National Advisory Committee for Aeronautics (NACA) - 6,928 Matching Results

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Ditching Investigation of a 1/15-Scale Model of the Convair-Liner Airplane

Description: A ditching investigation of a model of the Convair-Liner airplane was made to observe the behavior and determine the safest procedure for making an emergency water landing. The ditching model was designed and constructed by the National Advisory Committee for Aeronautics. Design information on the airplane was furnished by the Consolidated Vultee Aircraft Corporation. A three-view drawing of the airplane is shown. The investigation was made in calm water at the Langley tank no. 2 monorail.
Date: 1950
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 horizontal tail on low-speed static lateral stability characteristics of a model having 45 degree sweptback wing and tail surfaces

Description: Report presenting an investigation in the stability tunnel to determine the effects of changes in horizontal-tail size and location on the static lateral stability characteristics of a complete model with wing and tail surfaces having the quarter-chord line swept back 45 degrees. Available procedures for predicting the effect of the horizontal tail on directional stability were found to be unreliable when applied to swept-tail configurations.
Date: January 1950
Creator: Brewer, Jack D. & Lichtenstein, Jacob H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effects of variations in Reynolds number between 3.0 x 10sub6 and 25.0 x 10sub6 upon the aerodynamic characteristics of a number of NACA 6-series airfoil sections

Description: Results are presented of an investigation made to determine the two-dimensional lift and drag characteristics of nine NACA 6-series airfoil section at Reynolds numbers of 15.0 x 10sub6, 20.0 x 10sub6, and 25.0 x 10sub6. Also presented are data from NACA Technical Report 824 for the same airfoils at Reynolds numbers of 3.0 x 10sub6, 6.0 x 10sub6, and 9.0 x 10sub6. The airfoils selected represent sections having variations in the airfoil thickness, thickness form, and camber. The characteristics … more
Date: 1950
Creator: Loftin, Laurence K., Jr. & Bursnall, William J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Elastic and plastic buckling of simply supported solid-core sandwich plates in compression

Description: From Summary: "A solution is presented for the problem of the compressive buckling of simply supported, flat, rectangular, solid-core sandwich plates stressed either in the elastic range or in the plastic range. Charts for the analysis of long sandwich plates are presented for plates having face materials of 24S-T3 aluminum alloy, 76S-T6 Alclad aluminum alloy, and stainless steel. A comparison of computed and experimental buckling stresses of square solid-core sandwich plates indicates fair agr… more
Date: 1950
Creator: Seide, Paul & Stowell, Elbridge Z.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Floating characteristics of rudders and elevators in spinning attitudes as determined from hinge-moment-coefficient data with application to personal-owner-type airplanes

Description: Report presenting a study of the available rudder and elevator hinge-moment-coefficient data in order to determine the floating characteristics of various types of rudders and elevators in spinning attitudes. Results regarding the rudder floating characteristics, elevator floating characteristics, and a comparison of several types of rudders and elevators are provided.
Date: January 1950
Creator: Bihrle, William, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flutter of a uniform wing with an arbitrarily placed mass according to a differential-equation analysis and a comparison with experiment

Description: A method is presented for the calculation of the flutter speed of a uniform wing carrying an arbitrarily placed concentrated mass. The method, an extension of recently published work by Goland and Luke, involves the solution of the differential equations of motion of the wing at flutter speed and therefore does not require the assumption of specific normal modes of vibration. The order of the flutter determinant to be solved by this method depends upon the order of the system of differential eq… more
Date: 1950
Creator: Runyan, Harry L. & Watkins, Charles E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Space Oscillating Pressures Near the Tips of Rotating Propellers

Description: "The theory is given for calculating the free-space oscillating pressures associated with a rotating propeller, at any point in space. Because of its complexity this analysis is convenient only for use in the critical region near the propeller tips where the assumptions used by Gutin to simplify his final equations are not valid. Good agreement was found between analytical and experimental results in the tip Mach number range 0.45 to two, three, four, five, six, on eight-blade propellers and fo… more
Date: 1950
Creator: Hubbard, Harvey H. & Regier, Arthur A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Gust-Tunnel Investigation to Determine the Load at the Joint of a Coupled Airplane Configuration Encountering a Gust

Description: "An investigation has been made in the Langley gust tunnel with two identical airplane models approximating 1/40-scale models of the B-29, coupled in tandem with a boom so that the individual centers of gravity were equidistant from the single coupling joint at the tail of the lead airplane. Time histories of the boom joint load were obtained as the models were flown through a gust. The results indicate that on a similar configuration involving airplanes the size of B-29 airplanes a load on the… more
Date: January 1950
Creator: Cahen, George L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Icing-Protection Requirements for Reciprocating-Engine Induction Systems

Description: Report presenting an investigation of the icing of aircraft-engine induction systems. Criterions for safe operation and for the design of new induction system are established through the investigation. The results were obtained from laboratory investigations of carburetor-supercharger combinations, wind-tunnel investigations of air scoops, multicylinder-engine studies, and flight investigations.
Date: 1950
Creator: Coles, Willard D.; Rollin, Vern G. & Mulholland, Donald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a NACA high-speed strain-gage torquemeter

Description: Report presenting an investigation of a strain-gage torquemeter employing a circuit to minimize effects of contact resistance, which was evaluated under static and dynamic conditions. Effects of temperature, axial stress, slip-ring contact resistance, and speed on the operation of the torquemeter were investigated. Results regarding the torsion-shaft static calibration, axial-stress effects, and dynamic operation are provided.
Date: January 1950
Creator: Rebeske, John J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of the Longitudinal Characteristics of the MX-656 Configuration Using Rocket-Propelled Models Preliminary Results at Mach Numbers from 0.65 to 1.25

Description: "A rocket-propelled model of the MX-656 configuration has been flown through the Mach number range from 0.65 to 1.25. An analysis of the response of the model to rapid deflections of the horizontal tail gave information on the lift, drag, longitudinal stability and control, and longitudinal-trim change. The lift-coefficient range covered by the test was from -0.2 to 0,3 throughout most of the Mach number range" (p. 1).
Date: 1950
Creator: Mitchell, Jesse L. & Peck, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Linearized Supersonic Theory of Conical Wings

Description: Report presenting the theory of conical flow and its application to conical aircraft wings. Following an explanation of the theory, several types of wings are analyzed and compared with each other.
Date: January 1950
Creator: Lagerstrom, P. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The load distribution due to sideslip on triangular, trapezoidal, and related plan forms in supersonic flow

Description: "Expressions are presented for the load distribution on a representative group of plan forms in sideslip at supersonic speeds. These expressions were obtained by the application of lifting-surface theories based on the linearized equation for compressible flow. Sketches of the load distributions are included" (p. 1).
Date: January 1950
Creator: Jones, Arthur L. & Alksne, Alberta
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Method for determining the frequency-response characteristics of an element or system from the system transient output response to a known input function

Description: "A method is presented for the determination of the frequency-response characteristics of an element or system by utilizing the transient output response to a known but arbitrary input to the system. Since the application of special inputs, such as step functions or sinusoids, is often imperfect or impractical, a method for utilizing arbitrary inputs is desirable. Simple flight-test data may be reduced by this method to give the frequency response of an aircraft" (p. 1).
Date: 1950
Creator: Curfman, Howard J., Jr. & Gardiner, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of J33-A-27 Turbojet-Engine Compressor, II, Over - All Performance Characteristics of Modified Compressor at Equivalent Impeller Speeds from 6100 to 13,250 RPM

Description: "A modified J33-A-27 compressor was operated over a range of equivalent impeller speeds from 6100 to 13,250 rpm in order to obtain the over-all compressor performance. At the equivalent design speed of 11,800 rpm, the maximum efficiency of 0.764 and peak pressure ratio of 4.56 occurred at an equivalent weight flow of 104.07 pounds per second. At the highest equivalent speed (13,250 rpm) a maximum efficiency of 0.711, a maximum equivalent weight flow of 123.00 pounds per second, and a peak press… more
Date: 1950
Creator: Beede, William L. & Ginsburg, Ambrose
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Results Obtained from Flight Test of a Rocket Model Having the Tail Only of the Grumman XF10F Airplane Configuration, TED No. NACA DE 354

Description: "A flight test was made to determine the servoplane effectiveness and stability characteristics of the free-floating horizontal stabilizer to be used on the XF10F airplane. The results of this test indicate that servoplane effectiveness is practically constant through the speed range up to a Mach number of 1.15, and the stabilizer static stability is satisfactory. A loss of damping occurs over a narrow Mach number range near M = 1.0, resulting in dynamic instability of the stabilizer in this na… more
Date: 1950?
Creator: Gardner, William N. & Edmondson, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Propeller Flight Investigation to Determine the Effects of Blade Loading

Description: Note presenting a flight investigation of a three-blade propeller in climb and at high speed to determine the effects of blade power loading. Increasing the blade power coefficient from 0.06 to 0.09 was found to increase the efficiency approximately 8 percent at an airplane Mach number of 0.7 and a propeller-tip Mach number of 1.13. In climb, an increase in power loading over the range of blade power coefficients investigated was shown to reduce efficiency, as a consequence of increased induced… more
Date: January 1950
Creator: Hammack, Jerome B. & Vogeley, A. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Small Bending and Stretching of Sandwich-Type Shells

Description: "A theory has been developed for small bending and stretching of sandwich-type shells. This theory is an extension of the known theory of homogeneous thin elastic shells. It was found that two effects are important in the present problem, which are not normally of importance in the theory of curved shells: (1) the effect of transverse shear deformation and (2) the effect of transverse normal stress deformation" (p. 1).
Date: 1950
Creator: Reissner, Eric
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Spanwise loading for wings and control surfaces of low aspect ratio

Description: Report presenting a theory based on the principle of downwash and boundary conditions, which will predict the spanwise loading due to arbitrary spanwise angle-of-attack distribution, including uniform angle of attack, that induced by rolling, spanwise variation of twist or camber, and that due to deflection of arbitrary control surfaces of low aspect ratio. For plan forms with unswept trailing edges that the spanwise loading distribution, only the slope of the region at the wing trailing edge h… more
Date: January 1950
Creator: DeYoung, John
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of a Hermes A-2 Missile Body at Mach Number 4.04

Description: Force tests on a proposed body shape of the Hermes A-2 missile with and without longitudinal spoilers were made at Mach number 4.04. Values of normal force coefficient, pitching-moment coefficient, and center-of-pressure position were obtained.
Date: 1950
Creator: Ulmann, Edward F. & Lord, Douglas R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Theoretical Analysis of Elastic Vibrations of Fixed-Ended and Hinged Helicopter Blades in Hovering and Vertical Flight

Description: Note presenting a theoretical analysis of the frequency and damping characteristics of the free modes of vibrations of balanced fixed-ended and hinged elastic helicopter rotor blades in hovering and vertical flight. Torsional vibrations, bending vibrations in flapping and in lagging, and coupling between the flapping and lagging motions are considered.
Date: January 1950
Creator: Morduchow, Morris
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical calculations of the supersonic pressure distribution and wave drag for a limited family of tapered sweptback wings with symmetrical parabolic-arc sections at zero lift

Description: Report presenting the study of the supersonic pressure distribution and wave drag of sweptback wings at zero lift, which has been extended by means of linearized theory to include the combined effects of plan-form taper and curvature of profile. Calculations have been made for a specific wing with a supersonic leading edge, which are applicable to a limited family of plan forms.
Date: January 1950
Creator: Kainer, Julian H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Theoretical Investigation of the Effect on the Lateral Oscillations of an Airplane of an Automatic Control Sensitive to Yawing Accelerations

Description: Report presenting an investigation to determine the effect on the lateral oscillations of an airplane of an automatic control sensitive to yawing accelerations. Results indicated that a control of that type can successfully damp the lateral oscillations through a reasonable range of time lag.
Date: January 1950
Creator: Beckhardt, Arnold R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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