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Lift and drag coefficients for the Bell X-1 airplane (8-percent-thick wing) in power-off transonic flight

Description: Report presenting drag coefficients determined by the accelerometer method for the Bell X-1 airplane with 8-percent-thick wing and 6-percent-thick tail in power-off flight over a range of Mach numbers and lift coefficients. Results regarding the variation of computed lift and drag coefficients, variation of lift coefficient with Mach number, and effect of Mach number on lift-drag ratio are provided.
Date: June 25, 1951
Creator: Carman, L. Robert & Carden, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation of a Submerged Inlet and a Nose Inlet in the Transonic Flight Range With Free-Fall Models

Description: Memorandum presenting an NACA submerged inlet and an NACA series I nose inlet installed in bodies of 12.4 fineness ratio to determine the drag and pressure-recovery characteristics of each body-inlet configuration. The tests were conducted with large-scale free-fall models released at an altitude of 40,000 feet, for mass-flow ratios of about 0.4 and 0.7 over a Mach number range of about 0.70 to 1.10. Results regarding drag and ram-recovery ratios are provided.
Date: June 18, 1951
Creator: Selna, James
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary study of circulation in an apparatus suitable for determining corrosive effects of hot flowing liquids

Description: "A simple apparatus particularly applicable to the determination of the corrosive effects of flowing liquid metals on structural materials is described. In this apparatus, flow of the liquid medium at known velocities may be induced in toroidal shaped channels fabricated from the test structural material only, with no pump, valves, or flow meter required. A circulating velocity of 25 ft/sec has been obtained in preliminary tests and no basic limitation on increasing the speed was encountered" (… more
Date: June 29, 1951
Creator: Desmon, Leland G. & Mosher, Don R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Observations on Bauschinger Effect in Copper and Brass

Description: Memorandum presenting a study of the effect of prestrain in tension upon the stress-strain characteristics in compression for copper and brass. The residual stress phenomenon known as the Bauschinger effect is of primary importance in cyclic loading, inasmuch as it serves to reduce the yield strength of plastically strained metal to deformation of the opposite sign.
Date: June 19, 1951
Creator: Schwartzbart, H.; Jones, M. H. & Brown, W. F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Four Wings of Sweepback Angles 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees, NACA 65A006 Airfoil Section, Aspect Ratio 4, and Taper Ratio 0.6 in Combination With a Fuselage at High Subsonic Mach Numbers and at a Mach Number of 1.2

Description: Report discussing an investigation of the effect of sweepback angle on wing-fuselage characteristics at a subsonic and a supersonic Mach number. Lift, drag, and pitching-moment coefficients, downwash-angle, and total-pressure measurements are all provided.
Date: June 6, 1951
Creator: Luoma, Arvo A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: twisted and cambered triangular wing of aspect ratio 2 with NACA 0003-63 thickness distribution

Description: This report presents the results of an investigation to ascertain the lift, drag, and pitching moment of a wing-body combination having a triangular wing of aspect ratio 2 with NACA 0003-63 thickness distribution in streamwise planes and twisted and cambered for a nearly elliptical span load distribution. Results are shown for Mach numbers from 0.60 to 0.90 and from 1.30 to 1.70 at Reynolds numbers of 3.0 million and 7.5 million.
Date: June 12, 1951
Creator: Hall, Charles F. & Heitmeyer, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Instrumentation for Recording Transient Performance of Gas-Turbine Engines and Control Systems

Description: Report presenting design features for the instrumentation used in a study of the transient performance of gas-turbine engines and control systems. The dynamic characteristics of the instrumentation are discussed and examples of typical acceleration data for a controlled and an uncontrolled engine are provided.
Date: June 27, 1951
Creator: Delio, Gene J. & Schwent, Glennon V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-Speed Characteristics of a Wing Having 63 Degrees Sweepback and Uniform Camber

Description: Memorandum presenting low-speed tests of a semispan tapered wing with the leading edge swept back 63 degrees and with the NACA 0010 section cambered for a lift coefficient of 1.0 perpendicular to the leading edge to determine the extent to which stability characteristics could be improved by cambering the wing.
Date: June 26, 1951
Creator: Rose, Leonard M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure-distribution measurements over a 45 degree sweptback wing at transonic speeds by the NACA wing-flow method

Description: Report presenting measurements of pressure made over the chord of a swept-wing model at four stations along the span by the NACA wing-flow method. The model was an untapered 45 degree sweptback wing of aspect ratio 3.5 with 2-inch-chord NACA 65-210 airfoil sections normal to the leading edge. Results regarding the chordwise pressure distributions and spanwise distributions of section lift, drag, and pitching moment.
Date: June 25, 1951
Creator: Danforth, Edward C. B. & O'Bryan, Thomas C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An experimental study at moderate and high subsonic speeds of the flow over wings with 30 degrees and 45 degrees of sweepforward in conjunction with a fuselage

Description: Report presenting pressure distributions and wake measurements for wings with 30 and 45 degrees of sweepforward, in conjunction with a midwing fuselage, at Mach numbers up to 0.96. The wings had an NACA 65-210 section, a taper ratio of 0.38, and aspect ratios of 7.5 and 5.2. Results regarding pressure distributions, wake measurements, and corrections are provided.
Date: June 15, 1951
Creator: Whitcomb, Richard T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Tapered Wings Having Aspect Ratios of 4, 6, and 8, Quarter-Chord Lines Swept Back 45 Degrees, and NACA 63(Sub 1)a012 Airfoil Sections: Transonic-Bump Method

Description: Report presenting testing of a series of three wings over a range of Mach numbers by the use of the transonic-bump technique. The lift, drag, pitching-moment, and root-bending-moment data of wings of a variety of aspect ratios but with the same quarter-chord lines and airfoil sections were obtained.
Date: June 13, 1951
Creator: Polhamus, Edward C. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tabulated Pressure Coefficients and Aerodynamic Characteristics Measured on the Wing of the Bell X-1 Airplane in an Unaccelerated Stall and in Pull-Ups at Mach Numbers of 0.74, 0.75, 0.94, and 0.97

Description: "Tabulated pressure coefficients and aerodynamic characteristics are presented for six spanwise stations on the left wing of the Bell X-1 research airplane. The data were obtained in an unaccelerated stall and in pull-ups at Mach numbers of 0.74, 0.75, 0.94, and 0.97" (p. 1).
Date: June 19, 1951
Creator: Smith, Lawrence A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Camera for Photographing Cloud Droplets in Natural Suspension in the Atmosphere

Description: "A camera designed for use in flight has been developed by the NACA Lewis laboratory to photograph cloud droplets in their natural suspension in the atmosphere. A magnification of 32 times is employed to distinguish for measurement purposes all sizes of droplets greater than 5 microns in diameter. Photographs can be taken at flight speeds up to 150 miles per hour at 5-second intervals, A field area of 0.025 square inch is photographed on 7-inch-width roll film accommodating 40 exposures on an 1… more
Date: June 29, 1951
Creator: McCullough, Stuart & Perkins, Porter J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An experimental study at moderate and high subsonic speeds of the flow over wings with 30 degrees and 45 degrees of sweepback in conjunction with a fuselage

Description: Report presenting pressure distributions, wake measurements, and tuft patterns for wings with 30 and 45 degrees of sweepback in conjunction with a midwing fuselage at Mach numbers to 0.96. The wings have an NACA 65-210 section, a taper ratio of 2.6:1, and aspect ratios of 7.5 and 5.2. The study indicated that when the Mach number reached high subsonic values at low angles of attack, the locations of peak negative pressure coefficients on the upper surfaces of the sections near the wing-fuselage… more
Date: June 15, 1951
Creator: Whitcomb, Richard T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-speed longitudinal and wake air-flow characteristics at a Reynolds number of 5.5 x 10(exp 6) of a circular-arc 52 degrees sweptback wing with a fuselage and a horizontal tail at various vertical positions

Description: Report presenting an investigation in the 19-foot pressure tunnel to determine the effects of a fuselage and a horizontal tail located at various vertical positions on the low-speed longitudinal characteristics of a circular-arc 52 degree sweptback wing. Results regarding the effect of fuselage on longitudinal characteristics of the wing, effect of tail position on stability and tail effectiveness, and air-flow characteristics are provided.
Date: June 19, 1951
Creator: Foster, Gerald V. & Griner, Roland F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation in the Ames 12-Foot Pressure Wind Tunnel of a Model Horizontal Tail of Aspect Ratio 3 and Taper Ratio 0.5 Having the Quarter-Chord Line Swept Back 45 Degrees

Description: Memorandum presenting an investigation to evaluate the effect of Reynolds number and Mach number on the aerodynamic characteristics of a horizontal tail of aspect ratio 3 equipped with a plain, sealed, full-span elevator. The line joining the quarter-chord points of the airfoil sections was swept back 45 degrees and the sections perpendicular to this line were the NACA 64A010. Results regarding the effect of Reynolds number and effects of leading-edge roughness and elevator-nose seal are provid… more
Date: June 25, 1951
Creator: Kolbe, Carl D. & Bandettini, Angelo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of Flow in the Rotating Passages of a 48-Inch Impeller at Low Tip Speeds

Description: 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… more
Date: June 26, 1951
Creator: Michel, Donald J.; Ginsburg, Ambrose & Mizisin, John
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Dynamic Lateral Stability

Description: The paper presents flight measurements of the dynamic lateral stability of the D-558-II (BuAero No. 37974) research airplane. Data are presented for a range of calibrated airspeed from 167 miles per hour to 474 miles per hour.
Date: June 18, 1951
Creator: Stillwell, W. H. & Wilmerding, J. V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Characteristics of Four Nose Inlets as Measured at Mach Numbers Between 1.4 and 2.0

Description: Memorandum presenting the pressure recovery, mass flow, and axial force of four bodies with nose inlets measured at Mach numbers between 1.4 and 2.0 and angles of attack of 0, 3, 6, and 9 degrees. The drag coefficients of axially symmetric diffusers operating at the maximum mass-flow rates were calculated from schileren photographs of the head shock waves and frictional drag considerations. Results regarding open-nose diffusers and conical-shock diffusers are provided.
Date: June 25, 1951
Creator: Brajnikoff, George B. & Rogers, Arthur W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The torsional deflections of several propellers under operating conditions

Description: Report presenting propeller-blade torsional-deflection data obtained during an investigation of the pressure distribution on constant-chord solid aluminum-alloy blades differing only in camber and thickness. Testing indicated that thinner blades were able to produce greater amounts of deflection. Results regarding torsional deflections are also provided.
Date: June 22, 1951
Creator: Gray, W. H. & Allis, A. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 4 with 3-percent-thick, biconvex section

Description: Report presenting a wing-body combination with a plane triangular wing of aspect ratio 4 and 3-percent-thick, biconvex sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: June 8, 1951
Creator: Heitmeyer, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-flow investigation of the characteristics of seven unswept, untapered airfoils of aspect ratio 8.0

Description: Report presenting testing of a series of seven 10-percent-thick unswept and untapered airfoils of aspect ratio 8.0 using the wing-flow method at a range of Mach numbers. The most significant characteristic noted was the occurrence of an unstable pitching moment variation with angle of attack for small angles of attack at Mach numbers of 0.85 to 0.90 for all airfoils with a conventional thickness distribution. Results regarding lift characteristics, moment characteristics, and drag characteristi… more
Date: June 13, 1951
Creator: Crane, Harold L. & Adams, James J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Zero-Lift Drag Determined by Flight Tests at Transonic Speeds of Pylon, Underslung, and Symmetrically Mounted Nacelles at 40 Percent Semispan of a 45 Degrees Sweptback Wing and Body Combination

Description: Report presenting the effect on drag of varying the vertical position of a nacelle at 40 percent semispan of a 45 degree sweptback wing and body combination as determined by transonic flight tests at zero lift. Three nacelle positions were investigated: a pylon mounted nacelle, an underslung nacelle, and a symmetrically mounted nacelle. Results regarding total drag coefficient and maximum wing-tip helix angle are provided.
Date: June 25, 1951
Creator: Hoffman, Sherwood
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ditching Investigation of a 1/24-Scale Model of the Douglas C-124 Airplane

Description: "An investigation of a 1/24- scale dynamically similar model of the Douglas C-124 airplane was made to determine the ditching characteristics and proper technique for ditching the airplane. Various conditions of damage, landing attitude, flap setting, and speed were investigated. The behavior of the model was determined from visual observations, motion- picture records, and time-history deceleration records. The results of the investigation are presented in table form, photographs, and curves" … more
Date: June 18, 1951
Creator: Fisher, Lloyd J. & Windham, John O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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