Technical Report Archive & Image Library (TRAIL) - 269 Matching Results

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The Effect of Air Jets Simulating Chines or Multiple Steps on the Hydrodynamic Characteristics of a Streamline Fuselage

Description: Memorandum presenting preliminary tests in order to determine the effect of forced ventilation on the hydrodynamic characteristics of a scale model of a streamline fuselage of a hypothetical transonic airplane. The forced ventilation consisted of air ejected at about 300 feet per second through small orifices distributed over the fuselage bottom in a series of patterns simulating chines or multiple steps. Results regarding resistance, effective hydrodynamic lift, trim, spray, and air flow are p… more
Date: January 7, 1949
Creator: Weinflash, Bernard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of airfoil section and tip tanks on the aerodynamic characteristics at high subsonic speeds of an unswept wing of aspect ratio 5.16 and taper ratio 0.61

Description: Report presenting an investigation of the effect of two wing sections and a tip tank on the aerodynamic characteristics of a rigid unswept wing in the high-speed tunnel over a Mach number range of 0.60 to 0.90. Results regarding the effect of original airfoil sections, effect of modifications to Section B, effect of tip tank, and characteristics of the tip tank in the presence of the wing are provided.
Date: December 1, 1949
Creator: Silvers, H. Norman & Spreeman, Kenneth P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of an Increase in Hull Length-Beam Ratio From 15 to 20 on the Hydrodynamic Characteristics of Flying Boats

Description: Report presenting an investigation of the effect of hull length-beam ratio on the hydrodynamic characteristics of flying boats that extend to a length-beam ratio of 20. The results are compared with flying boats having a length-beam ratio of 15. Results regarding longitudinal stability, spray characteristics, take-off performance, taxiing and take-off behavior in waves, landing behavior in waves, and a summary chart are provided.
Date: August 24, 1949
Creator: Carter, Arthur W. & Whitaker, Walter E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Blade-Section Thickness Ratios on the Aerodynamic Characteristics of Related Full-Scale Propellers at Mach Numbers Up to 0.65

Description: Report discussing an investigation of two full-scale NACA propellers at a range of blade angles and at speeds of up to 500 miles per hour. The results are compared to previous investigations of five NACA propellers to evaluate the effects of blade-section thickness ratios on propeller characteristics.
Date: June 6, 1949
Creator: Maynard, Julian D. & Steinberg, Seymour
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of hot-gas bleedback ice prevention on performance of a turbojet engine with fixed-area tail-pipe nozzle

Description: Report presenting the results of an analytical investigation, which demonstrated that the inlet of a turbojet engine can be protected from ice accretions by bleeding hot gases from other locations within the engine to the inlet without undue loss in thrust. Results regarding the bleedback requirements, engine performance, effect of nozzle area, mixing efficiency, and seriousness of thrust losses are provided.
Date: May 16, 1949
Creator: Dietz, Robert O., Jr. & Krebs, Richard P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of rate of change of angle of attack on the maximum lift coefficient of a pursuit airplane

Description: Report presenting an investigation of the effect of the rate of change of angle of attack on the maximum lift coefficient of a pursuit airplane equipped with a low-drag-type wing in stalls of varying abruptness over a range of Mach and Reynolds numbers. Maximum lift coefficients were found to increase linearly with increasing rate of change of angle of attack per chord length of travel up to the maximum rate attained in the tests.
Date: January 20, 1949
Creator: Gadeberg, Burnett L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Rear Chine Strips on the Take-Off Characteristics of a High-Speed Airplane Fitted With NACA Hydro-Skis

Description: "Results are presented from tank take-off tests of a dynamic model of a hypothetical high-speed airplane fitted with NACA hydro-skis and having the transverse curvature of the lower rear portion of the fuselage broken by small longitudinal chine strips. For the configuration tested, both trim and resistance were considerably reduced by the addition of the strips from the speed at which the ski emerged to the speed at which the rear of the fuselage came clear of the water. The results indicate t… more
Date: March 17, 1949
Creator: Ramsen, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Span and Deflection of Split Flaps and Leading-Edge Roughness on the Longitudinal Stability and Gliding Characteristics of a 42 Degree Sweptback Wing Equipped With Leading-Edge Flaps

Description: Report discussing the effect of half-span and full-span split flaps through a deflection range on the low-speed, longitudinal characteristics of a sweptback wing with a round-nose, extensible leading-edge flap. Information about the effect of split-flap deflection on lift and stalling characteristics, effect of split flaps on gliding characteristics, and effect of leading-edge roughness on longitudinal stability is presented.
Date: June 21, 1949
Creator: Pratt, George L. & Bollech, Thomas V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Sweepback on the Low-Speed Static and Rolling Stability Derivatives of Thin Tapered Wings of Aspect Ratio 4

Description: Report discussing an investigation to determine the effect of sweepback on the static and rolling stability derivatives of a series of wings with a taper ratio of 0.6 and an aspect ratio of 4. The influence on the straight-flow characteristics, rolling-flow characteristics, and aileron characteristics are provided.
Date: August 9, 1949
Creator: Letko, William & Wolhart, Walter D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of temperature on performance of several ejector configurations

Description: Report presenting an investigation to determine the effect of the primary-jet temperature on the performance of several ejector configurations. The performance of ejectors expressed in terms of the ratio of weight of secondary air flow to primary air flow was found to be affected by temperature in two ways.
Date: June 13, 1949
Creator: Wilsted, H. D.; Huddleston, S. C. & Ellis, C. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of the propeller slipstream on the characteristics of submerged inlets

Description: Report presenting a wind-tunnel investigation to determine the effect of propeller operation on the characteristics of submerged inlets. The tests were performed with a model of a hypothetical fighter airplane powered by a turbine-propeller unit. The propeller had eight blades with thin airfoil shanks and dual rotation and the submerged inlets were placed in the fuselage behind the propeller and forward of the wing.
Date: September 9, 1949
Creator: Delany, Noel K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of high-lift and stall-control devices, fuselage, and horizontal tail on a wing swept back 42 degrees at the leading edge and having symmetrical circular-arc airfoils sections at a Reynolds number of 6.9 x 10(exp 6)

Description: Report presenting an investigation of the low-speed characteristics of a wing swept back 42 degrees at the leading edge and having various high-lift and stall-control devices and fuselage and horizontal tail vertical positions. Results regarding the characteristics of the basic wing, leading-edge flap investigation, wing fuselage investigation, and horizontal tail investigation are provided.
Date: April 20, 1949
Creator: Woods, Robert L. & Spooner, Stanley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effects of Horizontal-Tail Location and Wing Modifications on the High-Speed Stability and Control Characteristics of a 01.17-Scale Model of the McDonnell XF2H-1 Airplane (TED No, NACA DE336)

Description: "An additional series of high-speed wind-tunnel tests of a modified 0.17-scale model of the McDonnell XF2H-1 airplane was conducted to evaluate the effects of a reduction in the thickness-to-chord ratios of the tail planes, the displacement of the horizontal tail relative to the vertical tail, and the extension of the trailing edge of the wing. Two tail-intersection fairings designed to improve the flow at the tail were also tested. The pitching-moment characteristics of the model were improved… more
Date: October 14, 1949
Creator: Emerson, Horace F. & Axelson, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Mach number and sweep on the damping-in-roll characteristics of wings of aspect ratio 4

Description: An investigation of the damping-in-roll characteristics of three wings with an aspect ratio of 4, a taper ratio of 0.6, three sweep angles at the quarter chord line, and the NACA 65A006 section as determined through a range of Mach numbers and angles of attack.
Date: June 27, 1949
Creator: Kuhn, Richard E. & Myers, Boyd C., II
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effects of scale and test technique on the validity of small-scale measurements of the aerodynamic characteristics of a wing with the leading edge swept back 63 degrees

Description: Report presenting the lift and pitching-moment characteristics of two wings of the same plan form measured over a range of Mach and Reynolds numbers using the wing-flow method. One wing had a symmetrical airfoil section and no twist, while the other was cambered and twisted to support a uniform load distribution at a lift coefficient of 0.25 at Mach number 1.5. A comparison with previous testing is also provided.
Date: December 9, 1949
Creator: Rolls, L. Stewart
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of several leading-edge modifications on the stalling characteristics of a 45 degree swept-forward wing

Description: Report presenting an investigation to determine the effects of several leading-edge modifications on the maximum lift and pitching-moment characteristics on a large-scale 45 degree swept-forward wing. A full-span leading-edge flap deflected 30 degrees down tended to give the largest gain of maximum lift. Results regarding the plain leading-edge flaps and cambered nose are explored.
Date: June 14, 1949
Creator: McCormack, Gerald M. & Cook, Woodrow L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Some Airfoil-Section Variations on Wing-Aileron Rolling Effectiveness and Drag as Determined in Free Flight at Transonic and Supersonic Speeds

Description: Report presenting an investigation in free flight of the rolling effectiveness of plain ailerons in conjunction with wings having 0 and 45 degrees sweepback with several airfoil sections. Results regarding the rolling characteristics of rectangular and sweptback-wing configurations and drag measurements are provided.
Date: July 22, 1949
Creator: Sandahl, Carl A.; Bland, William M., Jr. & Strass, H. Kurt
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of systematic changes of trailing-edge angle and leading-edge radius on the variation with Mach number of the aerodynamic characteristics of a 10-percent-chord-thick NACA airfoil section

Description: Report presenting the results of a wind-tunnel investigation of the effects of variation of trailing-edge angle and leading-edge radius on the aerodynamic characteristics of a 10-percent-chord-thick airfoil section at a range of Mach numbers.
Date: September 26, 1949
Creator: Summers, James L. & Graham, Donald J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of wing-tip turrets on the aerodynamic characteristics of a typical bomber-wing model

Description: Report presenting wind-tunnel tests up to a Mach number of 0.85 to determine the effects of wing-tip gun turrets on the aerodynamic characteristics of a typical bomber-wing model. Lift, drag, and pitching-moment data are presented for the wing alone; for the wing with the turrets in the clean condition; and for the wing and the turrets with guns and sighting equipment. The turrets had negligible effect on the lift and pitching-moment characteristics of the wing.
Date: March 28, 1949
Creator: Boddy, Lee E. & Sutton, Fred B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Electric Thrust Meter Suitable for Flight Investigation of Propellers

Description: A lightweight instrument that utilizes resistance-wire electric strain gases to measure propeller-shaft thrust has been developed. A wind-tunnel investigation on a propeller installed, on a single-engine pursuit airplane showed that the instrument gave a reliable indication of propeller-shaft thrust to an accuracy of +/-2 percent within its calibrated range. No attempt was made to determine the relation of indicated shaft thrust to net propeller thrust.
Date: May 9, 1949
Creator: Perkins, Porter J., Jr. & Millenson, Morton B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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
Partner: UNT Libraries Government Documents Department
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An Empirical Method for Estimating Trailing-Edge Loads at Transonic Speeds

Description: Memorandum presenting an analysis of selected experimental pressure-distribution data at transonic speeds for the purpose of deriving an empirical method which may be used for estimating the trailing-edge loads and bending moments at the design stage. The trailing-edge normal-force and bending-moment coefficients calculated by the derived method follow the general trend of the experimental data and appear to be a guide where specifically applicable chordwise pressure-distribution data at transo… more
Date: October 6, 1949
Creator: Skopinski, T. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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
Partner: UNT Libraries Government Documents Department
open access

Estimation of Lift and Drag of Airfoils at Near Sonic Speeds and in the Presence of Detached Shock Waves

Description: Report presenting a semiempirical method of estimating the forces on airfoil at near sonic speeds and in the presence of detached shock waves. The calculated values were found to be in good agreement with wind-tunnel testing of the forces on sharp-nose airfoils and two-dimensional wings.
Date: February 23, 1949
Creator: Mayer, John P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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