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An Investigation of the Characteristics of an Unswept Wing of Aspect Ratio 4.01 in the Langley 8-Foot High-Speed Tunnel

Description: Report presenting an investigation of the characteristics of a low-aspect-ratio wing at high subsonic Mach numbers in the high-speed tunnel. The wing model had an NACA 65-108 airfoil section, an aspect ratio of 4.01, a taper ratio of 0.498, and no twist or dihedral. Results regarding normal-force characteristics, pitching-moment characteristics, and drag characteristics are provided.
Date: November 8, 1949
Creator: Bielat, Ralph P. & Cahn, Maurice S.
Item Type: Refine your search to only Report
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Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and flame holders on J35 turbojet engine

Description: From Summary: "An investigation of turbojet-engine thrust augmentation by means of tail-pipe burning has been conducted in the NACA Lewis altitude wind tunnel. Several fuel systems and flame holders were investigated in a 29-inch-diameter tail-pipe burner to determine the effect of fuel distribution and flame-holder design on tail-pipe-burner performance and operational characteristics over a range of simulated flight conditions. At an altitude of 5000 feet, the type of flame holder used had on… more
Date: November 8, 1949
Creator: Conrad, E. William & Prince, William R.
Item Type: Refine your search to only Report
open access

Altitude Performance of AN-F-58 Fuels in British Rolls-Royce Nene Single Combustor

Description: "An investigation was conducted with a single combustor from a British Rolls-Royce Nene turbojet engine to determine the altitude performance characteristics of AN-F-58 fuels. Three fuel blends conforming to AN-F-58 specifications were prepared in order to determine the influence of fuel boiling temperatures and aromatic content on combustion efficiencies and altitude operational limits. The performance of the three AN-F-58 fuels was compared in the range of altitudes from sea level to 65,000 f… more
Date: July 8, 1949
Creator: Cook, William P. & Koch, Richard G.
Item Type: Refine your search to only Report
open access

Preparation of bismuth powder

Description: The principal object of this report is to record results of tests made on equipment installed in Room 232 of ``T`` Building and used to prepare bismuth powder for process operations. Another object is to establish the most favorable operating conditions for the equipment and to prepare operating instructions therefor.
Date: March 8, 1949
Creator: Cox, Grover C.; Grasso, Joseph A.; Hale, Denver & Wright, John W.
Item Type: Refine your search to only Report
open access

Estimated transonic flying qualities of a tailless airplane based on a model investigation

Description: Report presenting an analysis of the estimated flying qualities of a tailless airplane with the wing quarter-chord line swept back 35 degrees in a range of Mach numbers based on tests of a model of the airplane in the 7- by 10-foot tunnel. Results regarding performance, longitudinal stability and control, and lateral stability and control are provided.
Date: June 8, 1949
Creator: Donlan, Charles J. & Kuhn, Richard E.
Item Type: Refine your search to only Report
open access

Model ditching investigation of the Douglas DC-4 and DC-6 airplanes

Description: Report presenting the ditching characteristics of the Douglas DC-4 and DC-6 in a water tank. Dynamically similar models of 1/16 scale were used for the investigation, which was conducted in calm and rough water. The ditching characteristics and safest ditching procedures were determined by testing at various landing attitudes, speeds, and simulated conditions of damage.
Date: November 8, 1949
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
Item Type: Refine your search to only Report
open access

Four in. three jaw type connector suitable for vertical mounting sample for job 11

Description: As authorized by purchase order No. 11-2532 dated March 11, 1949 of the Kellex Corp., the first sample of a 4 inch three jaw type connector for Job 11 was fabricated. The design of the connector was per Crane Co. drawing DR-25126-D except vertical mounting. The materials were per Crane Co. drawing A-24491-C. As instructed in verbal conversation with Dr. D.D. Jacobus and as requested in Mr. J.J. Cuniffe`s letter of May 6, 1949, and Ingersoll-Rand Company`s 1 1/4 inch 534 impact wrench with suita… more
Date: July 8, 1949
Creator: Grubbe, A.C.
Item Type: Refine your search to only Report
open access

Determination of the purity of polonium by means of the vacuum balance (Ad Interim Report)

Description: The assay technique is discussed in detail. The results of three purity determinations are: 94.92 per cent, 100.50 per cent, and 106.9 per cent. The errors present in each determination are stated. The inherent dangers in the present procedure are pointed out, and an improved method is outlined.
Date: March 8, 1949
Creator: Haring, M. M.
Item Type: Refine your search to only Report
open access

Tests of the NACA 64-010 and 64A010 Airfoil Sections at High Subsonic Mach Numbers

Description: Memorandum presenting aerodynamic characteristics of the NACA 64-010 and 64A010 airfoil sections as determined from wind-tunnel tests at Mach numbers from 0.3 to 0.9. Comparisons are made which indicate the only significant differences in the characteristics of the two sections to be a consistently greater lift-curve slope and an approximately 10-percent greater maximum section lift coefficient at Mach numbers above 0.7 for the NACA 64-010 airfoil section.
Date: July 8, 1949
Creator: Hemenover, Albert D.
Item Type: Refine your search to only Report
open access

Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 5: Static Longitudinal Stability and Control Throughout the Subsonic Speed Range of a Semispan Model of a Supersonic Airplane

Description: Memorandum presenting wind-tunnel tests of a semispan model of a hypothetical supersonic airplane to determine the static longitudinal stability and control characteristics of the airplane throughout the range of subsonic Mach numbers up to 0.95. The model had a long slender fuselage and a wing and horizontal tail of aspect ratio 4 and taper ratio 0.5. Results regarding the force and moment characteristics, wing wake and effective downwash at the horizontal tail, effects of compressibility, and… more
Date: December 8, 1949
Creator: Johnson, Ben H., Jr. & Rollins, Francis W.
Item Type: Refine your search to only Report
open access

Investigation at large scale of the pressure distribution and flow phenomena over a wing with the leading edge swept back 47.5 degrees having circular-arc airfoil sections and equipped with drooped-nose and plain flaps

Description: Report presenting an investigation of the pressure distribution over a wing with the leading-edge swept back 47.5 degrees and with symmetrical circular-arc airfoil sections in the full-scale tunnel at a designated Mach and Reynolds number. The investigation included measurements of the surface static pressures along the chord for six spanwise stations, for a large angle-of-attack range, and for several angles of yaw.
Date: September 8, 1949
Creator: Lange, Roy H.; Whittle, Edward F., Jr. & Fink, Marvin P.
Item Type: Refine your search to only Report
open access

Damping-in-Roll Characteristics of a 42.7 Degree Sweptback Wing as Determined From a Wind-Tunnel Investigation of a Twisted Semispan Wing

Description: Report presenting an investigation to determine the damping-in-roll characteristics of a 42.7 degree sweptback wing using a linearly twisted wing to represent a rolling wing. Results regarding the effect of the airfoil contour, damping-in-roll coefficient, wing-tip helix angle, and theoretical results are provided.
Date: August 8, 1949
Creator: Lockwood, Vernard E.
Item Type: Refine your search to only Report
open access

Smooth-Water Landing Stability and Rough-Water Landing and Take-Off Behavior of a 1/13-Scale Model of the Consolidated Vultee Skate 7 Seaplane, TED No. NACA DE 338

Description: A model of the Consolidated Vultee Aircraft Corporation Skate 7 seaplane was tested in Langley tank no. 2. Presented without discussion in this paper are landing stability in smooth water, maximum normal accelerations occurring during rough-water landings, and take-off behavior in waves.
Date: September 8, 1949
Creator: McKann, Robert F.; Coffee, Claude W. & Arabian, Donald D.
Item Type: Refine your search to only Report
open access

An empirical criterion for fin stabilizing jettisonable nose sections of airplanes

Description: "Investigations in the Langley 20-foot free-spinning tunnel of models of five jettisonable nose sections have shown that the airplane nose sections are inherently unstable but can be stabilized by the addition of suitable fins. An empirical criterion has been developed which indicates the fin area required for stabilizing an airplane jettisonable nose section" (p. 1).
Date: December 8, 1949
Creator: Scher, Stanley H.
Item Type: Refine your search to only Report
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