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Serial/Series Title
NACA Research Memorandums
190
Atomic Energy Commission Reports
61
NACA Technical Reports
22
Oak Ridge National Laboratory Reports
16
BNL (Series)
12
Brookhaven National Laboratory Reports
12
University of California Radiation Laboratory Reports
9
AEC research and development report
8
Hanford Works Reports
8
ORNL (Series)
7
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337 Matching Results
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The Origin of Aerodynamic Instability of Supersonic Inlets at Subcritical Conditions
Memorandum presenting an investigation of the phenomenon of the starting of aerodynamic instability or buzz in supersonic inlets with external compression. The starting of the buzz has been related to the existence in the flow field of a velocity discontinuity across a vortex sheet which originates at a shock intersection. Results regarding the inlets without separation on the central body, inlets with separation on the central body, the regulation of entering volume flow at angles of attack, experimental performance of various inlets, and an application of the results are provided.
Date:
January 26, 1951
Creator:
Ferri, Antonio & Nucci, Louis M.
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept, tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps - leading-edge flaps deflected
Report presenting aerodynamic characteristics of an unswept wing with an aspect ratio of 2.67, a taper ratio of 0.5, and employing full-span, 25-percent chord, plain, leading-edge flaps using wind-tunnel testing of a semispan model. The leading edge flap was generally effective at changing both the lift and pitching-moment coefficients at each angle of attack and Mach number. Results regarding lift characteristics, hinge-moment characteristics, drag characteristics, and pitching-moment characteristics are provided.
Date:
February 26, 1951
Creator:
Stivers, Louis S., Jr. & Malick, Alexander W.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation of the Aileron Characteristics of the Douglas D-558-I Airplane (BuAero No. 37972) at Mach Numbers Between 0.6 and 0.89
"Abrupt, rudder-fixed aileron rolls have been made with the Douglas D-558-I airplane (BuAero No. 37972) at Mach numbers between 0.6 and 0.89. Rolls were made at aileron deflections between one-eighth and one-half the maximum available deflection. The results obtained indicate that the aileron effectiveness is independent of Mach number and deflection within the range investigated" (p. 1).
Date:
May 26, 1950
Creator:
Thompson, Jim Rogers; Roden, William S. & Eggleston, John M.
Object Type:
Report
System:
The UNT Digital Library
Empirical cooling correlation for an experimental afterburner with an annular cooling passage
Report presenting an empirical cooling correlation for an experimental high-performance afterburner. The correlation equation is useful for shortening the experimental investigation of afterburner cooling characteristics inasmuch as it provides a method for interpolating the critical wall temperatures for other combinations of operating variables.
Date:
June 26, 1952
Creator:
Koffel, William K. & Kaufman, Harold R.
Object Type:
Report
System:
The UNT Digital Library
Base pressures measured on several parabolic-arc bodies of revolution in free flight at Mach numbers from 0.8 to 1.4 and at large Reynolds numbers
Report presenting base pressures measured on several fin-stabilized bodies of parabolic-arc profile in free flight at a range of Mach and Reynolds numbers. The bodies varied in length but had the same afterbody ratios. Results regarding base pressure coefficients, side pressure coefficients, effect of afterbody length, and drag are provided.
Date:
October 26, 1951
Creator:
Katz, Ellis & Stoney, William E., Jr.
Object Type:
Report
System:
The UNT Digital Library
Effect of Surface Finish on Fatigue Properties at Elevated Temperatures 1: Low-Carbon N-155 With Grain Size of A.S.T.M. 1
Effect of three surface finishes of roughness 4 to 5, 20 to 25, and 70 to 80 micro inches rms on fatigue properties were determined for low-carbon N-155 alloy of grain size A.S.T.M. 1 at temperatures of 80 , 1000, 1350, and 1500 F. The fatigue properties for the various finishes differed appreciably at room temperature; however, after short periods at 1000 F and for all periods investigated at temperatures above 1000 F, the specimen finishes had the same fatigue strength. It was concluded that the primary cause of the difference in room-temperature strength was due to compressive stresses set up in the surface and that at elevated temperatures these compressive stresses were relieved by annealing.
Date:
June 26, 1951
Creator:
Ferguson, Robert R.
Object Type:
Report
System:
The UNT Digital Library
Hinge-Moment and Other Aerodynamic Characteristics at Transonic Speeds of a Quarter-Span Spoiler on a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3
Memorandum presenting an investigation at transonic speeds in the high-speed 7- by 10-foot tunnel to determine the hinge-moment and other aerodynamic characteristics of an inboard plug-type spoiler on a 45 degree sweptback wing of aspect ratio 3. The results indicated that the spoiler would be overbalanced at low projections through the speed range investigated and the for the same rolling moment, the spoiler hinge moments would be small in comparison with those of a plain-flap-type control.
Date:
February 26, 1952
Creator:
Fikes, Joseph E.
Object Type:
Report
System:
The UNT Digital Library
Investigation of wing-tip ailerons on a 51.3 degrees sweptback wing at transonic speeds by the transonic-bump method
Report presenting an investigation to determine the aerodynamic characteristics of deflectable wing-tip ailerons on a sweptback wing in the Langley high-speed tunnel by means of the transonic bump technique. Three ailerons were investigated, one with a basic wing-plan form and two with an extended-tip plan form. Results regarding the longitudinal aerodynamic characteristics, rolling-moment data, control effectiveness, and lift effectiveness are provided.
Date:
November 26, 1951
Creator:
Moseley, William C., Jr. & Watson, James M.
Object Type:
Report
System:
The UNT Digital Library
Pressure Measurements on an Ogive-Cylinder Body at Mach Number 4.04
Report presenting pressure-distribution tests on an ogive-cylinder configuration with and without longitudinal spoilers at Mach number 4.04. Spoilers were not found to cause any noticeable change in the body pressures in regions that contribute the largest amount of normal body force. Results regarding a comparison of experimentation and theory, flow separation, and cross-flow effects are also provided.
Date:
February 26, 1952
Creator:
Lord, Douglas R. & Ulmann, Edward F.
Object Type:
Report
System:
The UNT Digital Library
The Effect of Raking the Aileron Tips on the Lateral-Control and Hinge-Moment Characteristics of a 20-Percent-Chord Partial-Span Outboard Aileron on a Wing With Leading-Edge Swept Back 51.3 Degrees
Report presenting an investigation at low speed to determine the lateral-control and hinge-moment characteristics of a 20-percent-chord unsealed partial-span outboard aileron with several plan forms. Results regarding the wing aerodynamic characteristics are also provided.
Date:
November 26, 1951
Creator:
Hammond, Alexander D.
Object Type:
Report
System:
The UNT Digital Library
Altitude Wind Tunnel Investigation of High-Temperature Afterburners
From Introduction: "During previous investigations of afterburning conducted at the NACA Lewis laboratory (references 1 to 4, for example), the objective of obtaining high exhaust-gas temperatures and, consequently, maximum thrust augmentation was compromised to some extent in order to alleviate the problem of afterburner shell cooling. The primary objective of the investigation reported herein was therefore the attainment of maximum exhaust-gas temperature imposed by the cooling techniques previously used, a secondary flow of cooling air was provided around the afterburner shell."
Date:
June 26, 1952
Creator:
Conrad, E. William & Campbell, Carl E.
Object Type:
Report
System:
The UNT Digital Library
Preliminary investigation of the effects of a paddle balance on the control characteristics at transonic speeds of a tapered 45.58 degrees sweptback wing of aspect ratio 3 having a full-span flap-type control
Report presenting an investigation in the high-speed tunnel on a 45.58 degree sweptback wing to determine the effects of a paddle balance on the control characteristics of a full-span flap-type control. The wing had an aspect ratio of 3, a taper ratio of 0.5, and an NACA 64A010 airfoil section measured in a plane at 45 degrees to the plane of symmetry. Results regarding the hinge-moment characteristics, lift characteristics, and rolling moment-characteristics are provided.
Date:
February 26, 1952
Creator:
Moseley, William C., Jr.
Object Type:
Report
System:
The UNT Digital Library
Low-speed tests of a free-to-yaw model in two wind tunnels of different turbulence
Report presenting tests at low speeds in the low turbulence pressure tunnel and the stability tunnel in order to determine the extent of any resulting oscillations of a model mounted with freedom in yaw and to demonstrate the extent to which directional fluctuations in an air stream can be responsible for the oscillations.
Date:
February 26, 1952
Creator:
Cahill, Jones F. & Bird, John D.
Object Type:
Report
System:
The UNT Digital Library
Survey of Available Information on Internal Flow Losses Through Axial Turbomachines
"Due to the scattered nature of existing information on the losses involved in the internal flow of gases through axial compressors and turbines, a brief survey of the available information on such losses is made. The present state of knowledge and the direction of future research toward the reduction of these losses are indicated" (p. 1).
Date:
January 26, 1951
Creator:
Wu, Chung-Hua
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of Flow in the Rotating Passages of a 48-Inch Impeller at Low Tip Speeds
Report presenting a study of the flow phenomena within the rotating passages of a 48-inch radial-inlet impeller at low tip speeds. Total and static pressures were measured within the impeller passages at two different tip speeds by using a suitable pressure-transfer device to transmit the pressures from the rotating passages to the stationary measuring station. Results regarding the overall compressor performance, static-pressure distribution along blades, total-pressure distribution across the passage, static-pressure distribution across the passage, pressure distribution from hub to shroud, and power input to impeller are provided.
Date:
June 26, 1951
Creator:
Michel, Donald J.; Ginsburg, Ambrose & Mizisin, John
Object Type:
Report
System:
The UNT Digital Library
Downwash in Vortex Region Behind Rectangular Half-Wing at Mach Number 1.91
Results of an experimental investigation to determine downwash and wake characteristics in region of trailing vortex system behind a rectangular half-wing at Mach number 1.91 are presented. The wing had a 5-percent thick symmetric diamond cross section beveled to a knife edge at the tip. At small angles of attack, downwash angles were in close agreement with predictions of linearized theory based on the assumption of an undistorted vortex sheet. At higher angles of attack, the flow was greatly influenced by the rolling up of the vortex sheet.
Date:
October 26, 1950
Creator:
Cummings, John L. & Haefeli, Rudolph C.
Object Type:
Report
System:
The UNT Digital Library
The Effective Downwash Characteristics at Transonic Speeds of a 6-Percent-Thick Wing With 47 Degrees of Sweepback in Combination With a Cylindrical Body as Determined From Force Measurements of a Horizontal Tail
Memorandum presenting the effective downwash characteristics of a wing-body configuration and the body alone determined from lift measurements of a horizontal tail located 0.333 and 0.479 wing semispan above the body center line. The wing had a sweepback angle of 47 degrees, an aspect ratio of 3.5, a taper ratio of 0.2, and a thickness ratio of 0.06.
Date:
November 26, 1952
Creator:
Coppolino, Domenic A.
Object Type:
Report
System:
The UNT Digital Library
Orthotoluidine and triethylamine in rocket engine applications
Report presenting a review of the literature pertaining to the use of orthotoluidine and triethylamine in rocket propellant combinations and a summary with particular emphasis on ignition delay investigations and fuel mixture applications. The survey indicated that orthotoluidine is about as good a rocket fuel as aniline with respect to cost, performance, and ignition characteristics, but it has a wider temperature application because of its lower freezing point.
Date:
January 26, 1953
Creator:
Ladanyi, Dezso J.
Object Type:
Report
System:
The UNT Digital Library
Cooling characteristics of an experimental tail-pipe burner with an annular cooling-air passage
The effects of tail-pipe fuel-air ratio (exhaust-gas temperatures from approximately 3060 degrees to 3825 degrees R), radial distribution of tail-pipe fuel flow, and mass flow of combustion gas and the inside wall were determined for an experimental tail-pipe burner cooled by air flowing through and insulated cooling-air to combustion gas mass flow from 0.066 to 0.192 were also determined. Results regarding the reproducibility of combustion-gas temperature profiles, effect of variables on average longitudinal profiles of combustion-gas temperature, variation of gas temperatures near the wall with cooling-air flow and temperature, and effects of variables on transverse gas temperatures are provided.
Date:
February 26, 1952
Creator:
Koffel, William K. & Kaufman, Harold R.
Object Type:
Report
System:
The UNT Digital Library
Air-flow characteristics of brazed and rolled wire filter cloth for transpiration-cooled afterburners
From Introduction: "Because of variation in the static-pressure drop across the porous material and in the cooling air required along the length of afterburner combustion chambers, a prescribed distribution of permeability is usually necessary. However, as a preliminary investigation, this report is concerned only with the attainment of uniform permeability. The results of an experimental investigation, conducted at the NACA Lewis laboratory, to determine the permeabilities of five thick meshes of wire filter cloth are presented herein."
Date:
October 26, 1953
Creator:
Koffel, William K.
Object Type:
Report
System:
The UNT Digital Library
Effects of rate of flap deflection on flap hinge moment and wing lift through the Mach number range from 0.32 to 0.87
Report presenting an investigation to determine the effect of rate of flap deflection on flap hinge moment and wing lift at a range of Mach and Reynolds numbers. For the rate of flap-deflection range investigated, the hinge-moment coefficient was practically independent of rate of flap deflection.
Date:
June 26, 1953
Creator:
Turner, Thomas R.
Object Type:
Report
System:
The UNT Digital Library
Turbine design considerations for turbine-propeller engine operating over a range of flight conditions
Report discussing the importance of designing aircraft turbines so that the entire range of operating conditions has been considered. In this particular investigation, the compressor performance was used to determine the turbine design requirements for a turbine-propeller engine to be operated up to altitudes of 40,000 feet and flight velocities up to 600 miles per hour. The two modes of engine operation considered were constant exhaust-nozzle area and variable exhaust-nozzle area.
Date:
June 26, 1953
Creator:
Davison, Elmer H.
Object Type:
Report
System:
The UNT Digital Library
Low-lift drag and stability data from rocket models of a modified-delta-wing airplane with and without external stores at Mach numbers from 0.8 to 1.36
Report presenting a flight investigation to determine the drag and stability at low lift coefficients of models of a modified-delta-wing airplane at a range of Mach and Reynolds numbers. A summary of the drag and stability data from the tests is provided.
Date:
March 26, 1953
Creator:
Mitcham, Grady L. & Blanchard, Willard S., Jr.
Object Type:
Report
System:
The UNT Digital Library
An extension of the investigation of the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA RM-10) at a Mach number of 1.61
Report presenting an investigation of the effects of heat transfer on boundary-layer transition at higher Reynolds numbers, greater amounts of heating, and a more extensive study of the effects of surface irregularities than what was published in a previous report. Report presenting tests with a smooth model and tests with surface roughness and tunnel flow disturbance are provided.
Date:
March 26, 1953
Creator:
Czarnecki, K. R. & Sinclair, Archibald R.
Object Type:
Report
System:
The UNT Digital Library