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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Technical Notes
 Collection: Technical Report Archive and Image Library
Absolute dimensions of Karman vortex motion

Absolute dimensions of Karman vortex motion

Date: January 1923
Creator: Heisenberg, Werner
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Accelerations and passenger harness loads measured in full-scale light-airplane crashes

Accelerations and passenger harness loads measured in full-scale light-airplane crashes

Date: August 1953
Creator: Eiband, A Martin; Simpkinson, Scott H & Black, Dugald O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Accelerations in transport-airplane crashes

Accelerations in transport-airplane crashes

Date: February 1958
Creator: Preston, G Merritt & Pesman, Gerard J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Accuracy of approximate methods for predicting pressures on pointed nonlifting bodies of revolution in supersonic flow

Accuracy of approximate methods for predicting pressures on pointed nonlifting bodies of revolution in supersonic flow

Date: August 1952
Creator: Ehret, Dorris M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The accuracy of the substitute-stringer approach for determining the bending frequencies of multistringer box beams

The accuracy of the substitute-stringer approach for determining the bending frequencies of multistringer box beams

Date: April 1956
Creator: Davenport, William W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An accurate and rapid method for the design of supersonic nozzles

An accurate and rapid method for the design of supersonic nozzles

Date: February 1955
Creator: Beckwith, Ivan E & Moore, John A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An accurate method of measuring the moments of inertia of airplanes

An accurate method of measuring the moments of inertia of airplanes

Date: October 1930
Creator: Miller, M P
Description: This note contains a description of an improved apparatus and procedure used by the NACA for determining the moments of inertia of airplanes. The method used, based on the pendulum theory, is similar to that previously used, but a recent investigation of its accuracy has resulted in the improvements described herein. The error, when using the new apparatus and procedure, has been found to be of the order of 1 per cent.
Contributing Partner: UNT Libraries Government Documents Department
Achievement of continuous wall curvature in design of two-dimensional symmetrical supersonic nozzles

Achievement of continuous wall curvature in design of two-dimensional symmetrical supersonic nozzles

Date: January 1952
Creator: Evvard, J C & Marcus, Lawrence R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acoustic analysis of ram-jet buzz

Acoustic analysis of ram-jet buzz

Date: November 1955
Creator: Mirels, Harold
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acoustic radiation from two-dimensional rectangular cutouts in aerodynamic surfaces

Acoustic radiation from two-dimensional rectangular cutouts in aerodynamic surfaces

Date: August 1955
Creator: Krishnamurty, K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acoustic, thrust, and drag characteristics of several full-scale noise suppressors for turbojet engines

Acoustic, thrust, and drag characteristics of several full-scale noise suppressors for turbojet engines

Date: April 1958
Creator: Ciepluch, Carl C; North, Warren J; Coles, Willard D & Antl, Robert J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acoustical treatment for the NACA 8- by 6-foot supersonic propulsion wind tunnel

Acoustical treatment for the NACA 8- by 6-foot supersonic propulsion wind tunnel

Date: June 1955
Creator: Beranek, Leo L; Labate, Samuel & Ingard, Uno
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Adaptation of aeronautical engines to high altitude flying

Adaptation of aeronautical engines to high altitude flying

Date: May 1923
Creator: Kutzbach, K
Description: Issues and techniques relative to the adaptation of aircraft engines to high altitude flight are discussed. Covered here are the limits of engine output, modifications and characteristics of high altitude engines, the influence of air density on the proportions of fuel mixtures, methods of varying the proportions of fuel mixtures, the automatic prevention of fuel waste, and the design and application of air pressure regulators to high altitude flying. Summary: 1. Limits of engine output. 2. High altitude engines. 3. Influence of air density on proportions of mixture. 4. Methods of varying proportions of mixture. 5. Automatic prevention of fuel waste. 6. Design and application of air pressure regulators to high altitude flying.
Contributing Partner: UNT Libraries Government Documents Department
Adaptor for measuring principal strains with Tuckerman strain gage

Adaptor for measuring principal strains with Tuckerman strain gage

Date: June 1943
Creator: Mcpherson, A E
Description: An adapter is described which uses three Tuckerman optical strain gages to measure the displacement of the three vortices of an equilateral triangle along lines 120 degrees apart. These displacements are substituted in well-known equations in order to compute the magnitude and direction of the principal strains. Tests of the adaptor indicate that principal strains over a gage length of 1.42 inch may be measured with a systematic error not exceeding 4 percent and a mean observational error of the order of + or minus 0.000006. The maximum observed error in strain was of the order of 0.00006. The directions of principal strains for unidirectional stress were measured with the adaptor with an average error of the order of 1 degree.
Contributing Partner: UNT Libraries Government Documents Department
Additional static and fatigue tests of high-strength aluminum-alloy bolted joints

Additional static and fatigue tests of high-strength aluminum-alloy bolted joints

Date: July 1954
Creator: Hartmann, E C; Holt, Marshall & Eaton, I D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Adhesion of ice in its relation to the de-icing of airplanes

Adhesion of ice in its relation to the de-icing of airplanes

Date: August 1939
Creator: Rothrick, A M & Selden, R
Description: 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 liquids will provide the best means of protection.
Contributing Partner: UNT Libraries Government Documents Department
Advantages of oxide films as bases for aluminum pigmented surface coatings for aluminum alloys

Advantages of oxide films as bases for aluminum pigmented surface coatings for aluminum alloys

Date: November 1931
Creator: Buzzard, R W & Mutchler, W H
Description: Both laboratory and weather-exposure corrosion tests showed conclusively that the protection afforded by aluminum pigmented spar varnish coatings applied to previously anodized aluminum surfaces was greatly superior to that afforded by the same coatings applied to surfaces which had simply been cleaned free from grease and not anodized.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic analysis of the gyroplane rotating-wing system

The aerodynamic analysis of the gyroplane rotating-wing system

Date: March 1934
Creator: Wheatley, John B
Description: An aerodynamic analysis of the gyroplane rotating-wing system is presented herein. This system consists of a freely rotating rotor in which opposite blades are rigidly connected and allowed to rotate or feather freely about their span axis. Equations have been derived for the lift, the lift-drag ratio, the angle of attack, the feathering angles, and the rolling and pitching moments of a gyroplane rotor in terms of its basic parameters. Curves of lift-drag ratio against lift coefficient have been calculated for a typical case, showing the effect of varying the pitch angle, the solidarity, and the average blade-section drag coefficient. The analysis expresses satisfactorily the qualitative relations between the rotor characteristics and the rotor parameters. As disclosed by this investigation, the aerodynamic principles of the gyroplane are sound, and further research on this wing system is justified.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic behavior of a harmonically oscillating finite sweptback wing in supersonic flow

The aerodynamic behavior of a harmonically oscillating finite sweptback wing in supersonic flow

Date: October 1951
Creator: Chang, Chieh-Chien
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and supersonic speeds

Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and supersonic speeds

Date: November 1956
Creator: Mitcham, Grady L; Stevens, Joseph E & Norris, Harry P
Description: A flight investigation of rocket-powered models of a tailless triangular-wing airplane configuration was made through the transonic and low supersonic speed range at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. An analysis of the aerodynamic coefficients, stability derivatives, and flying qualities based on the results obtained from the successful flight tests of three models is presented.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Reynolds numbers of 3.0 x 10(exp 6) and 6.0 x 10(exp 6) of three airfoil sections formed by cutting off various amounts from the rear portion of the NACA 0012 airfoil section

Aerodynamic characteristics at Reynolds numbers of 3.0 x 10(exp 6) and 6.0 x 10(exp 6) of three airfoil sections formed by cutting off various amounts from the rear portion of the NACA 0012 airfoil section

Date: April 1950
Creator: Smith, Hamilton A & Schaefer, Raymond F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of 15 NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)

Aerodynamic characteristics of 15 NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)

Date: October 1949
Creator: Loftin, Laurence K , Jr & Smith, Hamilton A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a circular cylinder at Mach number 6.86 and angles of attack up to 90 degrees

Aerodynamic characteristics of a circular cylinder at Mach number 6.86 and angles of attack up to 90 degrees

Date: January 1957
Creator: Penland, Jim A
Description: Pressure-distribution and force tests of a circular cylinder have been made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.88, a Reynolds number of 129,000, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and a simple modification of the Newtonian flow theory. An evaluation of the crossflow theory is made through comparison of present results with available crossflow Mach number drag coefficients.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of a model wing having a split flap deflected downward and moved to the rear

The aerodynamic characteristics of a model wing having a split flap deflected downward and moved to the rear

Date: May 1932
Creator: Weick, Fred E & Harris, Thomas E
Description: Tests were made on a model wing with three different sized split trailing-edged flaps, in the NACA 7 by 10 foot wind tunnel. The flaps were formed of the lower rear portion of the wing and were rotated downward about axes at their front edges. The lift, drag, and center of pressure were measured with the axis in its original position and also with it moved back in even steps to the trailing edge of the main wing, giving in effect an increase in area. The split flaps when deflected about their original axis locations gave slightly higher maximum lift coefficients than conventional trailing-edge flaps, and the lift coefficients were increased still further by moving the axes toward the rear. The highest value of C(sub L max), which was obtained with the largest flap hinged at 90 per cent of the chord from the leading edge, was 2.52 as compared with 1.27 for the basic wing.
Contributing Partner: UNT Libraries Government Documents Department