Resource Type
Serial/Series Title
NACA Research Memorandums
148
Atomic Energy Commission Reports
34
Hanford Works Reports
14
University of California Radiation Laboratory Reports
11
HW (Series)
10
Oak Ridge National Laboratory Reports
10
NACA Technical Reports
8
BMI (Series)
7
Battelle Memorial Institute Reports
7
ORNL (Series)
6
31 More
Country
234 Matching Results
Results open in a new window/tab.
Pressure Distributions on the Blade Sections of the NACA 10-(0)(066)-03 Propeller Under Operating Conditions
The fifth report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(0)(066)-03 propeller.
Date:
May 18, 1950
Creator:
Steinberg, Seymour & Milling, Robert W.
Object Type:
Report
System:
The UNT Digital Library
Investigation of effect of span and spanwise location of plain and stepped spoiler ailerons on lateral control characteristics of a wing with leading edge swept back 51.3 degrees
Report presenting a wind-tunnel investigation at low speed to determine the lateral control characteristics of a 51.3 degree sweptback-wing model equipped with either plain or stepped spoiler ailerons with a fixed projection of 5-percent-wing chord and various spans and spanwise locations. The results indicated that spanwise rolling-effectiveness charts of flap-type ailerons can not be used to predict effectiveness of spoiler-type ailerons on swept wings. Results regarding the wing aerodynamic characteristics with spoiler ailerons retracted, wing aerodynamic characteristics with spoiler ailerons projected, and a comparison of spoiler-type and flap-type ailerons.
Date:
January 18, 1950
Creator:
Fischel, Jack & Hammond, Alexander D.
Object Type:
Report
System:
The UNT Digital Library
Ditching Tests With a 1/16-Size Model of the Navy XP2V-1 Airplane at the Langley Tank No. 2 Monorail
Report discussing tests using a model of the Navy XP2V-1 to study its performance when ditched. From Summary: "Various landing attitudes, speeds, and conditions of damage were simulated. The performance of the model was determined and recorded from visual observations, by recording time histories of the longitudinal decelerations, and by taking motion pictures of the ditchings."
Date:
May 18, 1950
Creator:
Fisher, Lloyd J. & Tarshis, Robert P.
Object Type:
Report
System:
The UNT Digital Library
Analytical investigation of flow and heat transfer in coolant passages of free-convection liquid-cooled turbines
From Introduction: "An analytical investigation of the problems arising in connection with this cooling method was conducted at the NACA Lewis laboratory and is presented herein. This analysis investigates: (1) the smallest diameter hole that can be made without endangering the circulation of the liquid, and (2) methods of improving the circulation in a small-diameter hole."
Date:
July 18, 1950
Creator:
Eckert, E. R. G. & Jackson, Thomas W.
Object Type:
Report
System:
The UNT Digital Library
Tabulated Pressure Coefficients and Aerodynamic Characteristics Measured on the Wing of the Bell X-1 Airplane in Level Flight at Mach Numbers From 0.79 to 1.00 and in a Pull-Up at a Mach Number of 0.96
"Tabulated pressure coefficients and aerodynamic characteristics are presented for six spanwise stations on the left wing of the Bell X-1 research airplane. The data were obtained in level flight at Mach numbers from 0.79 to 1.00 and in a pull-up to an airplane normal-force coefficient of 0.91 at a Mach number of approximately 0.96" (p. 1).
Date:
September 18, 1950
Creator:
Carner, H. Arthur & Payne, Mary M.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation at Mach Numbers From 0.8 to 1.4 to Determine the Zero-Lift Drag of Wings With 'M' and 'W' Plan Forms
Report presenting testing of the zero-lift drag of two wings, one with 45 degree sweepforward of the inboard panel and 45 degree sweepback of the outboard panel ("M" wing) and the other with a reverse sweep ("W" wing) at a range of Mach numbers. Both wings were found to have greater drag than a sweptback wing and less drag than a rectangular wing at transonic speeds. The differences were reduced at Mach numbers above 1.25.
Date:
September 18, 1950
Creator:
Katz, Ellis; Marley, Edward T. & Pepper, William B.
Object Type:
Report
System:
The UNT Digital Library
Evaluation of Centrifugal Compressor Performance With Water Injection
The effects of water injection on a compressor are presented. To determine the effects of varying water-air ratio, the compressor was operated at a constant equivalent impeller speed over a range of water-air ratios and weight flows. Operation over a range of weight flows at one water-air ratio and two inlet air temperatures was carried out to obtain an indication of the effects of varying inlet air temperature. Beyond a water-air ratio of 0.03 there was no increase in maximum air-weight flow, a negligible rise in peak total-pressure ratio, and a decrease in peak adiabatic efficiency. An increase in inlet air temperature resulted in an increase in the magnitude of evaporation. An analysis of data indicated that the magnitude of evaporation within the compressor impeller was small.
Date:
July 18, 1951
Creator:
Beede, William L.; Hamrick, Joseph T. & Withee, Joseph R., Jr.
Object Type:
Report
System:
The UNT Digital Library
Control effectiveness and hinge-moment characteristics at low-speed of large-chord, horn-balanced, flap-type controls on a triangular wing of aspect ratio 2
Report presenting an investigation of large-chord flap-type controls with sweptback hinge lines and with various sizes and shapes of horn balances on a triangular wing of aspect ratio 2. Changes in the following elements were investigated: shielding of the horn balance, percentage of horn balance, trailing-edge thickness, flap nose seal, contour of the horn balance, and Reynolds number.
Date:
August 18, 1952
Creator:
Dods, Jules B., Jr.
Object Type:
Report
System:
The UNT Digital Library
Transonic aerodynamic characteristics of three thin triangular wings and a trapezoidal wing, all of low aspect ratio
Report presenting an investigation in the high-speed wind tunnel to determine the aerodynamic characteristics of three triangular wings and a trapezoidal wing through the transonic speed range by use of the bump technique. Data was obtained over a range of Mach and Reynolds numbers. Results regarding the lift, drag, pitching moment, and lift-drag ratio of the various wings are provided.
Date:
July 18, 1952
Creator:
Emerson, Horace F. & Gale, Bernard M.
Object Type:
Report
System:
The UNT Digital Library
Two-dimensional chord-wise load distributions at transonic speeds
Report presenting testing on the NACA 16-009 airfoil and on eight airfoils of the NACA 6A series, which shows that the chordwise loading due to lift at a Mach number of 1.0 is insignificantly affected by thickness distribution within the range of airfoil shapes presented and only slightly affected by thickness. Results regarding the experimental loading on symmetrical airfoils, method of estimating pressure distribution, experimental loadings on cambered airfoils, and scope of method are provided.
Date:
February 18, 1952
Creator:
Lindsey, Walter F. & Dick, Richard S.
Object Type:
Report
System:
The UNT Digital Library
Flame velocities over a wide composition range for pentane-air, ethylene-air, and propyne-air flames
Fundamental flame velocities are reported for pentane air, ethylene-air, and propylene-air mixtures for the concentration range 60 to 130 percent of stoichiometric. A form of the Tanford and Pease equation, which includes a small constant velocity term independent of diffusion, will predict the observed changes in flame velocity.
Date:
October 18, 1951
Creator:
Simon, Dorothy M. & Wong, Edgar L.
Object Type:
Report
System:
The UNT Digital Library
A comparison of the experimental and theoretical loading over triangular wings in sideslip at supersonic speeds
The results of an experimental investigation of the load distribution over two triangular wings in sideslip at Mach numbers from 1.20 to 1.79 are presented and compared with theory. The two wings tested have identical plan form, 45 degrees sweepback of the leading edge, and an aspect ratio of 4.0. One model was composed of round-nose airfoil sections and the other of sharp-nose, biconvex sections. For both wings the maximum thickness of streamwise sections was 6 percent and was located at the 30-percent chord.
Date:
May 18, 1951
Creator:
Boyd, John W.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Investigation of a Submerged Inlet and a Nose Inlet in the Transonic Flight Range With Free-Fall Models
Memorandum presenting an NACA submerged inlet and an NACA series I nose inlet installed in bodies of 12.4 fineness ratio to determine the drag and pressure-recovery characteristics of each body-inlet configuration. The tests were conducted with large-scale free-fall models released at an altitude of 40,000 feet, for mass-flow ratios of about 0.4 and 0.7 over a Mach number range of about 0.70 to 1.10. Results regarding drag and ram-recovery ratios are provided.
Date:
June 18, 1951
Creator:
Selna, James
Object Type:
Report
System:
The UNT Digital Library
The Forces and Pressure Distribution at Subsonic Speeds on a Cambered and Twisted Wing Having 45 Degrees of Sweepback and Aspect Ratio of 3 and a Taper Ratio of 0.5
Memorandum presenting an investigation conducted to determine the effects of scale and compressibility on the forces, moments, and pressure distribution on a cambered and twisted wing with an aspect ratio of 3.0 and a taper ratio of 0.5. Lift, drag, and pitching-moment data and the chordwise distribution of static pressure at seven spanwise stations are presented for specified Mach and Reynolds numbers. In order to determine the effects of camber and twist, the force, moment, and pressure data are compared with the data for an uncambered and untwisted wing of the same plan form.
Date:
July 18, 1952
Creator:
Boltz, Frederick W. & Kolbe, Carl D.
Object Type:
Report
System:
The UNT Digital Library
Analytical procedures for rapid selection of coolant passage configurations for air-cooled turbine rotor blades and for evaluation of heat-transfer, strength, and pressure-loss characteristics
Report presenting a method based on geometric factors of the coolant passage was evolved for the rapid selection and evaluation of coolant passage configurations for air-cooled turbine rotor blades. The most promising coolant passage configurations are analyzed to obtain absolute values of the required cooling-air weight flow, pressure loss, and strength characteristics.
Date:
September 18, 1952
Creator:
Ziemer, Robert R. & Slone, Henry O.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Survey of Boundary-Layer Development at a Nominal Mach Number of 5.5
Memorandum presenting a measurement of the mean skin-friction coefficients on a flat-plate model, with and without initial roughness, and on a wind tunnel wall were measured at a nominal Mach number of 5.5 over a range of Reynolds numbers.
Date:
June 18, 1952
Creator:
Bloom, Harold L.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Blade Failures in a J34, Eleven-Stage Axial-Flow Compressor
Report presenting a vibrational survey conducted during normal operation of a production eleven-stage axial-flow compressor powered as part of a complete turbojet engine. After serious third-stage vibration was detected, an investigation was conducted to study and eliminate the vibration with several component configurations. The vibrational source was determined to be an aerodynamic phenomenon related to a stall, but a new inlet-guide-vane assembly with a 4-percent increase in inlet area eliminated the vibration and increased the engine thrust 4 percent.
Date:
May 18, 1953
Creator:
Calvert, Howard F.; Meyer, André J., Jr. & Morse, C. Robert
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics extended to high angles of attack at transonic speeds of a small-scale 0 degree sweep wing, 45 degree sweptback wing, and 60 degree delta wing
Report presenting an investigation of a series of wings of various plan forms in the high-velocity field of the side-wall reflection plate of the 7- by 10-foot tunnel at a range of angles of attack and Mach numbers. The results indicated that the maximum lift coefficients obtainable increased with increase in sweep angle and decreased with Mach number at the lower subsonic Mach numbers.
Date:
November 18, 1952
Creator:
Wiley, Harleth G.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness at supersonic speeds of a 30-percent chord, 50-percent semispan elevon as a lateral control device
Report presenting the effectiveness of a 50-percent-semispan, constant-percent-chord elevon, and of upper-space spoilers as lateral control surfaces for a wing-fuselage combination with a wing swept back 63 degrees over a range of Mach numbers. For the elevon, results indicated that only about half of the predicted rolling-moment effectiveness was realized. The spoilers were found to be inferior to the elevons for lateral control because of a rapid loss of effectivness above an angle of attack of 4 degrees.
Date:
January 18, 1951
Creator:
Olson, Robert N. & Mead, Merrill H.
Object Type:
Report
System:
The UNT Digital Library
NACA research on combustors for aircraft gas turbines 1: effects of operating variables on steady-state performance
Some of the systematic research conducted by the NACA on aircraft gas-turbine combustors is reviewed. Trends depicting the effect of inlet-air pressure, temperature, and velocity and fuel-air ratio on performance characteristics, such as combustion efficiency, maximum temperature rise attainable, pressure loss, and combustor-outlet temperature distribution are described for a variety of turbojet combustors of the liquid-fuel type. These trends are further discussed as effects significant to the turbojet engine, such as altitude operational limits, specific fuel consumption, thrust, acceleration, and turbine life.
Date:
October 18, 1950
Creator:
Olson, Walter T. & Childs, J. Howard
Object Type:
Report
System:
The UNT Digital Library
Stability and control characteristics of a 1/4-scale Bell X-5 airplane model in the landing configuration
Report presenting an investigation of the static stability and control characteristics of a scale model of a preliminary Bell X-5 airplane design in the landing configuration with and without dive brakes. Results regarding the effects of slats, flaps, landing gear, gear doors, dive brakes and gap at the wing root are provided.
Date:
December 18, 1950
Creator:
Becht, Robert E.
Object Type:
Report
System:
The UNT Digital Library
Investigation of losses in the XJ35-A-23 two-stage turbine
Report presenting an investigation of the stage work distribution and losses through the turbine at design conditions of the XJ35-A-23 two-stage turbine. The investigation showed that the poor performance was primarily due to large whirl velocities at the turbine exit, choking in the second-stage rotor, and a choking condition upstream of the physical blade throat. If these conditions are eliminated, satisfactory two-stage turbine performance can be obtained.
Date:
August 18, 1952
Creator:
Rebeske, John J., Jr. & Forrette, Robert E.
Object Type:
Report
System:
The UNT Digital Library
Preliminary investigation of the drag characteristics of the NACA RM-10 missile at Mach numbers of 1.40 and 1.59 in the Langley 4- by 4-foot tunnel
Report presenting testing of a parabolic body of revolution in the 4- by 4-foot supersonic tunnel at two Mach numbers. The investigation included the effects of Reynolds number, fins, internal contour of body base, and two support systems on body pressure and force drag at an angle of attack of 0 degrees.
Date:
April 18, 1952
Creator:
Hasel, Lowell E.; Sinclair, Archibald R. & Hamilton, Clyde V.
Object Type:
Report
System:
The UNT Digital Library
Effects of spanwise thickness variation on the transonic aerodynamic characteristics of wings having 35 degrees of sweepback, aspect ratio 4, and taper ratio 0.60
Report presenting an investigation in the high speed 7- by 10-foot tunnel to determine the effects of a spanwise variation in thickness ratio on the aerodynamic characteristics of a wing with a plan form identical to that of a constant-percent thickness-ratio wing program. The wing with thickness variation had 35 degrees of sweepback, aspect ratio 4, and taper ratio of 0.60 with airfoil section tapered from an NACA 65A006 section at the root chord to an NACA 65A002 section at the tip chord. Results regarding the lift characteristics, drag characteristics, and pitching-moment characteristics are provided.
Date:
September 18, 1951
Creator:
Morrison, William D., Jr. & Fournier, Paul G.
Object Type:
Report
System:
The UNT Digital Library