular wings representing two airfoil sections for each of 11 apex angles

Preliminary investigation of a variable Mach number two-dimensional supersonic tunnel of fixed geometry

Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0 to 20 degrees at high subsonic speeds

Aerodynamic characteristics of a delta wing with leading edge swept back 45 degrees, aspect ratio 4, and NACA 65A006 airfoil section.Transonic-bump method

Investigation of the NACA-4-(3)(08)-03 two-blade propeller at forward Mach numbers to 0.925

Investigation of the NACA 4-(4)(06)-04 two-blade propeller at forward Mach numbers to 0.925

Aerodynamic characteristics of a wing with quarter-chord line swept back 35©�, aspect ratio 6, taper ratio 0.6, and NACA 65A006 airfoil section.Transonic-bump method

Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil section.Transonic-bump method

Effects of compressibility on lift and load characteristics of a tapered wing of NACA 64-210 airfoil sections up to a Mach number of 0.60

Investigation of spoiler ailerons for use as speed brakes or glide-path controls on two NACA 65-series wings equipped with full-span slotted flaps

An Investigation of a Full-Scale Model of the Republic XF-91 Airplane in the Ames 40- By 80-Foot Wind Tunnel: Pressure Data

Heat Transfer from High-Temperature Surfaces to Fluids III - Correlation of Heat-Transfer Data for Air Flowing in Silicon Carbide Tube with Rounded Entrance, Inside Diameter of 3/4 Inch, and Effective Length of 12 Inches

Landing Procedure in Model Ditching Tests of Bf 109

Systematic model researches on the stability limits of the DVL series of float designs

Calibration Tests of a Japanese Log Rodmeter

Calibration Tests of a German Log Rodmeter

Investigation of Stability and Control Characteristics of a 1/10-scale Model of a Canadian Tailless Glider in the Langley Free-flight Tunnel

Flight Test of the Aerojet 7KS-6000 T-27 Jato Rocket Motor

Performance of Axial-Flow Supersonic Compressor of the XJ55-FF-1 Turbojet Engine. IV - Analysis of Compressor Operation over a Range of Equivalent Tip Speeds from 801 to 1614 Feet Per Second

Performance of Axial-Flow Supersonic Compressor on XJ-55-FF-1 Turbojet Engine. I - Preliminary Performance of Compressor, 1, Preliminary Performance of Compressor

Performance of Axial-Flow Supersonic Compressor of XJ55-FF-1 Turbojet Engine, III, Over-All Performance of Compressor

Investigation of the Effect of Tip Tanks on the Wing Loading of a Republic F-84 Airplane in the Ames 40- by 80-foot Wind Tunnel

Heat Transfer from High-Temperature Surfaces to Fluids. III - Correlation of Heat-Transfer Data for Air Flowing in Silicon Carbide Tube with Rounded Entrance, Inside Diameter of 3/4 Inch, and Effective Length of 12 Inches, Part 3, Correlation of Heat-Transfer Data for Air Flowing in Silicon Carbide Tube with Rounded Entrance, Inside Diameter of 3/4 Inch, and Effective Length of 12 Inches

Effect of Air Cooling of Turbine Disk on Power and Efficiency of Turbine from Turbo Engineering Corporation TT13-18 Turbosupercharger.

Investigation of flow coefficient of circular, square, and elliptical orifices at high pressure ratios

Determination of rate, area, and distribution of impingement of of waterdrops on various airfoils from trajectories obtained on the differential analyzer

A review of instruments developed for the measurement of the meteorological factors conductive to aircraft icing

Investigation at low speeds of the effect of aspect ratio and sweep on rolling stability derivatives of untapered wings

Investigation of flow coefficient of circular, square, and elliptical orifices at high pressure ratios

High-lift and lateral control characteristics of an NACA 652-215 semispan wing equipped with plug and retractable ailerons and a full-span slotted flap

Influence of wing flexibility on force-time relation in shock strut following vertical landing impact

Method for evaluating from shadow or Schlieren photographs the pressure drag in two-dimensional or axially symmetrical flow phenomena with detached shock

The method of characteristics for the determination of supersonic flow over bodies of revolution at small angles of attack

Method of determining conditions of maximum efficiency of an independent turbine-propeller combination

Oxidation characteristics of molybdenum disulfide and effect of such oxidation on its role as a solid-film lubricant

Laminar mixing of a compressible fluid

Longitudinal flying qualities of several single-rotor helicopters in forward flight


Published Year

Subject

Author

‹‹ previous 1 2 ... 71 72 73 74 75 76 77 ... 83 84 next ››