National Advisory Committee for Aeronautics (NACA) - 1,423 Matching Results

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Wing plan forms for high-speed flight

Description: From Summary: "It is pointed out that, in the case of an airfoil of infinite aspect ratio moving at an angle of sideslip, the pressure distribution is determined solely by that component of the motion in a direction normal to the leading edge. It follows that the attachment of plane waves to the airfoil at near-sonic or supersonic speeds (Ackeret theory) may be avoided and the pressure drag may be reduced by the use of plan forms in which the angle of sweepback is greater than the Mach angle."
Date: 1947
Creator: Jones, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing pressure distribution and rotor-blade motion of an autogiro as determined in flight

Description: From Summary: "This report presents the results of tests in which the pressure distribution over the fixed wing of an autogiro was determined in both steady and accelerated flight. In the steady-flight condition, the rotor-blade motion was also measured. These data show that in steady flight the rotor speed as a function of the air speed is largely affected by the variation of the division of load between the rotor and the wing; as the load on the wing increases, the rotor speed decreases."
Date: July 31, 1933
Creator: Wheatley, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing Spar Stress Charts and Wing Truss Proportions

Description: "In order to simplify the calculation of beams continuous over three supports, a series of charts have been calculated giving the bending moments at all the critical points and the reactions at all supports for such members. Using these charts as a basis, calculations of equivalent bending moments, representing the total stresses acting in two bay-wing trusses of proportions varying over a wide range, have been determined, both with and without allowance for column effect. This leads finally to… more
Date: 1926
Creator: Warner, Edward P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Working Charts for the Determination of the Lift Distribution Between Biplane Wings

Description: "In this report are presented empirical working charts from which the distribution of lift between wings, that is the fraction of the total lift borne by each, can be determined in the positive lift range for any ordinary biplane cellule whose individual wings have the same profile. The variables taken directly into account include airfoil section, stagger, gap/chord ratio, decalage, chord ratio, and overhang. It is shown that the influence of unequal sweepback and unequal dihedral in upper and… more
Date: July 11, 1932
Creator: Kuhn, Paul
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Working Charts for the Selection of Aluminum Alloy Propellers of a Standard Form to Operate With Various Aircraft Engines and Bodies

Description: "Working charts are given for the convenient selection of aluminum alloy propellers of a standard form, to operate in connection with six different engine-fuselage combinations. The charts have been prepared from full-scale test data obtained in the 20-foot propeller research tunnel of the National Advisory Committee for Aeronautics. An example is also given showing the use of the charts" (p. 3).
Date: March 25, 1929
Creator: Weick, Fred E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The zero-lift drag of a slender body of revolution (NACA RM-10 research model) as determined from tests in several wind tunnels and in flight at supersonic speeds

Description: From Summary: "The results of tests of a slender body of revolution designated the NACA rm-10 have been compiled from various NACA test facilities. Zero-lift drag data are presented for a Reynolds number range from about 1 x 10(6) to 40 x 10(6) from several wind tunnels and from about 12 x 10(6) to 140 x 10(6) from free-flight tests. The Mach numbers covered include 1.5 to 2.4 for the wind-tunnel data and 0.85 to 2.5 for the flight results. The wind tunnel models were tested with and without 60… more
Date: April 16, 1953
Creator: Evans, Albert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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