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Investigation of interaction effects arising from side-wall boundary layers in supersonic wind-tunnel tests of airfoils

Description: Report presenting an investigation to determine the cause for a discrepancy between theoretical and experimental pressure distributions found during a two-dimensional investigation of flapped airfoils in a 2- by 8-inch supersonic tunnel. The results indicated that a tunnel-boundary-layer and model-flow interaction effect on the flow over models mounted directly from the walls in supersonic wind tunnels exists.
Date: November 3, 1948
Creator: Czarnecki, K. R. & Schueller, C. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Horn Balances on a 45 Degree Sweptback Horizontal Tail Surface at High Subsonic Speeds

Description: A wind-tunnel investigation of horn balances on a 45 degree sweptback, semispan, horizontal tail surface was made to determine the effects of horn size and inboard-edge fairing at a Mach number of 0.30 and to determine the effects of compressibility up to a Mach number of 0.89. Presented are lift, drag, pitching-moment, and hinge-moment data and lift and hinge-moment parameters.
Date: December 3, 1948
Creator: Johnson, Harold S. & Thompson, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Correlation of the Effect of Compressibility on the Location of the Section Aerodynamic Center at Subcritical Speeds

Description: Memorandum presenting a correlation of available two-dimensional airfoil data to determine the effects of compressibility on the location of the section aerodynamic center at low lift coefficients. The results indicate that large forward or rearward movements of the aerodynamic center with Mach number are possible.
Date: November 3, 1948
Creator: Polhamus, Edward C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 2: maximum thickness at midchord

Description: "The lift, drag, and pitching-moment characteristics of a triangular wing, having an aspect ratio of 2 and a symmetrical double-wedge profile of 5-percent-chord maximum thickness at midchord, have been evaluated from wind-tunnel tests at Mach numbers from 0.50 to 0.975 and from 1.09 to 1.49 and at Reynolds numbers ranging from 0.67 to 0.85 million. The lift, drag, and pitching-moment coefficients of the triangular wing with a leading-edge sweepback of approximately 63 degrees did not exhibit th… more
Date: December 3, 1948
Creator: Walker, Harold J. & Berggren, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Horizontal Tails 2: Unswept and 35 Degree Swept-Back Plan Forms of Aspect Ratio 4.5

Description: Memorandum presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of two semispan horizontal tails with unswept and 35 degree sweptback plan forms. The two models had an aspect ratio of 4.5, taper ratio of 0.5, and an NACA 64A010 airfoil section. Test results are presented with and without standard roughness applied to their leading edges and with sealed and unsealed radius-nose elevators.
Date: June 3, 1948
Creator: Dods, Jules B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Ground Effect on Downwash Angles and Wake Location

Description: "A theoretical study was made of the reduction in downwash and the upward displacement of the wake in the presence of the ground, and some verification of theory was obtained by means of air-flow measurements made with a ground-board and image-wing combination. Methods are given for estimating the effects and numerous examples are included to illustrate the nature of these effects and to show their order of magnitude" (p. 1).
Date: October 3, 1941
Creator: Katzoff, S. & Sweberg, Harold H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Longitudinal Stability of Elastic Swept Wings at Supersonic Speed

Description: "The longitudinal stability characteristics of elastic swept wings of high aspect ratio experiencing bending and torsional deformations are calculated for supersonic speed by the application of linearized lifting-surface theory. A parabolic wing deflection curve is assumed and the analysis is simplified by a number of structural approximations. The method is thereby limited in application to wings of high aspect ratio for which the root effects are small" (p. 1).
Date: December 3, 1948
Creator: Frick, C. W. & Chubb, R. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Lagrangian Multiplier Method of Finding Upper and Lower Limits to Critical Stresses of Clamped Plates

Description: "The theory of Lagrangian multipliers is applied to the problem of finding both upper and lower limits to the true compressive buckling stress of a clamped rectangular plate. The upper and lower limits thus bracket the true stress, which cannot be exactly found by the differential-equation approach. The procedure for obtaining the upper limit, which is believed to be new, presents certain advantages over the classical Rayleigh-Ritz method of finding upper limits" (p. 213).
Date: May 3, 1946
Creator: Budiansky, Bernard & Hu, Pai C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Mach Number on the Aerodynamic Characteristics of a Single-Engine Pursuit Airplane as Determined From Tests of a 1/3-Scale Model

Description: Report discussing the effects of Mach number on the aerodynamic characteristics of an Allison powered single-engine pursuit airplane. Information about the lift, drag, pitching-moment characteristics, stability, tail effectiveness, and elevator effectiveness with Mach number is provided.
Date: May 3, 1945
Creator: Robinson, Robert C. & Jessen, Henry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of fuel on performance of a single combustor of an I-16 turbojet engine at simulated altitude conditions

Description: As part of a study of the effects of fuel composition on the combustor performance of a turbojet engine, an investigation was made in a single I-16 combustor with the standard I-16 injection nozzle, supplied by the engine manufacturer, at simulated altitude conditions. The 10 fuels investigated included hydrocarbons of the paraffin olefin, naphthene, and aromatic classes having a boiling range from 113 degrees to 655 degrees F. They were hot-acid octane, diisobutylene, methylcyclohexane, benzen… more
Date: July 3, 1947
Creator: Zettle, Eugene V.; Bolz, Ray E. & Dittrich, R. T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Determination of Ram-Jet Combustion-Chamber Temperatures by Means of Total-Pressure Surveys

Description: "A method is described by which the total temperature of the gases at the combustion-chamber outlet of a ram-jet engine may be determined from the loss in total pressure measured across the combustion chamber. A working chart is presented by means of which the ratio of the total temperature of the gases at the combustion-chamber outlet to the total temperature of the gases at the combustion-chamber inlet may be determined from the measured loss of total pressure across the combustion chamber an… more
Date: March 3, 1947
Creator: Pinkel, I. Irving
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Knock-Limited Blending Characteristics of Benzene, Toluene, Mixed Xylenes, and Cumene in an Air-Cooled Cylinder

Description: "An investigation was conducted to determine the knock-limited blending characteristics of leaded fuels containing selected aromatic fuel components (benzene, toluene, mixed xylenes, and cumene). Each of the aromatics was blended with an alkylate blending agent and with a virgin base stock. The blending characteristics of the resulting fuels were determined in a full-scale aircraft-engine cylinder" (p. 1).
Date: February 3, 1945
Creator: Hensley, Reece V. & Breitwieser, Roland
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Endurance Tests of a 22-Inch-Diameter Pulse-Jet Engine With a Neoprene-Coated Valve Grid

Description: Report discussing the results of testing to determine the operating life of a 22-inch-diameter pulse-jet engine equipped with a neoprene-coated valve grid. The valve grid was found to extend the operating life and only reduced the performance slightly.
Date: October 3, 1945
Creator: Manganiello, Eugene J.; Valerino, Michael F. & Breisch, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms September 4, 1947 to September 5, 1947 at Clinton County Army Air Field, Ohio

Description: The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from September 4, 1947 to September 5, 1947 are presented.
Date: April 3, 1948
Creator: Funk, Jack
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of the Directional Stability and Control of a P-51D Airplane with a Horn-Balanced Rudder as Compared with Previously Tested Vertical-Tail Configurations

Description: "At the request of the Air Materiel Command, Army Air Forces, flight tests were conducted on a P-5lD-20-NA (AAF No. 44-63826) airplane equipped with a horn-balanced rudder. This rudder was fitted with an unbalancing tab as was the original product fan rudder. Tests were made both with the unbalancing tab in operation and with the unbalancing tab locked. The modification to the original vertical tail consisted of removing the cap from the top of the fin and adding 1.91 square feet of area to the… more
Date: December 3, 1946
Creator: Mungall, Robert G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning Tunnel Tests of a 1/20-Scale Model of the Chance Vought XF6U-1 Airplane, TED No. NACA 2390

Description: "A spin investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/20-scale model of the Chance Vought XF6U-1 airplane. The effects of control settings and movements upon the erect and inverted spin and recovery characteristics of the model were determined for the normal-fighter condition. The investigation also included tests for the take-off fighter condition (wing-tip tanks plus fuel added) spin-recovery parachutes, and simulated pilot escape" (p. 1).
Date: October 3, 1948
Creator: Klinar, Walter J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Knock-Limited Power Outputs from a CFR Engine Using Internal Coolants 3 - Four Alkyl Amines, Three Alkanolamines, Six Amides, and Eight Heterocyclic Compounds

Description: An investigation of the antiknock effectiveness of various additive-water solutions when used as internal coolants has been conducted at the NACA Cleveland laboratory. Nine compounds have been previously run in a CFR engine and the results are presented. In an effort to find a good anti-knock-coolant additive with more desirable physical properties than those of the nine compounds previously investigated, water solutions of four alkyl amines, three alkanolamines, six amides, and eight heterocyc… more
Date: February 3, 1947
Creator: Imming, Harry S. & Bellman, Donald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Crystal Structure at Room Temperature of Six Cast Heat-Resisting Alloys

Description: The crystal structures of alloys 61, X-40,X-50, 422-19, 6059, and Vitallium, derived from x-ray diffraction, are discussed. The alloys have been, or are being considered for use in gas turbine applications. The predominant phase was a solid solution of the face centered cubic type of the principal constituent elements.The lattice parameters were found to be between 3.5525 and 3.5662.
Date: June 3, 1947
Creator: Rosenbaum, Burt M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller Engine 2 - Windmilling Characteristics

Description: Wind tunnel investigations were performed to determine the performance properties of an axial-flow gas turbine-propeller engine II. Windmilling characteristics were determined for a range of altitudes from 5000 to 35,000 feet, true airspeeds from 100 to 273 miles per hour, and propeller blade angles from 4 degrees to 46 degrees.
Date: August 3, 1948
Creator: Conrad, E. W. & Durham, J. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Evaluation of the Spin and Recovery Characteristics of the Douglas XF3D-1 Airplane

Description: "A preliminary evaluation of the spin and recovery characteristics of the XF3D-1 airplane has been made, based primarily on the results of the free-spinning tunnel tests of a model which closely simulated the XF3D-1 in tail design, tail length, and mass loading. Estimates have been made of the rudder-pedal force that may be encountered in effecting recovery from a spin and of the spin recovery parachute requirements of the airplane for demonstration spins. The method of bail-out which should be… more
Date: July 3, 1947
Creator: Scher, Stanley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of J33-A-21 and J33-A-23 Turbojet-Engine Compressors with Water Injection

Description: "As part of the performance investigation of compressors for the J33 turbojet engine, the A-21 model and the A-23 model with a 17- and a 34-blade impeller were operated with water injection at their respective design equivalent speeds of 11,500 and 11,750 rpm. Inlet conditions of pressure of 14 inches of mercury absolute and of ambient temperature correspond to those of the investigation of these models without water injection. The water-air ratio by weight ranged from 0.05 to 0.06. By the use … more
Date: August 3, 1949
Creator: Beede, William L. & Withee, Joseph R., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ditching Tests of a 1/9-Size Model of the Army P-38 Airplane in Langley Tank No. 2 and at the Outdoor Catapult

Description: "A dynamically similar model of the Army P-38 airplane was tested to determine the best way to land this airplane on the water and to determine its probable ditching performance. The tests consisted of ditching the model at various landing attitudes, flap settings, speeds, weights, and conditions of simulated damage. The model was ditched in calm water from the tank towing carriage and a few ditching were made in both calm and rough water at the outdoor catapult" (p. 1).
Date: December 3, 1946
Creator: Jarvis, George A. & Cederborg, Gibson A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of the Longitudinal Stability and Control Characteristics of the Grumman F8F-1 Airplane, TED No. NACA 2379

Description: A series of flight tests have been made at the Langley Flight Research Division at the request of the Bureau of Aeronautics, Department of the Navy, to determine the flying qualities of the Grumman F8F-1 air- plane. This paper presents the test results necessary to determine the longitudinal stability and control characteristics end the stalling characteristics. The range of Mach numbers covered in this investigation was approximately 0.10 to 0.62, and no attempt was made to investigate compres… more
Date: September 3, 1948
Creator: Assadourian, Arthur & Reeder, John P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine, Part 1, Performance and Windmilling Drag Characteristics

Description: From Summary: "The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-type 4000-pound-thrust turbojet engine for a range of pressure altitudes from 5000 to 40,000 feet and ram pressure ratios from 1.02 to 1.86 are presented and the experimental and analytical methods employed are discussed. By means of suitable generalizing factors applied to the measured performance data, curves were obtained from which the engine performance at any altitude for a giv… more
Date: August 3, 1948
Creator: Fleming, William A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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