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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Experiments with an airfoil model on which the boundary layers are controlled without the use of supplementary equipment

Experiments with an airfoil model on which the boundary layers are controlled without the use of supplementary equipment

Date: April 1, 1931
Creator: Abbott, I H
Description: This report describes test made in the Variable Density Wind Tunnel of the NACA to determine the possibility of controlling the boundary layer on the upper surface of an airfoil by use of the low pressure existing near the leading edge. The low pressure was used to induce flow through slots in the upper surface of the wing. The tests showed that the angle of attack for maximum lift was increased at the expense of a reduction in the maximum lift coefficient and an increase in the drag coefficient.
Contributing Partner: UNT Libraries Government Documents Department
Lift and drag characteristics of a low-drag airfoil with slotted flap submitted by Curtiss-Wright Corporation

Lift and drag characteristics of a low-drag airfoil with slotted flap submitted by Curtiss-Wright Corporation

Date: December 1, 1941
Creator: Abbott, I H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Pressure-distribution measurements of a low-drag airfoil with slotted flap submitted by Curtiss-Wright Corporation

Pressure-distribution measurements of a low-drag airfoil with slotted flap submitted by Curtiss-Wright Corporation

Date: December 1, 1941
Creator: Abbott, I H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary Low-Drag-Airfoil and Flap Data from Tests at Large Reynolds Numbers and Low Turbulence

Preliminary Low-Drag-Airfoil and Flap Data from Tests at Large Reynolds Numbers and Low Turbulence

Date: March 1, 1942
Creator: Abbott, I. H.; Davidson, M. & Jacobs, E. N.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Airship model tests in the variable density wind tunnel

Airship model tests in the variable density wind tunnel

Date: January 1, 1932
Creator: Abbott, Ira H
Description: This report presents the results of wind tunnel tests conducted to determine the aerodynamic characteristics of airship models. Eight Goodyear-Zeppelin airship models were tested in the original closed-throat tunnel. After the tunnel was rebuilt with an open throat a new model was tested, and one of the Goodyear-Zeppelin models was retested. The results indicate that much may be done to determine the drag of airships from evaluations of the pressure and skin-frictional drags on models tested at large Reynolds number.
Contributing Partner: UNT Libraries Government Documents Department
The drag of two streamline bodies as affected by protuberances and appendages

The drag of two streamline bodies as affected by protuberances and appendages

Date: January 1, 1934
Creator: Abbott, Ira H
Description: This report presents the results of wind tunnel tests of two airship models conducted to determine the drag coefficients at zero pitch, and the effect of fins and cars and of flat and streamlined protuberances located at various positions along the hull. During the investigation the stern of one model was rounded off to produce a blunter shape. The extreme range of the Reynolds number based on the over-all length of the models was from 1,300,000 to 33,000,000. At large values of the Reynolds number the streamlined protuberance affected the drag very little, and the additional drag caused by the flat protuberance was less than the calculated drag by the protuberance alone. The fins and cars together increased the bare-hull drag about 20 per cent.
Contributing Partner: UNT Libraries Government Documents Department
Flow observations with tufts and lampblack of the stalling of four typical airfoil sections in the NACA variable-density tunnel

Flow observations with tufts and lampblack of the stalling of four typical airfoil sections in the NACA variable-density tunnel

Date: October 1, 1938
Creator: Abbott, Ira H
Description: A preliminary investigation of the stalling processes of four typical airfoil sections was made over the critical range of the Reynolds Number. Motion pictures were taken of the movements of small silk tufts on the airfoil surface as the angle of attack increased through a range of angles including the stall. The boundary-layer flow also at certain angles of attack was indicated by the patterns formed by a suspension of lampblack in oil brushed onto the airfoil surface. These observations were analyzed together with corresponding force-test measurements to derive a picture of the stalling processes of airfoils.
Contributing Partner: UNT Libraries Government Documents Department
Fuselage-drag tests in the variable-density wind tunnel: streamline bodies of revolution, fineness ratio of 5

Fuselage-drag tests in the variable-density wind tunnel: streamline bodies of revolution, fineness ratio of 5

Date: September 1, 1937
Creator: Abbott, Ira H
Description: Results are presented of the drag tests of six bodies of revolution with systematically varying shapes and with a fineness ratio of 5. The forms were derived from source-sink distributions, and formulas are presented for the calculation of the pressure distribution of the forms. The tests were made in the N.A.C.A. variable-density tunnel over a range of values of Reynolds number from about 1,500,000 to 25,000,000. The results show that the bodies with the sharper noses and tails have the lowest drag coefficients, even when the drag coefficients are based on the two-thirds power of the volume. The data shows the most important single characteristic of the body form to be the tail angle, which must be fine to obtain low drag.
Contributing Partner: UNT Libraries Government Documents Department
Interference effects of longitudinal flat plates on low-drag airfoils

Interference effects of longitudinal flat plates on low-drag airfoils

Date: November 1, 1942
Creator: Abbott, Ira H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation

Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation

Date: January 1, 1942
Creator: Abbott, Ira H
Description: Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, 20 degrees, and 40 degrees are presented. The normal force coefficients agree with lift coefficients obtained in previous test of the same model, except for the maximum lifts with flap deflection. Pressure distribution measurements were made at Reynolds Number of about 6,000,000.
Contributing Partner: UNT Libraries Government Documents Department