National Advisory Committee for Aeronautics (NACA) - 45 Matching Results

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Accelerations and bottom pressures measured on a B-24D airplane in a ditching test

Description: From Introduction: "This report presents only that portion of the data from the first ditching which was to be used roughly establish the accelerations experienced by the pilot and the amount of water pressure to which the fuselage structure was subjected during the ditching."
Date: November 1944
Creator: Steiner, Margaret F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Tests of an NACA 66(215)-116, a=0.6 Airfoil With a 0.25c Slotted Flap for the Fleetwings XA-39 Airplane

Description: Report presenting testing in the two-dimensional low-turbulence tunnels on a 24-inch-chord model of the NACA 66(215)-116 a = 0.6 airfoil with a 0.25-chord slotted flap. The optimum flap pivot positions were found for three different conditions. The conditions were determined from a consideration of the landing, take-off, and strafing requirements of the airplane.
Date: November 1944
Creator: Cahill, Jones F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Application of Spring Tabs to Elevator Controls

Description: Equations are presented for calculating the stick-force characteristics obtained with a spring-tab type of elevator control. The main problems encountered in the design of a satisfactory elevator spring tab are to provide stick forces in the desired range, to maintain the force per g sufficiently constant throughout the speed range, to avoid undesirable "feel" of the control in ground handling or in flight at low airspeeds, and to prevent flutter. Examples are presented to show the design featu… more
Date: November 24, 1944
Creator: Phillips, William H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Axial Fatigue Tests at Zero Mean Stress of 24S-T Aluminum-Alloy Sheet With and Without a Circular Hole

Description: "Axial fatigue tests were made on 189 coupon specimens of 0.032-inch 24S-T aluminum-alloy sheet and a few supplementary specimens of 0.004-inch sheet. The mean load was zero. The specimens were restrained against lateral buckling by lubricated solid guides described in a previous report on this project. About two-thirds of the 0.032-inch specimens were plain coupons nominally free from stress raisers. The remainder contained a 0.1285-inch drilled hole at the center where the reduced section was… more
Date: November 1944
Creator: Brueggeman, W. C.; Mayer, M., Jr. & Smith, W. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bending and Shear Stresses Developed by the Instantaneous Arrest of the Root of a Cantilever Beam With a Mass at Its Tip

Description: Report discusses an investigation into the behavior of a cantilever beam in transverse motion with a mass at its tip when the root is suddenly brought to rest. Equations for determining the stresses, deflections, and accelerations that arise in the beam are also provided. This testing can be applied to the shock created in an airplane when landing and the vibrations that result.
Date: November 1944
Creator: Stowell, Elbridge Z.; Schwartz, Edward B.; Houbolt, John C. & Schmieder, Albert K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bending and Shear Stresses Developed by the Instantaneous Arrest of the Root of a Moving Cantilever Beam

Description: Report presenting a theoretical and experimental investigation of the behavior of a cantilever beam in transverse motion when its root is suddenly brought to rest. The results of both types of investigations are compared.
Date: November 1944
Creator: Stowell, Elbridge Z.; Schwartz, Edward B. & Houbolt, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Breaking Aircraft-Engine Oil Foams by Use of Electrically Charged Condenser Plates

Description: Report presenting a determination of the effectiveness of a charged condenser for breaking oil foams and to obtain data on which to base the design of such a device for mounting at the oil-tank inlet of an airplane. Results regarding the condenser-plate area and arrangement, wet-plate design, condenser voltage, oil temperature, water in oil, and some safety considerations are provided.
Date: November 1944
Creator: Pinkel, I. Irving
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cascade investigation of buckets for a modern aircraft turbosupercharger

Description: Report presenting a cascade investigation in two-dimensional flow in the 5-inch cascade tunnel and the 1-inch turbine-element testing apparatus to obtain a satisfactory bucket design for use in a modern aircraft turbosupercharger. Results regarding the root sections, pitch sections, and tip sections are provided.
Date: November 1944
Creator: Kantrowitz, Arthur & Erwin, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Charts for the Determination of Wing Torsional Stiffness Required for Specified Rolling Characteristics or Aileron Reversal Speed

Description: From Summary :"A series of charts are presented by which the wing torsional stiffness required to meet a given standard of rolling effectiveness may be quickly determined. The charts may also be used to obtain quickly the aileron reversal speed and the variation of the loss in rolling effectiveness with airspeed. The charts apply to linearly tapered wings and elliptical wings of tubular-shell construction having various aspect ratios with aileron span and location of ailerons as variables. In t… more
Date: November 9, 1944
Creator: Pearson, Henry A. & Aiken, William S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Correlation of the drag characteristics of a typical pursuit airplane obtained from high-speed wind-tunnel and flight tests

Description: In order to obtain a correlation of drag data from wind-tunnel and flight tests at high Mach numbers, a typical pursuit airplane, with the propeller removed, was tested in flight at Mach numbers up to 0.755, and the results were compared with wind-tunnel tests of a 1/3-scale model of the airplane. The tests results show that the drag characteristics of the test airplane can be predicted with satisfactory accuracy from tests in the Ames 16-foot high-speed wind tunnel of the Ames Aeronautical Lab… more
Date: November 2, 1944
Creator: Nissen, James M.; Gadeberg, Burnett L. & Hamilton, William T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Critical combinations of shear and transverse direct stress for an infinitely long flat plate with edges elastically restrained against rotation

Description: An exact solution and a closely concurring approximate energy solution are given for the buckling of an infinitely long flat plate under combined shear and transverse direct stress with edges elastically restrained against rotation. It was found that an appreciable fraction of the critical stress in pure shear may be applied to the plate without any reduction in the transverse compressive stress necessary to produce buckling. An interaction formula in general use was shown to be decidedly conse… more
Date: November 8, 1944
Creator: Batdorf, S. B. & Houbolt, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Ditching tests with a 1/10-size model of the Army A-20A airplane in Langley tank no.2 and on an outdoor catapult

Description: Testing of a dynamically similar model of an Army A-20A airplane to determine the best way to land the airplane in calm and rough water and to determine its probable ditching performance. Results regarding the effect of speed and attitude, effect of flap setting, effect of wind and seaway, effect of simulated damage, effect of sinking speed, effect of propellers, effect of gun blisters, and effect of weight are provided.
Date: November 1944
Creator: Jarvis, George A. & Steiner, Margaret F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Developed Width on Strength of Axially Loaded Curved Sheet Stringer Panels

Description: Report presenting compression tests on six 24S-T aluminum alloy curved sheet-stringer panels 12 inches in length and 24 inches in width, reinforced by six Zeo stringers spaced 4 inches between centers. The increase in developed width had no significant effect on the strain for buckling of sheet between stringers, the strain for buckling of sheet between rivets, the load carried per sheet bay, or the stress at failure.
Date: November 1944
Creator: McPherson, Albert E.; Fienup, Kenneth L. & Zibritosky, George
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Hinge-Moment Parameters on Elevator Stick Forces in Rapid Maneuvers

Description: Report presenting an investigation into the importance of stick force as a criterion of longitudinal stability with special reference to transient effects for maneuvers of short duration. The analysis showed that different combinations of elevator parameters which give the same stick force per unit acceleration in turns give widely different force variations during the entries into and recoveries from steady turns and during maneuvers of short duration such as abrupt pull-ups.
Date: November 1944
Creator: Jones, Robert T. & Greenberg, Harry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Lateral Shift of Center of Gravity on Rudder Deflection Required for Trim

Description: Report discusses the results of testing of rudder deflection for trim at low speeds in the critical wave-off condition. Depending on the lateral center-of-gravity location on the airplane, the useful load in the wings will change and the ability of the rudder to trim the airplane may be greatly improved.
Date: November 1944
Creator: Phillips, W. H.; Crane, H. L. & Hunter, P. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of tilt of the propeller axis on the longitudinal-stability characteristics of single-engine airplanes

Description: Report presenting the results of tests of a model of a single-engine airplane with two different tilts of the propeller axis. The results indicate that on a typical design, a 5 degree downward tilt of the propeller axis will considerably reduce the destabilizing effects of power.
Date: November 1944
Creator: Goett, Harry J. & Delany, Noel K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Estimates of the Vertical-Tail Loads of a Bell P-63A-1 Airplane (AAF No. 42-68889) in Accelerated Rolling Maneuvers Based on Flight Tests With Two Vertical-Tail Arrangements

Description: Report discussing the results of using an enlarged vertical tail on a P-63A-1 on directional stability. The tests included measurements of the amount of sideslip at various speeds and normal accelerations. Potential required modifications for increased performance using the larger tail are also described.
Date: November 30, 1944
Creator: Johnson, Harold I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Estimation of the Internal-Cooling Requirements of an Aircraft-Engine Cylinder When Using Oxygen Boost

Description: Report discusses a method developed to estimate the quantities of internal coolants required to prevent overheating of the aircraft cylinder when oxygen boost is applied. The formula and calculations related to inlet-air pressure, added oxygen, added water, added nitrogen, and total fluid weight are detailed.
Date: November 1944
Creator: Evvard, John C. & Moeckel, W. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Study of the Coating Found on Scuffed Cast-Iron Piston Rings During Operation in Nitrided-Steel Cylinders

Description: Report presenting cast-iron piston rings that were run in nitrided-steel cylinder barrels under scuffing conditions and showed a coating material on the scuffed areas. Only a few of the 14 etching reagents that were tried attacked the coating chemically, indicating good corrosion resistance. Results regarding the occurrence of coating, metallurgical characteristics, and chemical characteristics are provided.
Date: November 1944
Creator: Kittel, J. Howard & Vierthaler, Walter A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental verification of a simplified vee-tail theory and analysis of available data on complete models with vee tails

Description: An analysis has been made of available data on vee tail surfaces. Previously published theoretical studies of vee tails have been extended to include the control effectiveness and control forces in addition to the stability. Tests of two isolated tail surfaces with various amounts of dihedral provided a check of the theory. Methods for designing vee tails were also developed and are given in the present paper.
Date: November 14, 1944
Creator: Purser, Paul E. & Campbell, John P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Verification of the Rudder-Free Stability Theory for an Airplane Model Equipped with Rudders Having Negative Floating Tendency and Negligible Friction

Description: "An investigation has been made in the Langley free-flight tunnel to obtain an experimental verification of the theoretical rudder-free stability characteristics of an airplane model equipped with conventional rudders having negative floating tendencies and negligible friction. The model used in the tests was equipped with a conventional single vertical tail having rudder area 40 percent of the vertical tail area. The model was tested both in free flight and mounted on a strut that allowed free… more
Date: November 1944
Creator: McKinney, Marion O. & Maggin, Bernard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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F-3 and F-4 Engine Tests of Several High-Antiknock Components of Aviation Fuel

Description: Report discussing testing on triptane, hot-acid octane, diisopropyl, neohexane, mixed xylenes, cumene, benzene, toluene, and methyl tert-butyl ether in several blends to determine their knock-limited performance data in F-3 and F-4 engines at standard operating conditions. All of the blending agents examined were found to be usable, with concentrations varying depending on various thermodynamic properties.
Date: November 27, 1944
Creator: Imming, Harry S.; Barnett, Henry C. & Genco, Russell S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Fairing Compositions for Aircraft Surfaces

Description: Note presenting fairing compositions applied to aircraft surfaces, welds and junctions of metal plates, and rivet depressions to improve the aerodynamic efficiency of the airplane at high speeds. A method is described for formulating fairing compositions which have, within limits, desired coefficients of thermal expansion. Results regarding water-immersion tests, thermal expansion and softening temperature, temperature-cycle tests, and density are provided.
Date: November 1944
Creator: Turner, Philip S.; Doran, Jewel & Reinhart, Frank W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation at High Mach Numbers of Several Methods of Measuring Static Pressure on an Airplane Wing

Description: Report discusses an investigation into static pressures in subsonic and supersonic flow over an airplane wing as measured by static-pressure tubes, a static-pressure belt, and orifices flush with the wing surface. The results obtained from the three types of measuring devices and a comparison to theoretical calculations are presented.
Date: November 1944
Creator: Zalovcik, John A. & Daum, Fred L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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