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Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section

Description: From Introduction: "This paper presents the results of the investigation of the wing-alone and of the wing-fuselage configuration employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the air stream. The results of closely related sweptback-wing investigations, which are part of the present transonic programs, are presented in references 1 to 3."
Date: October 21, 1949
Creator: Goodson, Kenneth W. & Morrison, William D., Jr.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of an Airfoil-Forebody Swept Flying-Boat Hull With a Wing and Tail Swept Back 51.3 Degrees at the Leading Edge

Description: Report discussing an investigation of the aerodynamic characteristics of an airfoil-forebody swept flying boat hull with a wing and tail swept back 51.3 degrees at the leading edge. The swept hull's minimum drag coefficient was about the same as the parent model or streamline model. Various combinations of flaps were also utilized.
Date: September 9, 1949
Creator: Naeseth, Rodger L. & MacLeod, Richard G.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of the NACA 8-H-12 airfoil section at six Reynolds numbers from 1.8 x 10(exp 6) to 11.0 x 10(exp 6)

Description: Report presenting an investigation in the two-dimensional low-turbulence pressure tunnel to determine the aerodynamic characteristics of the NACA 8-H-12 airfoil section at four Reynolds numbers. The section lift, drag, and pitching-moment characteristics are presented for smooth and rough surface conditions. Generally, no unusual scale effects are present for either condition.
Date: December 1949
Creator: Schaefer, Raymond F. & Smith, Hamilton A.
Item Type: Refine your search to only Report
open access

The aerodynamic characteristics throughout the subsonic speed range of a thin, sharp-edged horizontal tail of aspect ratio 4 equipped with a constant-chord elevator

Description: From Introduction: "Recent investigations have indicated several wing plan forms, wing sections, and wing-body-tail combinations suitable for flight at supersonic speeds. One such lifting surface, a thin, sharp-edged without sweep of aspect ratio 4 and taper ratio 0.5, has been the subject of an investigation in the Ames 12-foot pressure wind tunnel. The aim of the investigation was to determine the aerodynamic characteristics of such a wing plan form throughout the range of subsonic Mach numbe… more
Date: June 30, 1949
Creator: Bandettini, Angelo & Reed, Verlin D.
Item Type: Refine your search to only Report
open access

Aerodynamic Properties of Cruciform-Wing and Body Combinations at Subsonic, Transonic, and Supersonic Speeds

Description: From Introduction: "Although the aerodynamic characteristics of the components of such configurations may be well known, the mutual interference resulting from combining the wings, as well as the wings and body, may be so great that is desirable to study the aerodynamic properties of the complete configurations. Two methods of handling this problem are presented in this report. The first method is essentially an extension of the theory for slender wing-body combinations of reference 1 to determ… more
Date: June 1949
Creator: Spreiter, John R.
Item Type: Refine your search to only Report
open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Aerodynamic characteristics in sideslip of a large-scale model having a 63 degree swept-back vertical tail

Description: Report presenting an investigation to determine the effects of a vertical tail with the leading edge swept back 63 degrees on the aerodynamic characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees. The aerodynamic characteristics in sideslip with and without the vertical tail are also presented. Results regarding the directional stability, rudder effectiveness, and rudder hinge moments are described.
Date: October 7, 1949
Creator: McCormack, Gerald M.
Item Type: Refine your search to only Report
open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Characteristics at a Mach number of 1.53 including effect of small variations of sweep

Description: Measured values of lift, drag, and pitching moment at a Mach number of 1.53 and Reynolds numbers of 0.31, 0.62, and 0.84 million are presented for a wing-fuselage combination having a wing leading-edge sweep angle of 63 degrees, an aspect ratio of 3.42, a taper ratio of 0.25, and an NACA 64A006 section in the stream direction. Data are also presented for sweep angles of 57.0 degrees, 60.4 degrees, 67.0 degrees, and 69.9 degrees. The experimentally determined characteristics were less favorable … more
Date: January 26, 1949
Creator: Madden, Robert T.
Item Type: Refine your search to only Report
open access

Aerodynamic Study of a Wing-Fuselage Combination Employing a Wing Swept Back 63 Degrees: Characteristics for Symmetrical Wing Sections at High Subsonic and Moderate Supersonic Mach Numbers

Description: From Summary: "Results of wind-tunnel tests are presented for a wing with the leading edge swept back 63^o and of symmetrical section in combination with a body at Mach numbers from 0.5 to 0.95 and from 1.09 to 1.51."
Date: July 7, 1949
Creator: Mas, Newton A.
Item Type: Refine your search to only Report
open access

Aerodynamic Study of a Wing-Fuselage Combination Employing a Wing Swept Back 63 Degrees: Characteristics Throughout the Subsonic Speed Range With the Wing Cambered and Twisted for a Uniform Load at a Lift Coefficient of 0.25

Description: Report presenting wind-tunnel testing to determine the independent effects of Mach and Reynolds numbers on the aerodynamic characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and with camber and twist. Results regarding the fuselage alone and the effects of camber and twist are also provided.
Date: August 15, 1949
Creator: Jones, J. Lloyd & Demele, Fred A.
Item Type: Refine your search to only Report
open access

Aerodynamic Study of a Wing-Fuselage Combination Employing a Wing Swept Back 63 Degrees: Effects at Subsonic Speeds of a Constant-Chord Elevon on a Wing Cambered and Twisted for a Uniform Load at a Lift Coefficient of 0.25

Description: Report presenting testing of a cambered and twisted wing with constant-chord elevons with a slender fuselage to determine the longitudinal and lateral control from the elevons for a range of Mach numbers. Results regarding lift, drag, pitching-moment, and rolling-moment characteristics for various elevon deflections are provided.
Date: December 5, 1949
Creator: Jones, J. Lloyd & Demele, Fred A.
Item Type: Refine your search to only Report
open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Effects of split flaps, elevons, and leading-edge devices at low speed

Description: Report presenting an investigation to evaluate the effects of split flaps, elevons, sharp leading edges, drooped-nose flaps, and extended-nose flaps on the lift, drag, and pitching-moment characteristics at low speed of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and an aspect ratio of 3.5. Results regarding the plain wing and wing-fuselage combinations, Reynolds number, split flaps, elevons, leading-edge devices, and highest lift coefficient attained bef… more
Date: May 19, 1949
Creator: Hopkins, Edward J.
Item Type: Refine your search to only Report
open access

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

Description: 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.
Item Type: Refine your search to only Report
open access

Alpha-Decay in Isotopes of Atomic Number Less Than 83

Description: Some time ago we started work in an attempt to observe alpha-particle decay in isotopes of atomic number less than 83. In the first experiments, thin targets of gold leaf were bombarded with 190-Mev deuterons in the 184-inch cyclotron. Two alpha-decay periods were observed in these targets; one of 0.7 minutes half-life and another of 4.3 minutes half-life. The alpha-particle energies were 5.7 and 5.2 Mev, respectively. Chemical separations proved that the 4.3-minute period is due to a gold isot… more
Date: September 5, 1949
Creator: Thompson, S. G.; Ghiorso, A.; Radmussen, J. O. & Seaborg, G. T.
Item Type: Refine your search to only Report
open access

Altitude-chamber performance of British Rolls-Royce Nene II engine 1: standard 18.75-inch-diameter jet nozzle

Description: Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with a standard 18.75-inch-diameter jet nozzle. Results regarding the simulated flight performance and generalized performance across other altitude and pressure characteristics are provided.
Date: September 23, 1949
Creator: Barson, Zelmar & Wilsted, H. D.
Item Type: Refine your search to only Report
open access

Altitude-Chamber Performance of British Rolls-Royce Nene II Engine 2: 18.41-Inch-Diameter Jet Nozzle

Description: Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with an 18.41-inch-diameter jet nozzles. Testing occurred at a range of simulated altitudes and ram-pressure ratios. Results regarding the simulated flight performance, generalized performance, and effect of jet-nozzle area on performance are provided.
Date: October 26, 1949
Creator: Armstrong, J. C.; Wilsted, H. D. & Vincent, K. R.
Item Type: Refine your search to only Report
open access

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

Altitude-Test-Chamber Investigation of McDonnell Afterburner on J34 Engine

Description: "An altitude-test-chamber investigation was conducted to determine the operational and performance characteristics of a McDonnell afterburner with a fixed-area exhaust nozzle on a J34 engine. At rated engine speed, the altitude limit, as determined by combustion blow-out, occurred as a band of unstable operation of about 6000-foot altitude in width with minimum altitude limits from 31,000 feet at a simulated flight Mach number of 0.40 to about 45,500 feet at a simulated flight Mach number of 1.… more
Date: June 2, 1949
Creator: Reller, John O. & Dowman, Harry W.
Item Type: Refine your search to only Report
open access

Altitude-wind-tunnel investigation of AN-F-58 fuel in experimental version of J47 turbojet engine

Description: An altitude-wind-tunnel investigation of the performance of AN-F-58 and AN-F-32 fuels in an experimental turbojet engine was conducted over a range of simulated altitudes and flight Mach numbers. Combustion efficiencies obtained with AN-F-58 and AN-F-32 fuels were approximately equal. The minimum-speed altitude operational limit was essentially the same with either AN-F-58 or AN-F-32 fuel. Starting characteristics of the two fuels were approximately the same at low wind milling speeds. Visual o… more
Date: May 2, 1949
Creator: Meyer, Carl L.
Item Type: Refine your search to only Report
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