Search
Search U.S. government technical reports digitized or harvested by TRAIL.
Keyword Search
14045 results returnedSearch results
- Aerodynamic Characteristics of a 45 Degree Swept-Back Wing With Aspect Ratio of 3.5 and NACA 2S-50(05)-50(05) Airfoil Sections
- Measurements of Static and Total Pressure Throughout the Transonic Speed Range as Obtained from an Airspeed Head Mounted on a Freely Falling Body
- Comparative Drag Measurements at Transonic Speeds of 6-Percent-Thick Airfoils of Symmetrical Double-Wedge and Circular-Arc Sections From Tests by the NACA Wing-Flow Method
- Comparative Drag Measurements at Transonic Speeds of an NACA 65-006 Airfoil and a Symmetrical Circular-Arc Airfoil
- A Low-Speed Investigation of an Annular Transonic Air Inlet
- Investigation of High-Lift and Stall-Control Devices on a NACA 64-Series 42 Degree Sweptback Wing With and Without Fuselage
- A Method for Predicting the Stability in Roll of Automatically Controlled Aircraft Based on the Experimental Determination of the Characteristics of an Automatic Pilot
- Flight Investigation to Determine the Hinge Moments of a Beveled-Edge Aileron on a 45 Degree Sweptback Wing at Transonic and Low Supersonic Speeds
- Full-Scale Investigation of the Maximum Lift and Flow Characteristics of an Airplane Having Approximately Triangular Plan Form
- Location of Detached Shock Wave in Front of a Body Moving at Supersonic Speeds
- Longitudinal Stability and Control Characteristics of a Semispan Airplane Model With a Swept-Back Tail From Tests at Transonic Speeds by the NACA Wing-Flow Method
- Longitudinal Stability and Control of High-Speed Airplanes With Particular Reference to Dive Recovery
- Longitudinal Stability and Control Characteristics of an Airplane Model Having a 42.8 Degree Sweptback Circular-Arc Wing With Aspect Ratio 4.00, Taper Ratio 0.50, and Sweptback Tail Surfaces
- Low-Speed Characteristics in Pitch of a 42 Degree Sweptback Wing With Aspect Ratio 3.9 and Circular-Arc Airfoil Sections
- Measurements of Aerodynamic Characteristics of a 35 Degree Sweptback NACA 65-009 Airfoil Model With 1/4-Chord Plain Flap by the NACA Wing-Flow Method
- An Investigation of the Downwash at the Probable Tail Location Behind a High-Aspect-Ratio Wing in the Langley 8-Foot High-Speed Tunnel
- An Investigation of the Lateral-Control Characteristics of Spoilers on a High-Aspect-Ratio Wing of NACA 65-210 Section in the Langley 8-Foot High Speed Tunnel
- Investigation of the Loads on a Typical Bubble-Type Canopy
- An Investigation of the Low-Speed Characteristics of Two Sharp-Edge Supersonic Inlets Designed for Essentially External Supersonic Compression
- An Investigation of the Low-Speed Stability and Control Characteristics of Swept-Forward and Swept-Back Wing in the Ames 40- by 80-Foot Wind Tunnel
- An Analysis of Airspeeds and Mach Numbers Attained by Lockheed Constellation Airplanes in Transcontinental Operations During the Early Summer of 1946
- Increase in Stable-Air-Flow Operating Range of a Mixed-Flow Compressor by Means of a Surge Inhibitor
- Flight Tests to Determine the Effect of Taper on the Zero-Lift Drag of Wings at Low Supersonic Speeds
- Free-Flight Investigation of Control Effectiveness of Full-Span 0.2-Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Section Thickness and Wing Sweepback
- Free-Flight Investigation of Fullspan, 0.2 Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Wing Sweepback, Taper, Aspect Ratio, and Section-Thickness Ratio
- High-Speed Wind-Tunnel Investigation of the Lateral Control Characteristics of Plain Ailerons on a Wing with Various Amounts of Sweep
- Flight-Test Measurements of Aileron Control Surface Behavior at Super Critical Mach Numbers
- Flight Observations of Aileron Flutter at High Mach Numbers as Affected by Several Modifications
- Free-Fall Measurements at Transonic Velocities of the Drag of a Wing-Body Configuration Consisting of a 45 Degree Swept-Back Wing Mounted Forward of the Maximum Diameter on a Body of Fineness Ratio 12
- Force and Longitudinal Control Characteristics of a 1/16-Scale Model of the Bell XS-1 Transonic Research Airplane at High Mach Numbers
- Initial Test in the Transonic Range of Four Flutter Airfoils Attached to a Freely Falling Body
- An Investigation at Low Speed of a Large-Scale Triangular Wing of Aspect Ratio Two 2: The Effect of Airfoil Section Modifications and the Determination of the Wake Downwash
- Further investigation of NACA 4-(5)(08)-03 two-blade propeller at high forward speeds
- Results of preliminary flight investigation of aerodynamic characteristics of the NACA two-stage supersonic research model RM-1 stabilized in roll at transonic and supersonic velocities
- Results of flight tests at supersonic speeds to determine the effect of body nose fineness ratio on body and wing drag
- Some pressure-distribution measurements on a swept-wing at transonic speeds by the NACA wing-flow method
- Drag characteristics of rectangular and swept-back NACA 65-009 airfoils having various aspect ratios as determined by flight tests at supersonic speeds
- Drag characteristics of rectangular and swept-back NACA 65-009 airfoils having aspect ratios of 1.5 and 2.7 as determined by flight tests at supersonic speeds
- Two-dimensional wind-tunnel investigation at high Reynolds numbers of two symmetrical circular-arc airfoil sections with high-lift devices
- Tests of the landing on water of a model of a high-speed airplane - Langley tank model 229
- Comparison of the transonic drag characteristics of two wing-body combinations differing only in the location of the 45 degree sweptback wing
- Calculations of the Supersonic Wave Drag of Nonlifting Wings with Arbitrary Sweepback and Aspect Ratio: Wings Swept Behind the Mach Lines
- Lateral stability and control characteristics of an airplane model having 42.8 degree sweptback circular-arc wing with aspect ratio 4.00, taper ratio 0.50, and sweptback tail surfaces
- Canopy loads investigation for the F6F-3 airplane
- Investigation of Pressure Distribution over an Extended Leading-Edge Flap on a 42 Degrees Sweptback Wing
- Pressure-distribution measurements on a full-scale horizontal tail surface for a Mach number range of 0.20 to 0.70
- A method for predicting the stability in roll of automatically controlled aircraft based on the experimental determination of the characteristics of an automatic pilot
- Measurements of the effects of thickness ratio and aspect ratio on the drag of rectangular-plan-form airfoils at transonic speeds
- Preliminary investigation of spoiler lateral control on a 42 degree sweptback wing at transonic speeds
- Wind-tunnel development of optimum double-slotted-flap configurations for seven thin NACA airfoil sections