Resource Type
Serial/Series Title
NACA Research Memorandums
181
Atomic Energy Commission Reports
53
Hanford Works Reports
28
NACA Technical Reports
22
HW (Series)
20
University of California Radiation Laboratory Reports
19
Oak Ridge National Laboratory Reports
18
ORNL (Series)
11
UCRL (Series)
8
AEC research and development report
7
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362 Matching Results
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Some pressure-distribution measurements on a swept-wing at transonic speeds by the NACA wing-flow method
Report presenting results of chordwise pressure-distribution measurements on a 45 degree sweptback wing at transonic speeds. The two stations for measuring were located at the 18 percent chord from the root and the 87 percent chord. The changes in pressure distribution with Mach number did not indicate any appreciable net loss in section lift, but did indicate large increases in the section drag and diving moment.
Date:
June 6, 1947
Creator:
Johnston, J. Ford & Danforth, Edward C. B.
Object Type:
Report
System:
The UNT Digital Library
Location of Detached Shock Wave in Front of a Body Moving at Supersonic Speeds
"It is shown that for velocities slightly in excess of sonic, the position of detached shock wave located in front of a given body at zero angle of attack may be estimated theoretically to a reasonable degree of accuracy. In case of bodies of revolution the result was simple, but for two-dimensional bodies, pressure coefficient varies with Mach number, and slight difficulty appears. Theory developed compares favorably with available experimental data" (p. 1).
Date:
May 6, 1947
Creator:
Laitone, Edmund V. & Pardee, Otway O'M.
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation of thrust augmentation of a turbojet engine at zero ram by means of tail-pipe burning
Report presenting an investigation of the performance of a turbojet engine equipped with a tail-pipe burner at zero ram over a range of rotor speeds and tail-pipe-burner fuel flows. A thrust augmentation of 40 percent was obtained at zero ram for a tail-pipe-burner fuel-air ratio of 0.043 or a total fuel-air ratio of 0.056. Results with an engine with standard tail pipe, engine with tail pipe burner and no afterburning, and engine with tail pipe burner and afterburning are provided.
Date:
January 6, 1947
Creator:
Lundin, Bruce T.; Dowman, Harry W. & Gabriel, David S.
Object Type:
Report
System:
The UNT Digital Library
An Analysis of Airspeeds Attained by a Douglas DC-4 Airplane in Commercial Operations During the Early Months of 1947
Report presenting airspeed and altitude data for nonscheduled cargo operations of a Douglas DC-4 airplane between Seattle, Washington and Alaska during February and March of 1947 to determine the probability of reaching or exceeding given values of airspeed and Mach number. The total probability of exceeding a placard never-exceed speed of 266 mph depends primarily on exceeding the speed in descent. The probability was found to be about once in 100 hours of descent or once in 1000 hours of general flying time.
Date:
October 6, 1949
Creator:
Steiner, Roy
Object Type:
Report
System:
The UNT Digital Library
Flutter Investigation in the Transonic Range of Six Airfoils Attached to Three Freely Falling Bodies
Report presenting testing of six flutter wings, two swept 45 degrees and four unswept, attached to three freely falling bodies. Flutter frequency and phasing were recorded.
Date:
May 6, 1948
Creator:
Clevenson, S. A. & Lauten, William T., Jr.
Object Type:
Report
System:
The UNT Digital Library
Flight-Test Evaluation of the Longitudinal Stability and Control Characteristics of 0.5-Scale Models of the Lark Pilotless-Aircraft Configuration
Report presenting flight tests to determine the longitudinal stability and control characteristics of models of the Lark pilotless aircraft. Testing included the standard configuration with the horizontal wing flaps deflected 0 degrees, 15 degrees, and 60 degrees, and a test with the tail surfaces in line with the wings with the wing flaps not deflected. Results regarding time-history records, drag, longitudinal stability, and control effectiveness are provided.
Date:
February 6, 1948
Creator:
Stone, David G.
Object Type:
Report
System:
The UNT Digital Library
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
The third investigation in a series to determine the fundamental characteristics of trailing-edge controls at transonic speeds. This particular report uses a 35 degree sweptback untapered airfoil model with an aspect ratio of 3 and a flap with a bevelled trailing edge with a trailing-edge angle of 23 degrees. Results regarding lift, pitching-moment, and hinge-moment characteristics are provided.
Date:
January 6, 1950
Creator:
Johnson, Harold I. & Brown, B. Porter
Object Type:
Report
System:
The UNT Digital Library
An Empirical Method for Estimating Trailing-Edge Loads at Transonic Speeds
Memorandum presenting an analysis of selected experimental pressure-distribution data at transonic speeds for the purpose of deriving an empirical method which may be used for estimating the trailing-edge loads and bending moments at the design stage. The trailing-edge normal-force and bending-moment coefficients calculated by the derived method follow the general trend of the experimental data and appear to be a guide where specifically applicable chordwise pressure-distribution data at transonic speeds are not available.
Date:
October 6, 1949
Creator:
Skopinski, T. H.
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation of thrust augmentation of 4000-pound-thrust axial-flow-type turbojet engine by interstage injection of water-alcohol mixtures in compressor
Report presenting an experimental investigation of thrust augmentation of a 4000-pound-thrust axial-flow-type turbojet engine by interstage injection of water-alcohol mixtures into the compressor at sea-level, zero-ram conditions. the number, size, and arrangement of interstage nozzles were varied to produce a satisfactory augmentation system of minimum complication. Results regarding the unaugmented performance with and without interstage-injection nozzles, augmented performance with three-stage system, augmented performance with other injection systems, temperature surveys, and engine operation are provided.
Date:
April 6, 1950
Creator:
Povolny, John H.; Useller, James W. & Chelko, Louis J.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section: transonic-bump method
From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuelage configurations employing a wing with the quarter-chord line swept back 60^o, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the free stream."
Date:
September 6, 1949
Creator:
King, Thomas J., Jr. & Myers, Boyd C., II
Object Type:
Report
System:
The UNT Digital Library
Temperature survey of the wake of two closely located parallel jets
Report presenting a temperature survey made in the wake of two closely located parallel jets emerging into the atmosphere from two types of twin convergent nozzles. Results regarding the twin unshrouded nozzles and twin nozzles with twin geometry-simulated shrouds are provided.
Date:
February 6, 1950
Creator:
Sloop, John L. & Morrell, Gerald
Object Type:
Report
System:
The UNT Digital Library
An Investigation of the Low-Speed Characteristics of Two Sharp-Edge Supersonic Inlets Designed for Essentially External Supersonic Compression
Report presenting an investigation of two sharp-edge annular inlets with conical central bodies at low airspeeds in the propeller research tunnel to obtain information concerning the surface-pressure, drag, and pressure-recovery characteristics of the inlets at subsonic flight. Results regarding the nose and inner surface of the diffuser, inlet lips, minimum surface pressures and critical Mach numbers, pressure surveys in inlets, and pressure surveys in diffusers are provided.
Date:
June 6, 1947
Creator:
Dennard, John S.
Object Type:
Report
System:
The UNT Digital Library
Comparative Drag Measurements at Transonic Speeds of an NACA 65-006 Airfoil and a Symmetrical Circular-Arc Airfoil
Report presenting measurements made at transonic speeds by the freely-falling-body method to compare the drag of a rectangular plan-form airfoil of aspect ratio 7.6 with an NACA 65-006 airfoil section. Results regarding the velocity measurements, base-pressure measurements, and airfoil drag measurements are provided.
Date:
March 6, 1947
Creator:
Thompson, Jim Rogers & Marschner, Bernard W.
Object Type:
Report
System:
The UNT Digital Library
Pressure-Distribution Data for the NACA 64(Sub 1)-012 and 64(Sub 1)A012 Airfoils at High Subsonic Mach Numbers
"Pressure-distribution data of the NACA 64(sub 1)-012 and 64(sub 1)A012 airfoils have been analyzed to determine the effects of increasing the trailing-edge angle from 9 to 14 degrees. The primary effect of increasing the trailing-edge angle was to decrease the loading over the rear portion of the airfoil under lifting conditions. The differences in trailing-edge load increased with Mach number and lift coefficient" (p. 1).
Date:
May 6, 1949
Creator:
Humphreys, Milton D.
Object Type:
Report
System:
The UNT Digital Library
Properties of certain intermetallics as related to elevated-temperature applications 1: molybdenum disilicide
Report presenting a method for the preparation and purification of the intermetallic molybdenum desilicide was developed and its properties were determined. Chemical properties were found to be highly inert, unattacked by boiling hydrochloric acid, sulfuric acid, or aqueous sodium hydroxide, slightly attacked by nitric acid, and dissolved by molten sodium hydroxide. Other mechanical properties of the material were also provided.
Date:
October 6, 1949
Creator:
Maxwell, W. A.
Object Type:
Report
System:
The UNT Digital Library
The Effect of Blade-Section Thickness Ratios on the Aerodynamic Characteristics of Related Full-Scale Propellers at Mach Numbers Up to 0.65
Report discussing an investigation of two full-scale NACA propellers at a range of blade angles and at speeds of up to 500 miles per hour. The results are compared to previous investigations of five NACA propellers to evaluate the effects of blade-section thickness ratios on propeller characteristics.
Date:
June 6, 1949
Creator:
Maynard, Julian D. & Steinberg, Seymour
Object Type:
Report
System:
The UNT Digital Library
Two-dimensional wind-tunnel investigation of a 6-percent-thick symmetrical circular-arc airfoil section with leading-edge and trailing-edge high-lift devices deflected in combination
Report presenting a two-dimensional wind-tunnel investigation of a 6-percent-thick symmetrical circular-arc airfoil with leading-edge and trailing-edge high-lift devices. The purpose of the investigation was to determine the effects on maximum section lift coefficient of different leading-edge slats and drooped-nose flaps when used in combination with a plain trailing-edge flap. Results regarding slat configuration, drooped-nose-flap configurations, and a comparison of slat and drooped-nose-flap configurations are provided.
Date:
September 6, 1949
Creator:
Nuber, Robert J. & Cheesman, Gail A.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Investigation at a Mach number of 1.53 to determine the effects of cambering and twisting the wing for uniform load at a lift coefficient of 0.25
Testing was performed at Mach number 1.53 with a wing-fuselage combination with a wing with 63 degrees leading-edge sweep, an aspect ratio of 3.46, and a taper ratio of 0.25. The wing had an NACA 64A005 thickness distribution parallel to the plane of symmetry and was cambered and twisted. Results regarding the comparison of lift, drag, and pitching-moment characteristics of WF-63c and WF-63, effects of sweep, and effects of Reynolds number are provided.
Date:
May 6, 1949
Creator:
Madden, Robert T.
Object Type:
Report
System:
The UNT Digital Library
Investigation of downwash and wake characteristics at a Mach number of 1.53 2: triangular wing
Report presenting the results of an experimental investigation of the downwash and wake characteristics behind a triangular plan-form wing in a supersonic stream. Measurements were made of the variation of downwash angle with angle of attack at several positions within the induced flow field. Results regarding the spanwise variation of the induced stream angle, rate of change of downwash at zero lift, variation of downwash with angle of attack, and wake are provided.
Date:
June 6, 1949
Creator:
Perkins, Edward W. & Canning, Thomas N.
Object Type:
Report
System:
The UNT Digital Library
Longitudinal Trim and Drag Characteristics of Rocket-Propelled Models Representing Two Airplane Configurations
Report discussing an investigation of the longitudinal trim and drag characteristics of two airplane configurations through the transonic speed range. One configuration had a thin straight wing and tail and one had a thicker 35 degree sweptback wing and a 46 degree sweptback tail on the same fuselage-fin arrangement. Information about the control effectiveness and stability and application to a full-scale airplane is also provided.
Date:
February 6, 1950
Creator:
Parks, James H. & Mitchell, Jesse L.
Object Type:
Report
System:
The UNT Digital Library
Stability and control characteristics at low speed of a 1/5-scale model of the Edo 142 hydro-ski research airplane
Report presenting an investigation in the 300 mph tunnel to determine the low-speed stability and control characteristics and the jet-engine duct-inlet pressure recovery characteristics of a model of the Edo 142 hydro-ski research airplane. Results regarding the longitudinal stability and control, stall-control devices, alighting gear, lateral stability, directional control, lateral control, and duct pressure recovery are provided.
Date:
August 6, 1951
Creator:
Riebe, John M.; MacLeod, Richard G. & Moseley, William C., Jr.
Object Type:
Report
System:
The UNT Digital Library
Dynamic Investigation of Turbine-Propeller Engine Under Altitude Conditions
Memorandum presenting an investigation of the dynamics of a turbine-propeller engine in the altitude wind tunnel employing the frequency-response technique for a range of pressure altitudes form 10,000 to 30,000 feet. The investigation showed that the dynamic responses generalized for pressure altitude over the range of frequencies investigated. Results regarding steady-state characteristics, the linearity investigation, and dynamic characteristics are provided.
Date:
December 6, 1950
Creator:
Krebs, Richard P.; Himmel, Seymour C.; Blivas, Darnold & Shames, Harold
Object Type:
Report
System:
The UNT Digital Library
Low-Speed Static Stability Characteristics of a Canard Model with a 45 Degree Sweptback Wing and a 60 Degree Triangular Horizontal Control Surface
Memorandum presenting an investigation of the low-speed static stability characteristics of a canard model with a 45 degree sweptback wing and a 60 degree triangular horizontal control surface. Results regarding longitudinal stability and control and lateral stability and control are provided.
Date:
September 6, 1950
Creator:
Draper, John W.
Object Type:
Report
System:
The UNT Digital Library
A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2: Wing-fuselage configuration having a wing of 0 degrees sweepback, aspect ratio 4.0,taper ratio 0.6, and NACA 65A006 ai
Report presenting an analysis of a series of wing-body combinations in the 8-foot high-speed tunnel. The paper presents the results of an investigation of a wing-fuselage combination with a wing of unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section. Results regarding force and moment characteristics and wake and downwash characteristics are provided.
Date:
March 6, 1951
Creator:
Cahn, Maurice S. & Bryan, Carroll R.
Object Type:
Report
System:
The UNT Digital Library