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open access

Aerodynamic and Lateral-Control Characteristics of a 1/28-Scale Model of the Bell X-1 Airplane Wing-Fuselage Combination: Transonic-Bump Method

Description: Report discussing an investigation into the lateral-control characteristics and the pitching-moment characteristics of a scale model of the X-1 wing-fuselage configuration. Information about the estimated variation of rolling effectiveness and wing-fuselage pitching-moment coefficient is described in detail.
Date: May 5, 1950
Creator: Lockwood, Vernard E.
open access

Aerodynamic Characteristics at a Mach Number of 1.25 of a 6-Percent-Thick Triangular Wing and 6- and 9-Percent-Thick Triangular Wings in Combination With a Fuselage: Wing Aspect Ratio 2.31, Biconvex Airfoil Sections

Description: Report discussing testing to determine the aerodynamic characteristics of two semispan delta-wing configurations. Information about the lift characteristics, drag characteristics, pitching-moment characteristics, and comparison with other results is provided.
Date: May 5, 1950
Creator: Hall, Albert W. & Morris, Garland J.
open access

Aerodynamic Characteristics at a Mach Number of 1.38 of Four Wings of Aspect Ratio 4 Having Quarter-Chord Sweep Angles of 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees

Description: Report discussing testing to determine the supersonic aerodynamic characteristics of four sweptback wings and wing-body configurations at several angles. Information about basic wing data, modifications to the 60 degree wing, the effects of sweep, and effects of fuselage are included.
Date: October 10, 1950
Creator: Kemp, William B., Jr.; Goodson, Kenneth W. & Booth, Robert A.
open access

Aerodynamic characteristics at Reynolds numbers of 3.0 x 10(exp 6) and 6.0 x 10(exp 6) of three airfoil sections formed by cutting off various amounts from the rear portion of the NACA 0012 airfoil section

Description: Report presenting an investigation of the two-dimensional aerodynamic characteristics of three airfoil sections formed by removing various portions of the original chord from the trailing edge of the NACA 0012 airfoil section. Results regarding lift, drag, and pitching moment and aerodynamic center are provided.
Date: April 1950
Creator: Smith, Hamilton A. & Schaefer, Raymond F.
open access

Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic bump method

Description: From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuselage configurations employing a wing with the quarter-chord line swept back 60^o, aspect ratio 2, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the free stream."
Date: February 24, 1950
Creator: Myers, Boyd C., II & King, Thomas J., Jr.
open access

Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and NACA 65A004 airfoil section: transonic-bump method

Description: From Introduction: "This paper presents the results of an investigation of force and moment characteristics for a wing with an unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and an NACA 65A004 airfoil section parallel to the free stream."
Date: March 8, 1950
Creator: Polhamus, Edward C. & Campbell, George S.
open access

Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A004 airfoil section: Transonic-bump method

Description: From Introduction: "This paper presents the results of the investigation of the wing alone and of the wing-fuselage configurations employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A004 airfoil section parallel to the air stream. The experimental results of a wing of identical plan from having an NACA 65A006 airfoil section which was tested as part of the transonic program are presented in reference 1.
Date: May 8, 1950
Creator: Myers, Boyd C., II & Wiggins, James W.
open access

Aerodynamic Characteristics of Damping Screens

Description: From Summary: "The experimental investigation of damping screens described herein was undertaken primarily to test theories of the effects of damping screens and to obtain information on the performance of screens in oblique flow. The characteristics investigated include the damping of longitudinal and lateral components of turbulence, the effect of screens on scale, the conditions for the production of turbulence and eddies by screens, and the damping of spatial variations of mean speed."
Date: January 1950
Creator: Schubauer, G. B.; Spangenberg, W. G. & Klebanoff, P. S.
open access

Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 1: presentation and analysis of pressure measurements (stabilizing fins removed)

Description: Experimental investigation of flow about a slender body of revolution (NACA RM-10 missile) aligned and inclined to a supersonic stream was conducted at Mach numbers from 1.49 to 1.98 at a Reynolds number of approximately 30,000,000. Boundary-layer measurements at zero angle of attack are correlated with subsonic formulations for predicting boundary-layer thickness and profile. Comparison of pressure coefficients predicted by theory with experimental values showed close agreement at zero angle o… more
Date: July 20, 1950
Creator: Luidens, Roger W. & Simon, Paul C.
open access

Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 2: presentation and analysis of force measurements

Description: Experimental investigation of aerodynamic forces acting on body of revolution (NACA RM-10 missile) with and without stabilizing fins was conducted at Mach numbers from 1.49 to 1.98 at angles of attack from 0 to 9 degrees and at Reynolds number of approximately 30,000,000. Comparison of experimental lift, drag, and pitching-moment coefficients and center of pressure location for body alone is made with linearized potential theory and a semiempirical method. Results indicate that aerodynamic char… more
Date: July 21, 1950
Creator: Esenwein, Fred T.; Obery, Leonard J. & Schueller, Carl F.
open access

Aerodynamic characteristics of NACA RM 10 missile in 8 by 6 foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98. 3: analysis of force distribution at angle of attack (stabilizing fins removed)

Description: Report presenting an analysis of the force distribution on a slender pointed body of revolution at angle of attack utilizing pressure-distribution data and balance measurements. The data were obtained in the supersonic tunnel at a variety of Mach numbers and angles of attack. Results regarding normal forces and axial force are provided.
Date: December 12, 1950
Creator: Luidens, Roger W. & Simon, Paul C.
open access

Aerodynamic characteristics with fixed and free transition of a modified delta wing in combination with fuselage at high subsonic speeds

Description: From Introduction: "An investigation of the high-speed aerodynamic characteristics of a modified delta wing in combination with a fuselage was conducted in the Langley high-speed 7- by 10-foot tunnel. The model was tested on the sting support system through a Mach number range of 0.40 to 0.90 with both free and fixed transition. Because of the nature of the transition effect, the results seemed to be of the general interest and are presented in the present paper."
Date: May 2, 1950
Creator: Polhamus, Edward C. & King, Thomas J., Jr.
open access

Aerodynamic coefficients for an oscillating airfoil with hinged flap, with tables for a Mach number of 0.7

Description: From Introduction: "The fundamental integral equation for the pressure distribution on an oscillating thin airfoil moving at subsonic speed has been derived by Possio in reference 1. Collocation procedures have been used by Possio, Frazer, and Skan, and others to obtain lift and moment on an oscillating first plate. An important contribution has been made by Dietze (see reference 2 and 3), who has developed an iterative procedure for numerical solution of Possio's integral equation."
Date: October 1950
Creator: Turner, M. J. & Rabinowitz, S.
open access

The aerodynamic forces and moments on a 1/10-scale model of a fighter airplane in spinning attitudes as measured on a rotary balance in the Langley 20-foot free-spinning tunnel

Description: From Introduction: "This investigation provides general information on the magnitudes and directions of the aerodynamic forces and moments acting on a fighter airplane in fully developed spins. The investigation includes the determination of the effects on the aerodynamic forces and moments of varied rudder setting with and against the spin, of tail modifications, and of deflected flaps and lowered landing gear."
Date: September 1950
Creator: Stone, Ralph W., Jr.; Burk, Sanger M., Jr. & Bihrle, William, Jr.
open access

The Aerodynamic Forces on Slender Plane- and Cruciform-Wing and Body Combinations

Description: From Introduction: "Since these results were not applicable to the present problem, a theoretical analysis of the aerodynamic properties of slender wing-body combinations was undertaken. The results of this investigation were first reported in reference 5 and were later extended in reference 6 to include cruciform-wing and body combinations. The present report summarizes and extends the theory and results previously presented in these references."
Date: 1950%
Creator: Spreiter, John R.
open access

Aerodynamic Investigation of a Parabolic Body of Revolution at Mach Number of 1.92 and Some Effects of an Annular Jet Exhausting From the Base

Description: Report discussing an investigation of a parabolic body of revolution with and without the effects of an annular jet exhausting from the base. The aerodynamic characteristics, pressures, lift-curve slope, and other characteristics with the jet in operation and inoperative were compared.
Date: February 8, 1950
Creator: Love, Eugene S.
open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: effect of Reynolds number at supersonic Mach numbers on the longitudinal characteristics of a wing twisted and cambered for uniform load

Description: Report presenting a wind-tunnel investigation of the longitudinal characteristics of a wing-body combination with a wing with leading edge swept back 63 degrees. Lift, drag, and pitching-moment measurements were made over a range of Mach and Reynolds numbers. Results regarding the general characteristics and effect of Reynolds number are provided.
Date: October 9, 1950
Creator: Heitmeyer, John C.
open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effect of sideslip on aerodynamic characteristics at a Mach number of 1.4 with the wing twisted and cambered

Description: Report presenting the longitudinal and lateral characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and cambered and twisted for a uniform load at lift coefficient 0.25 and Mach number 1.5. The investigation occurred over a range of sideslip angles. The results indicated that the longitudinal characteristics were essentially unaffected by Reynolds number or the sideslip angles investigated.
Date: September 29, 1950
Creator: Lessing, Henry C.
open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness of an elevon as a longitudinal control and the effects of camber and twist on the maximum lift-drag ratio at supersonic speeds

Description: Report presenting an investigation concerned with the measurement of the characteristics of longitudinal-control devices for a wing-fuselage combination with a wing with the leading edge swept back 63 degrees. Most of the investigation was devoted to testing a 30-percent-chord, 50-percent-semispan elevon, but some used upper-surface spoilers. Results regarding the characteristics of the wing with the elevon undeflected and control-surface effectiveness are provided.
Date: May 8, 1950
Creator: Olson, Robert N. & Mead, Merrill H.
open access

Aeronautical study of a wing-fuselage combination employing a wing swept back 63 degrees: Characteristics at supersonic speeds of a model with the wing twisted and cambered for uniform load

Description: Report presenting the lift, drag, and pitching-moment characteristics of a wing-fuselage combination employing a wing with the leading edge swept back 63 degrees and cambered and twisted for a uniform load at a lift coefficient of 0.25 and Mach number 1.53. The experimental results are compared to those from other investigations. A maximum lift-drag ratio of 8.9 and a minimum drag coefficient of 0.0145 was obtained.
Date: January 9, 1950
Creator: Hall, Charles F. & Heitmeyer, John C.
open access

The Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending August 31, 1950

Description: Technical report outlining various experiments that took place in the Oak Ridge Area Critical Mass Laboratory until August 31, 1950. Experiments took place in categories of critical experiments, experimental engineering, heat transfer, radiation damage, nuclear measurements, reactor physics, ARE reactor design, circulating fuel reactors, and circulating moderator reactors. [From Summary]
Date: December 4, 1950
Creator: Ellis, C. B. & Thompson, W. E.
open access

Alkyl Phosphoric Acids as Extraction Agents for Uranium

Description: The recent interest in tributyl phosphate as an extracting solvent for uranium indicated that consideration of n-butyl phosphoric acid for this application might be of interest if some way could be devised to overcome the manipulation and miscibility difficulties. It was found that if the material was placed in any one of a number of carrier solvents, it had a remarkably strong extractive effect on uranyl ion out of acid solutions without a salting agent present.
Date: January 27, 1950
Creator: Stewart, D. C., (Donald Charles), 1912-1996
open access

Altitude-Chamber Performance of British Roll-Royce Nene II Engine 4: Effect of Operational Variables on Temperature Distribution at Combustion-Chamber Outlets

Description: "Temperature surveys were made at the combustion-chamber outlets of a British Rolls-Royce Nene II engine. The highest mean nozzle-vane and mean gas temperatures were found to occur at a radius approximately 75% of the nozzle-vane length from the inner ring of the nozzle-vane assembly. Variations in engine speed, jet-nozzle area, simulated altitude, and simulated flight speed altered the temperature level but did not materially affect the pattern of radial temperature distribution" (p. 1).
Date: July 3, 1950
Creator: Huntley, Sidney C.
open access

Altitude-Chamber Performance of British Rolls-Royce Nene II Engine 3 - 18.00-Inch-Diameter Jet Nozzle

Description: An altitude-chamber investigation of British Rolls-Royce Nene II turbojet engine was conducted over range of altitudes from sea level to 65,000 feet and ram pressure ratios from 1.10 to 3.50, using an 18.00-inch-diameter jet nozzle. The 18.00-inch-diameter jet nozzle gave slightly lower values of net-thrust specific fuel consumption than either the 18.41- or the standard 18.75-inch-diameter jet nozzles at high flight speeds. At low flight speeds, the 18.41-inch-diameter jet nozzle gave the lowe… more
Date: July 10, 1950
Creator: Grey, Ralph E.; Brightwell, Virginia L. & Barson, Zelmar
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