National Advisory Committee for Aeronautics (NACA) - 173 Matching Results

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Determination of the Profile Drag of an Airplane Wing in Flight at High Reynolds Numbers

Description: Report presenting flight tests to determine the profile-drag coefficients of a portion of the original wing surface of an all-metal airplane and a portion of the wing made aerodynamically smooth and more nearly fair than the original section. Tests were also carried out to determine the point of transition from laminar to turbulent boundary layer and to determine the velocity distribution along the upper surface of the wing.
Date: 1939
Creator: Bicknell, Joseph
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Hydrodynamic and Aerodynamic Tests of a Family of Models of Seaplane Floats With Varying Angles of Dead Rise: N.A.C.A. Models 57-A, 57-B, and 57-C

Description: Report presenting testing of three models of V-bottom floats for twin-float seaplanes with varying angles of dead rise were tested in a tank and a wind tunnel. Results regarding the effect of angle of dead rise, height and amount of spray at hump speed, aerodynamic drag, effect of cross-sectional shape and load coefficients, and spray strips are provided.
Date: July 1939
Creator: Parkinson, John B.; Olson, Roland E. & House, Rufus O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests in the gust tunnel of a model of the XBM-1 airplane

Description: Report presenting testing of a dynamically scaled model of a Navy XBM-1 biplane in the gust tunnel to provide data for use in determining the structure of atmospheric gusts from measurements of the motions of the full-scale airplane in rough air. Records for two flights for several gradients were evaluated to give histories of events during passage through the gust.
Date: October 1939
Creator: Donely, Philip & Shufflebarger, C. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theory of Automatic Control of Airplanes

Description: "Methods of automatically controlling the airplane are reviewed. Equations for the controlled motion including inertia effects of the control are developed and methods of investigating the stability of the resulting fifth and higher order equations are presented. The equations for longitudinal and lateral motion with both ideal and non-ideal controls are developed in dimensionless form in terms of control parameters based on simple dynamic tests of the isolated control unit" (p. 1).
Date: April 1939
Creator: Weiss, Herbert K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Intermittent-flow coefficients of a poppet valve

Description: "Flow coefficients were determined for the inlet valve of a modern air-cooled cylinder during operation of the valve. The cylinder head with valves was mounted on a large tank that could be evacuated. Operating the valve with a rotating cam allowed air to flow through the valve into the evacuated tank. The change of pressure in the tank was a measure of the amount of air flowing though the valve in a given number of cycles. The flow coefficients were determined from the pressure across the valv… more
Date: April 1939
Creator: Waldron, C. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of Several Forms of Fixed Wing Slot in Combination With a Slotted Flap on an N.A.C.A. 23012 Airfoil

Description: Note presenting tests of several forms of fixed wing slot in a large-chord NACA 23012 airfoil in the closed-throat 7- by 10-foot wind tunnel. The airfoil extended completely across the test section so that two-dimensional flow was approximated. The data are presented in the form of tables of important aerodynamic characteristics for each slot tested and as curves of section lift, profile-drag, and pitching-moment coefficients.
Date: April 1939
Creator: Bamber, M. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A flight investigation of the distribution of ice-inhibiting fluids on a propeller blade

Description: Report presenting an investigation of the flow of ice-inhibiting fluids over the blade surfaces of a 12.5-foot-daimeter propeller in flight by discharging dyed fluids at various stations along the leading edges of the blades. The effects on the distribution of varying the fluid composition, the blade-surface roughness, and the orifice design were also observed.
Date: September 1939
Creator: Rodert, Lewis A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of an N.A.C.A. 23021 Airfoil With Two Arrangements of a 40-Percent-Chord Slotted Flap

Description: Note presenting an investigation in the 7- by 10-foot wind tunnel of an NACA 23021 airfoil with two arrangements of a 40-percent-chord slotted flap. The effect of slot shape, flap position, and flap deflection on the section aerodynamic characteristics was determined. Results regarding coefficients, precision, plain airfoils, and slotted-flap arrangements are provided.
Date: September 1939
Creator: Duschik, Frank
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Combined Beam-Column Stresses of Aluminum-Alloy Channel Sections

Description: The results of a research program to obtain design data on the strength of open-channel aluminum-alloy sections subjected to combined column and beam action. The results of the tests of about 70 specimens were graphed for stresses due to axial load and stresses due to bending loading as functions of length to radius of gyration of the specimens. From these graphs a design chart was derived that is suitable for ready use.
Date: September 1939
Creator: Gottlieb, R.; Thompson, T. M. & Witt, E. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Effect of Yawing on Lateral-Stability Characteristics 2: Rectangular N.A.C.A. 23012 Wing with a Circular Fuselage and a Fin

Description: Note presenting testing of an N.A.C.A. 23012 rectangular wing with rounded tips in combination with a fuselage of circular cross section at several angles of yaw in the NACA 7- by 10-foot wind tunnel. The model was tested as a high-wing, a midwing, and a low-wing monoplane; for each wing location, tests were made with two amounts of dihedral and with partial-span split flaps. Results regarding the wing and fuselage, fin and fuselage, and wing, fuselage, and fin are provided.
Date: September 1939
Creator: Bamber, M. J. & House, R. O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An instrument for estimating tautness of doped fabrics on aircraft

Description: Technical note presenting the design and use of a spring-loaded tautness meter that can be used in both horizontal and vertical positions to compare the tautness of various panels. Results of tests made on the fabric coverings of various airplanes are reported and discussed.
Date: September 1939
Creator: Kline, Gordon M. & Schiefer, Herbert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Resume of Air-Load Data on Slats and Flaps

Description: "A resume of the generally available test data regarding air loads on slats and flaps is presented and data attained up to the fall of 1938 are included. The data are given in the form of N.A.C.A. standard coefficients of air forces and moments on the lift-increasing device and, when available, the aerodynamic characteristics of the combined wing and high-lift device are included. Slats of the Handley Page type, fixed auxiliary airfoils, and flaps of several different types are covered" (p. 1).
Date: March 1939
Creator: Wenzinger, Carl J. & Rogallo, Francis M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some Elementary Principles of Shell Stress Analysis With Notes on the Use of the Shear Center

Description: "The analysis of various types of shell under combined bending and torsion is discussed. The calculation and the use of the shear center are touched upon as incidental problems. Twelve fully worked numerical examples are given in an appendix" (p. 1).
Date: March 1939
Creator: Kuhn, Paul
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some fundamental considerations in regard to the use of power in landing an airplane

Description: From Summary: "This note is concerned with the effect of power on landing speed and apparent maximum lift coefficient. It is shown that when secondary effects are neglected, the maximum available increase in lift due to power is equal to the thrust being developed. If the increase in lift due to power is expressed in coefficient form, very high values may be shown under conditions which, on analysis, are found to be wholly impracticable in flight."
Date: March 1939
Creator: Diehl, Walter S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Adhesion of Ice in Its Relation to the De-Icing of Airplanes

Description: From Summary: "The various possible means of preventing ice adhesion on airplane surfaces are critically reviewed. Results are presented of tests of the adhesives forces between ice and various solid and liquid forces. It is concluded that the de-icing of airplane wings by heat from engine exhaust shows sufficient promise to warrant full-scale tests. For propellers, at least, and possibly for certain small areas such as windshields, radio masts, etc. the use of de-icing or adhesion-preventing l… more
Date: August 1939
Creator: Rothrick, A. M. & Selden, R. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Profile-Drag and Boundary-Layer Measurements Obtained in Flight and in the Full-Scale Wind Tunnel

Description: "The effect of the existing turbulence in the full scale tunnel was determined from measurements of the profile drag of an N-22 section by the momentum method under corresponding conditions in flight and the tunnel. The transition-point location on the upper surface of the air-foil was also determined from velocity surveys in the boundary layer. The measurements were made at section lift coefficients from 0.480 to 0.635 with a range of Reynolds Numbers from 4,600,000 to 3,900,000. The results s… more
Date: March 1939
Creator: Goett, Harry J. & Bicknell, Joseph
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tandem Air Propellers

Description: "Tests of 2-blade, adjustable-pitch, counter rotating tandem model propellers, adjusted to absorb equal power at maximum efficiency, were made at Stanford University. The characteristics, for 15 degrees, 25 degrees, 35 degrees, and 45 degrees pitch settings at 0.75 R of the forward propeller and for 8-1/2 percent, 15 percent, and 30 percent diameter spacings, were compared with those of 2-blade and 4-blade propellers of the same blade form" (p. 1).
Date: February 1939
Creator: Lesley, E. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Local Instability of Centrally Loaded Columns of Channel Section and Z-Section

Description: "Charts are presented for the coefficients in formulas for the critical compressive stress at which cross-sectional distortion begins in a thin-wall member with either a channel section or a Z-section with identical flanges. The energy method of Timoshenko was used in the theoretical calculations required for the construction of the charts. The deflection equations were carefully selected to give good accuracy. The calculation of the critical compressive stress at stresses beyond the elastic ra… more
Date: August 1939
Creator: Lundquist, Eugene E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Torsional stability of aluminum alloy seamless tubing

Description: Torsion tests were made on 51ST aluminum-alloy seamless tubes having diameter-to-thickness ratios of from 77 to 139 and length-to-diameter ratios of from 1 to 60. The torsional strengths developed in the tubes which failed elastically (all tubes having lengths greater than 2 to 6 times the diameter) were in most cases within 10 percent of the value indicated by the theories of Donnel, Timoshenko, and Sturm, assuming a condition of simply supported ends.
Date: March 1939
Creator: Moore, R. L. & Paul, D. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Frequency of Torsional Vibration of a Tapered Beam

Description: "A solution for the equation of torsional vibration of tapered beams has been found in terms of Bessel functions for beams satisfying the following conditions: (a) the cross sections along the span are similar in shape; and (b) the torsional stiffness of a section can be expressed as a power of a linear function of distance along the span. The method of applying the analysis to actual cases has been described. Charts are given from which numerical values can be immediately obtained for most cas… more
Date: March 1939
Creator: Coleman, Robert P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Propeller Tests to Determine the Effect of Number of Blades at Two Typical Solidities

Description: "Propellers with equal total blade area, but with different numbers, were tested at Stanford University. The tests show generally that, for equal total blade area, propellers with the larger number of blades absorb the greater power and, provided hubs have equal drag, develop the higher efficiency. It is shown that the differences found are in agreement, qualitatively, with what might be predicted from simple blade-element theory" (p. 1).
Date: April 1939
Creator: Lesley, E. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of an N.A.C.A. 23012 Airfoil with a slotted deflector flap

Description: Section aerodynamic characteristics of a large-chord N.A.C.A. 23012 airfoil with a slotted deflector flap were obtained in the N.A.C.A. 7- by 10-foot wind tunnel. The characteristics of an N.A.C.A. slotted flap and of a simple split flap are included for comparison. The slotted deflector flap was found to have a somewhat lower maximum lift coefficient and somewhat higher drag at high lift coefficients than the N.A.C.A. slotted flap. The high drag of the open slot with the deflector flap neutral… more
Date: April 1939
Creator: House, R. O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Physical Properties of Synthetic Resin Materials

Description: "A study was made to determine the physical properties of synthetic resins having paper, canvas, and linen reinforcements, and of laminated wood impregnated with a resin varnish. The results show that commercial resins have moduli of elasticity that are too low for structural considerations. Nevertheless, there do exist plastics that have favorable mechanical properties and, with further development, it should be possible to produce resin products that compare favorably with the light-metal all… more
Date: March 1939
Creator: Fishbein, Meyer
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effects of Surface Waviness and of Rib Stitching on Wing Drag

Description: "Surface waviness and rib stitching have been investigated as part of a series of tests to determine the effects on wing drag of common surface irregularities. The tests were made in the N.A.C.A. 8-foot high-speed wind tunnel at Reynolds Numbers up to 17,000,000. The results of the tests showed that the waviness common to airplane wings will cause no serious increase in drag unless the waviness exists on the forward part of the wing, where it may cause premature transition or premature compress… more
Date: August 1939
Creator: Hood, Manley J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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