National Advisory Committee for Aeronautics (NACA) - 27 Matching Results

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Aerodynamic characteristics of the NACA 8-H-12 airfoil section at six Reynolds numbers from 1.8 x 10(exp 6) to 11.0 x 10(exp 6)

Description: Report presenting an investigation in the two-dimensional low-turbulence pressure tunnel to determine the aerodynamic characteristics of the NACA 8-H-12 airfoil section at four Reynolds numbers. The section lift, drag, and pitching-moment characteristics are presented for smooth and rough surface conditions. Generally, no unusual scale effects are present for either condition.
Date: December 1949
Creator: Schaefer, Raymond F. & Smith, Hamilton A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Study of a Wing-Fuselage Combination Employing a Wing Swept Back 63 Degrees: Effects at Subsonic Speeds of a Constant-Chord Elevon on a Wing Cambered and Twisted for a Uniform Load at a Lift Coefficient of 0.25

Description: Report presenting testing of a cambered and twisted wing with constant-chord elevons with a slender fuselage to determine the longitudinal and lateral control from the elevons for a range of Mach numbers. Results regarding lift, drag, pitching-moment, and rolling-moment characteristics for various elevon deflections are provided.
Date: December 5, 1949
Creator: Jones, J. Lloyd & Demele, Fred A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of means of improving the uncontrolled lateral motions of personal airplanes

Description: From Summary: "The purpose of this investigation was to determine whether such airplanes could be made to fly uncontrolled for an indefinite period of time without getting into dangerous attitudes and for a reasonable period of time (one to three minutes) without deviating excessively from their original course. The results of this analysis indicated that the uncontrolled motions of a personal airplane could be made safe as regards spiral tendencies and could be greatly improved as regards main… more
Date: December 1949
Creator: McKinney, Marion O., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparative Tests of the Rolling Effectiveness of Constant-Chord, Full-Delta, and Half-Delta Ailerons on Delta Wings at Transonic and Supersonic Speeds

Description: Report presenting comparative tests of the rolling power of plain constant-chord, full-delta, and half-delta ailerons on delta wings with varying degrees of sweepback were tested on rocket-propelled test vehicles. Results regarding the effect of leading-edge sweepback, a comparison of rolling effectiveness, and comparison with theory are provided.
Date: December 12, 1949
Creator: Sandahl, Carl A. & Strass, H. Kurt
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Effectiveness of Coordinated Turns and Level Sideslips for Correcting Lateral Displacement During Landing Approaches

Description: Memorandum presenting a calculation of the amount of possible correction for coordinated turns with limited bank angle and level sideslips for a large transport airplane, the C-54D. The results indicate that for all instances from the end of the runway, coordinated turns are the more effective maneuver.
Date: December 15, 1949
Creator: Faber, Stanley
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Ditching Investigation of a 1/18-Scale Model of the North American B-45 Airplane

Description: An investigation of a 1/18-scale dynamically similar model of the North American B-45 airplane was made to observe the ditching behavior and determine the proper landing technique to be used in an emergency water landing. Various conditions of damage were simulated to determine the behavior which probably would occur in a full-scale ditching. The behavior of the model was determined from high-speed motion-picture records, time-history acceleration records, and visual observations. It was conclu… more
Date: December 22, 1949
Creator: Fisher, Lloyd J. & Thompson, William C.
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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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 wing flexibility and variable air lift upon wing bending moment during landing impacts of a small seaplane

Description: From Summary: "A smooth-water-landing investigation was conducted with a small seaplane to obtain experimental wing-bending-moment time histories together with time histories of the various parameters necessary for the prediction of wing bending moments during hydrodynamic forcing functions. The experimental results were compared with calculated results which include inertia-load effects and the effects of air-load variation during impact. The responses of the fundamental mode were calculated w… more
Date: December 21, 1949
Creator: Merten, Kenneth F. & Beck, Edgar 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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Experimental investigation at supersonic speeds of side scoops employing boundary-layer suction

Description: Report presenting the pressure-recovery characteristics of a model with two scoops situated on the aft position of a long forebody and connected through diffusors to a common settling chamber at a range of Mach numbers. The effects of interaction between the flow in the two air-induction systems and of varying the mass flow through the boundary-layer scoops were studied. Results at several different angles of attack are provided.
Date: December 12, 1949
Creator: Edwards, Sherman S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of Flutter of a Propeller With Clark Y Section Operating at Zero Forward Velocity at Positive and Negative Blade-Angle Settings

Description: Report presenting an investigation of the flutter of a small one-blade wooden propeller with a Clark Y section. The highest flutter speeds were found in the vicinity of the angle of zero aerodynamic moment, with flutter speed increasing in this region with decreasing pressure.
Date: December 1949
Creator: Baker, John E. & Paulnock, Russell S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Test of the Aerojet 7KS-6000 T-27 Jato Rocket Motor

Description: "A flight test of the Aero jet Engineering Corporation's 7KS-6000 T-27 Jato rocket motor was conducted at the Langley Pilotless Aircraft Research Station at Wallops Island, Va, to determine the flight performance characteristics of the motor. The flight test imposed an absolute longitudinal acceleration of 9.8 g upon the rocket motor at 2.8 seconds after launching. The total impulse developed by the motor was 43,400 pound-seconds, and the thrusting time was 7.58 seconds" (p. 1).
Date: December 20, 1949
Creator: Bond, Aleck C. & Thibodaux, Joseph G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Free-Flight Technique for Measuring Damping in Roll by Use of Rocket-Powered Models and Some Initial Results for Rectangular Wings

Description: Report presenting a simplified method for obtaining free-flight measurements of damping in roll through the use of rocket-powered models. Initial configurations have been tested for a range of Mach numbers. Results regarding the rolling velocity with two different airfoil sections and damping-in-roll coefficient are provided.
Date: December 20, 1949
Creator: Edmondson, James L. & Sanders, E. Claude, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Full-Scale Hydrodynamic Evaluation of a Modified Navy J4F-2 Amphibian with a 0.425-Scale XP5M-1 Hull Bottom: TED No. NACA DE325

Description: "An investigation was made to evaluate the hydrodynamic qualities of a 0.425-scale model of the Navy XP5M-1 hull, which was installed on a modified Navy J4F-2 amphibian. Longitudinal and directional stability during take-off and landing, low-speed maneuverability, spray characteristics, and take-off performance were investigated. The behavior of the airplane in moderately rough water was also observed. The opinions of three pilots have been correlated with the data" (p. 1).
Date: December 7, 1949
Creator: Land, Norman S.; Elliott, John M. & Christopher, Kenneth W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 5: Static Longitudinal Stability and Control Throughout the Subsonic Speed Range of a Semispan Model of a Supersonic Airplane

Description: Memorandum presenting wind-tunnel tests of a semispan model of a hypothetical supersonic airplane to determine the static longitudinal stability and control characteristics of the airplane throughout the range of subsonic Mach numbers up to 0.95. The model had a long slender fuselage and a wing and horizontal tail of aspect ratio 4 and taper ratio 0.5. Results regarding the force and moment characteristics, wing wake and effective downwash at the horizontal tail, effects of compressibility, and… more
Date: December 8, 1949
Creator: Johnson, Ben H., Jr. & Rollins, Francis W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of altitude performance of AN-F-58 fuels in annular combustor of J34-WE-22 engine

Description: From Summary: "An investigation was conducted in the combustor of a 3000-pound-thrust turbojet engine to determine the altitude performance characteristics of AN-F-58 fuels. Three fuels conforming to AN-F-58 specification were prepared in order to determine the influence of boiling-temperature range and aromatic content on altitude performance. The performance of the three AN-F-58 fuels was compared with the performance of AN-F-48 (grade 100/130) fuel in the range of simulated altitudes from 20… more
Date: December 5, 1949
Creator: Tischler, Adelbert O. & Scull, Wilfred E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Landing Procedure in Model Ditching Tests of Bf 109

Description: The purpose of the model tests is to clarify the motions in the alighting on water of a land plane. After discussion of the model laws, the test method and test procedure are described. The deceleration-time-diagrams of the landing of a model of the Bf 109 show a high deceleration peek of greater than 20g which can be lowered to 4 to 6g by radiator cowling and brake skid.
Date: December 1949
Creator: Sottorf, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-Speed Investigation of Deflectable Wing-Tip Ailerons on an Untapered 45 Degrees Sweptback Semispan Wing With and Without an End Plate

Description: Report presenting a low-speed wind-tunnel investigation to determine the characteristics of deflectable wing-tip ailerons on an untapered 45 degree sweptback semispan wing. Ailerons with triangular and parallelogram plan forms with a maximum chord of 0.625 wing chord and a flat-plat profile were investigated. The aerodynamic characteristics in pitch and lateral control characteristics are included.
Date: December 14, 1949
Creator: Fischel, Jack & Watson, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Plastic buckling of a long flat plate under combined shear and longitudinal compression

Description: Report presenting the condition for plastic buckling of a long flat plate under combined shear and longitudinal compression is obtained by using the theory of plastic buckling developed for simple loading, provided the ratio of shear to longitudinal compression is assumed constant during the loading process. A detailed calculation for a number of simply supported plates made of a typical aluminum alloy shows that an approximate algebraic relationship provided in the paper will suffice for deter… more
Date: December 1949
Creator: Stowell, Elbridge Z.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation of a Variable Mass-Flow Supersonic Nose Inlet

Description: Memorandum presenting a method for varying the mass flow of supersonic inlets with a circular cross section and a central body. The method consists of changing the size of the entering stream tube by means of an inflatable boot on the surface of the central body.
Date: December 13, 1949
Creator: Hayes, Clyde
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure-Distribution Measurements on the Tail Surfaces of a Rotating Model of the Design BFW - M31

Description: In order to obtain insight into the flow conditions on tail surfaces on airplanes during spins, pressure-distribution measurements were performed on a rotating model of the design BFW-M31. For the time being, the tests were made for only one angle of attack (alpha = 60 degrees) and various angles of yaw and rudder angles. The results of these measurements are given; the construction of the model, and the test arrangement used are described. Measurements to be performed later and alterations pla… more
Date: December 1949
Creator: Kohler, M. & Mautz, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Stability of Alclad Plates

Description: Report presenting a theoretical solution for the buckling of Alclad plates on the basis of plasticity theory. Both the differential equation of equilibrium of the buckled plate and energy expression are provided. Results regarding the buckling of long simply supported plates under longitudinal compression and under shear and for a plate column are provided.
Date: December 1949
Creator: Buchert, Kenneth P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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