Resource Type
Serial/Series Title
NACA Research Memorandums
451
NACA Technical Notes
368
NACA Technical Memorandums
125
NACA Wartime Reports
111
NACA Technical Reports
88
NACA Advanced Restricted Reports
47
NACA Memorandum Reports
31
NACA Advanced Confidential Reports
18
NACA Aircraft Circulars
18
NACA Restricted Bulletins
12
4 More
Country
States
1,172 Matching Results
Results open in a new window/tab.
Studies of the speed stability of a tandem helicopter in forward flight
Flight-test measurements, related analytical studies, and corresponding pilots' opinions of the speed stability of tandem-rotor helicopter are presented. An undesirable instability, evidenced by rearward stick motion with increasing forward speed at constant power, is indicated to be caused by variations with speed of the front-rotor downwash at the rear rotor. An analytical expression for predicting changes in speed stability caused by changes in rotor geometry is derived and constants for use with the analytical expression are presented in chart form. Means for improving stability with speed are studied both analytically and experimentally. The test results also give some information as to the flow conditions at the rear rotor.
Date:
June 4, 1953
Creator:
Tapscott, Robert J. & Amer, Kenneth B.
Object Type:
Report
System:
The UNT Digital Library
A correlation of loadings and afterbody length-beam ratios of various flying-boat hulls
"The gross weight, beam, and afterbody length of 12 contemporary flying boats and amphibians with pointed afterbodies are tabulated and correlated. For most of the hulls considered, the afterbody length-beam ratios are shown to be directly proportion to the gross-load coefficients" (p. 1).
Date:
June 1946
Creator:
Parkinson, John B.
Object Type:
Report
System:
The UNT Digital Library
A Study of the Tightness and Flushness of Machine-Countersunk Rivets for Aircraft
Bulletin presenting the results of an investigation to determine possible improvements in the tightness and the flushness of machine-countersunk rivets. Specimens used in the study were simple lap joints made by different riveting methods. The results indicate that a comparison of the quality of machine-countersunk riveted joints on the basis of maximum load alone is not justified.
Date:
June 1942
Creator:
Lundquist, Eugene E. & Gottlieb, Robert
Object Type:
Report
System:
The UNT Digital Library
Full-Scale Evaluation of Some Flameholder Design Concepts for High-Inlet-Velocity Afterburners
Memorandum presenting an investigation of a full-scale afterburner with high burner-inlet velocity conducted to determine burner performance with several variations in burner design. Variables receiving particular attention were flameholder design and burner length. Results regarding diffuser performance, performance of the reference two-V-gutter flameholder, designs to improve combustion for high-velocity conditions, and operational characteristics are provided.
Date:
June 28, 1956
Creator:
Prince, William R.; Velie, Wallace W. & Braithwaite, Willis M.
Object Type:
Report
System:
The UNT Digital Library
Analytical Investigation of Fuel-Cooled Turbine Blades With Return-Flow Type of Finned Coolant Passages
Memorandum presenting an investigation of coolant-flow rates for a turbine rotor blade with return-flow type of coolant-passage configuration formed by fins within a capped blade shell with both hydrogen and methane fuels as coolants. Results regarding spanwise blade and coolant temperature distributions, effects of coolant inlet temperature on hydrogen-coolant-flow requirements, comparison of return-flow-blade coolant requirements, effect of fin thickness and fin height, comparison of hydrogen and methane as coolants, and feasibility of fuel-cooled turbines are provided.
Date:
June 26, 1957
Creator:
Nachtigall, Alfred J. & Slone, Henry O.
Object Type:
Report
System:
The UNT Digital Library
Cascade Investigation of Cooling Characteristics of a Castfinned Air-Cooled Turbine Blade for Use in a Turboprop Engine
Memorandum presenting an experimental investigation of the cooling characteristics of a small air-cooled turbine blade for use in a turboprop engine in a static cascade facility. Three test blades were studiued at three combustion-gas temperatures. Results regarding gas-flow conditions in cascade test section, correlation of temperature data, and application of correlated data to the typical engine are provided.
Date:
June 12, 1957
Creator:
Stepka, Francis S.; Richards, Hadley T. & Hickel, Robert O.
Object Type:
Report
System:
The UNT Digital Library
Analyses for Turbojet Thrust Augmentation With Fuel-Rich Afterburning of Hydrogen, Diborane, and Hydrazine
Turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine was computed. Results regarding takeoff thrust augmentation and flight thrust augmentation are provided.
Date:
June 18, 1957
Creator:
Morris, James F.
Object Type:
Report
System:
The UNT Digital Library
Effects of Wing-Fuselage Flow Fields on Missile Loads at Subsonic Speeds
"The flow-field characteristics around a swept-wing airplane model at low subsonic speed are described, and the loads induced on a typical missile model while operating within these flow fields are presented. In addition, theoretical flow fields are compared with experiment and are used in first-order estimations of the resulting induced missile loads" (p. 1).
Date:
June 27, 1955
Creator:
Alford, William J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Aerodynamic Characteristics of an Airplane Configuration Having Tail Surfaces Outboard of the Wing Tips at Mach Numbers of 2.30, 2.97, and 3.51
Memorandum presenting an investigation to determine the drag, static longitudinal and lateral stability, and longitudinal trim characteristics of an airplane configuration with tail surfaces outboard of the wing tips. Included in the basic data are some effects of Reynolds number, engine pack, and wing twist combined with toe-out of the vertical tails.
Date:
June 23, 1958
Creator:
Church, James D.; Hayes, William C., Jr. & Sleeman, William C., Jr.
Object Type:
Report
System:
The UNT Digital Library
Investigation of High-Angle-of-Attack Performance of a 14 Deg Ramp-Type Inlet in Various Circumferential Body Locations: Mach Number Range 1.5 to 2.0
Memorandum presenting an investigation to determine the internal flow performance of a fixed 14 degree ramp inlet from zero to 20 degrees angle of attack conducted at three free-stream Mach numbers. The inlet was mounted in three circumferential fuselage locations and utilized inlet throat and fuselage boundary-layer removal.
Date:
June 26, 1957
Creator:
Mitchell, Glenn A. & Chiccine, Bruce G.
Object Type:
Report
System:
The UNT Digital Library
Low-Speed Roll Effectiveness of a Differentially Deflected Horizontal-Tail Surface on a 42 Degree Swept-Wing Model
Memorandum presenting an investigation to determine the roll effectiveness of a differentially deflected horizontal tail of a 42 degree swept-wing model. The model was tested through an angle-of-attack range of 0 degrees through the stall in the clean and landing configurations with the horizontal tail in a low position. Results regarding the longitudinal characteristics and lateral characteristics are provided.
Date:
June 19, 1956
Creator:
Boisseau, Peter C.
Object Type:
Report
System:
The UNT Digital Library
A Low-Pressure-Loss Short Afterburner for Sea-Level Thrust Augmentation
Memorandum presenting an investigation of the problems associated with the design of a low-pressure-loss, short afterburner for sea-level thrust augmentation in a static, sea-level test stand. Results regarding diffuser pressure losses, afterburner pressure losses, and afterburner performance are provided.
Date:
June 7, 1955
Creator:
Ciepluch, Carl C.; Velie, Wallace W. & Burley, Richard R.
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of the Transonic and Supersonic Flutter Characteristics of the Upper and Lower Vertical Tails of an Air-to-Ground Missile
"Flutter models of the upper and lower vertical tails of an air-to-ground missile have been tested in the Mach number range from 0.5 to 3.0. It was found that the upper surface exhibited more or less conventional flutter behavior throughout the Mach number range, whereas the lower surface experienced a sudden change in flutter mode at a Mach number of about 1.18. This change in flutter mode was accompanied by a decrease of about 50 percent in the density required for flutter to occur" (p. 1).
Date:
June 5, 1957
Creator:
Hanson, Perry W. & Rainey, A. Gerald
Object Type:
Report
System:
The UNT Digital Library
Performance of JP-4 Fuel With Fluorine-Oxygen Mixtures in 1000-Pound-Thrust Rocket Engines
Memorandum presenting seven injectors of four different types that were tested for use with JP-4-oxygen-fluorine propellant combinations. By using the best of the injectors, high characteristic velocities were obtained over the complete range of 0- to 70-percent fluorine in the oxidant. Results regarding injector performance, heat rejection, injector with triplet-jet elements in skewed array, and fluorine addition are provided.
Date:
June 11, 1958
Creator:
Nored, Donald L. & Douglass, Howard W.
Object Type:
Report
System:
The UNT Digital Library
A comparison of three spinner-diffuser designs in an NACA D(sub S) cowling for the Pratt & Whitney R-2800 engine
Report presenting testing to determine which of three spinner-diffuser designs on an NACA cowling was the most effective in cooling a Pratt & Whitney R-2800 engine installation. The results of pressure-distribution studies in front of and behind each bank of cylinders are presented for a wide range of propeller-operating conditions.
Date:
June 1944
Creator:
Habel, Louis W. & Korycinski, Peter F.
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel vibration tests of a four-blade single rotating pusher propeller
Report presenting vibration tests of a four-blade single-rotating propeller operating in a simulated pusher condition performed because the combination of wake and downwash behind a wing might provide serious excitation for reactionless vibrations of propellers with four or more blades. Measurements of propeller vibratory stress were made for various airspeeds, engine speeds, and engine powers.
Date:
June 1943
Creator:
Miller, Mason F.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of Carburetor Air Scoops for the XTB2D-1 Airplane with Emphasis on Means for Bypassing the Boundary Layer
Report presenting an investigation of carburetor-air scoops designed for the XTB2D-1 airplane in the NACA propeller-research tunnel. The purpose of the investigation was to determine the performance of several scoops and to make modifications necessary to improve the pressure recovery without adversely affecting the drag of the airplane. The investigation included tests of nine carburetor-air scoops with numerous boundary-layer-bypass and ducting modifications, the original engine cowl, and two canopies.
Date:
June 1944
Creator:
Nichols, Mark R.; Keith, Arvid L., Jr. & Boswinkle, Robert W., Jr.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamics of the carburetor air scoop and the engine cowling of a single-engine torpedo-bomber-type airplane
From Introduction: "An investigation of the power-plant installation of a single-engine torpedo-bomber-type airplane has been conducted in the NACA Cleveland altitude wind tunnel at the request of the Bureau of Aeronautics, Navy Department. A similar investigation was previously conducted on a three-tenths scale mock-up of the forward portion of the fuselage of this airplane in the Langley 20-foot tunnel. (See reference 1)."
Date:
June 1946
Creator:
Palter, Herman
Object Type:
Report
System:
The UNT Digital Library
Investigation of a Ram-Jet-Powered Helicopter Rotor on the Langley Helicopter Test Tower
Report discussing tests on a helicopter rotor powered by ram-jet engines located at the rotor blade tips. Information about the basic hovering characteristics of the rotor and the propulsive characteristics of the ram-jet engine were obtained over a range of speeds and fuel rates. Results were also obtained in the power-off condition and with the engines removed.
Date:
June 3, 1953
Creator:
Carpenter, Paul J. & Radin, Edward J.
Object Type:
Report
System:
The UNT Digital Library
The Effect of Liquid and Ice Particles on the Erosion of a Supercharger-Inlet Cover and Diffuser Vanes
Report discussing the results of accelerated erosion tests to determine the separate effects of the passage of fuel, water, and ice particles through a supercharger. Recommendations for preventing erosion are provided, including materials choice and joint design.
Date:
June 1946
Creator:
Rollin, Vern G.
Object Type:
Report
System:
The UNT Digital Library
Characteristics of a Hydraulic Control Determined from Transient Data Obtained with a Turbojet Engine at Altitude
Memorandum presenting characteristics of a hydraulic control as determined by analyzing transient data obtained with a turbojet engine operating in the altitude wind tunnel. The excellent overall performance of the speed control is attributed to the elimination of large lags in the control system, thereby permitting the use of relatively high loop gains while still maintaining satisfactory damping in transients. Some information regarding the frequency-response analysis of speed control, simulation of speed control, and acceleration control are provided.
Date:
June 16, 1954
Creator:
Vasu, George; Hinde, William L. & Craig, R. T.
Object Type:
Report
System:
The UNT Digital Library
Recommended Test Procedure for Aircraft Engine Turbosupercharger Power Plants
Report describes a procedure for instrumenting, testing, and presenting the overall characteristics of any engine turbosupercharger installation. The preflight analysis of the system, required testing, importance of accurate data recording, measurements to record, methods of measuring, and presentation of results are also included.
Date:
June 1943
Creator:
NACA Subcommittee on Recovery of Power from Exhaust Gas
Object Type:
Report
System:
The UNT Digital Library
Effect of various carburetor throttle settings on the flow characteristics at the outlet of a supercharger inlet elbow
Report presenting an investigation to determine the effect of varying the carburetor throttle settings on the flow characteristics at the outlet of the supercharger inlet elbow. Air flow tests were made at several carburetor throttle settings ranging from open to closed. Results regarding distortion and turbulence are provided.
Date:
June 1945
Creator:
Moses, Jason J.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Statistical Nature of Fatigue Properties
Note presenting an experimental program to study the subject of metal fatigue and to determine and evaluate the fundamental factors which influence the behavior. The statistics of the fatigue-fracture curves and endurance limits were determined for a variety of metals and the effects of some metallurgical factors on the statistical nature of fatigue properties were shown.
Date:
June 1952
Creator:
Epremian, E. & Mehl, R. F.
Object Type:
Report
System:
The UNT Digital Library