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 Collection: National Advisory Committee for Aeronautics Collection
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
Pressure-distribution measurements of two airfoil models with Fowler flaps submitted by Consolidated Aircraft Corporation as alternative wing sections of the XB-32 airplane

Pressure-distribution measurements of two airfoil models with Fowler flaps submitted by Consolidated Aircraft Corporation as alternative wing sections of the XB-32 airplane

Date: January 1, 1942
Creator: Abbott, Ira H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of four models representing intermediate sections of the XB-33 airplane including sections with slotted flap and ailerons

Tests of four models representing intermediate sections of the XB-33 airplane including sections with slotted flap and ailerons

Date: June 1, 1942
Creator: Abbott, Ira H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests in the variable-density wind tunnel of the NACA 23012 airfoil with plain and split flaps

Tests in the variable-density wind tunnel of the NACA 23012 airfoil with plain and split flaps

Date: January 1, 1939
Creator: Abbott, Ira H & Greenberg, Harry
Description: Section characteristics for use in wing design are presented for the NACA 23012 airfoil with plain and split flaps of 20 percent wing chord at a value of the effective Reynolds number of about 8,000,000. The flap deflections covered a range from 60 degrees upward to 75 degrees downward for the plain flap and from neutral to 90 degrees downward for the split flap. The split flap was aerodynamically superior to the plain flap in producing high maximum lift coefficients and in having lower profile-drag coefficients at high lift coefficients.
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 & Sherman, Albert
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
Tests of a Highly Cambered Low-Drag-Airfoil Section with a Lift-Control Flap, Special Report

Tests of a Highly Cambered Low-Drag-Airfoil Section with a Lift-Control Flap, Special Report

Date: December 1, 1942
Creator: Abbott, Ira H. & Miller, Ralph B.
Description: Tests were made in the NACA two-dimensional low turbulence pressure tunnel of a highly cambered low-drag airfoil (NACA 65,3-618) with a plain flap designed for lift control. The results indicate that such a combination offers attractive possibilities for obtaining low profile-drag coefficients over a wide range of lift coefficients without large reductions of critical speed.
Contributing Partner: UNT Libraries Government Documents Department
Summary of Airfoil Data

Summary of Airfoil Data

Date: January 1, 1945
Creator: Abbott, Ira H; Von Doenhoff, Albert E & Stivers, Louis, Jr
Description: The historical development of NACA airfoils is briefly reviewed. New data are presented that permit the rapid calculation of the approximate pressure distributions for the older NACA four-digit and five-digit airfoils by the same methods used for the NACA 6-series airfoils. The general methods used to derive the basic thickness forms for NACA 6 and 7-series airfoils together with their corresponding pressure distributions are presented. Detail data necessary for the application of the airfoils to wing design are presented in supplementary figures placed at the end of the paper. The report includes an analysis of the lift, drag, pitching-moment, and critical-speed characteristics of the airfoils, together with a discussion of the effects of surface conditions. Available data on high-lift devices are presented. Problems associated with lateral-control devices, leading-edge air intakes, and interference are briefly discussed, together with aerodynamic problems of application. (author).
Contributing Partner: UNT Libraries Government Documents Department
Tail Buffeting

Tail Buffeting

Date: February 1, 1943
Creator: Abdrashitov, G.
Description: An approximate theory of buffeting is here presented, based on the assumption of harmonic disturbing forces. Two cases of buffeting are considered: namely, for a tail angle of attack greater and less than the stalling angle, respectively. On the basis of the tests conducted and the results of foreign investigators, a general analysis is given of the nature of the forced vibrations the possible load limits on the tail, and the methods of elimination of buffeting.
Contributing Partner: UNT Libraries Government Documents Department
The Theory of a Free Jet of a Compressible Gas

The Theory of a Free Jet of a Compressible Gas

Date: March 1, 1944
Creator: Abramovich, G. N.
Description: In the present report the theory of free turbulence propagation and the boundary layer theory are developed for a plane-parallel free stream of a compressible fluid. In constructing the theory use was made of the turbulence hypothesis by Taylor (transport of vorticity) which gives best agreement with test results for problems involving heat transfer in free jets.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems-effect of Method of Positioning the Radar Antenna on the Speed of Response

Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems-effect of Method of Positioning the Radar Antenna on the Speed of Response

Date: August 13, 1952
Creator: Abramovitz, M.
Description: Proportional navigation guidance systems - radar antenna positioning effects on speed of response.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the performance of proportional navigation guidance systems : effect of method of positioning the radar antenna on the speed of response

Theoretical investigation of the performance of proportional navigation guidance systems : effect of method of positioning the radar antenna on the speed of response

Date: August 13, 1952
Creator: Abramovitz, Marvin
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the performance of proportional navigation guidance systems : effect of missile configuration on the speed of response

Theoretical investigation of the performance of proportional navigation guidance systems : effect of missile configuration on the speed of response

Date: January 19, 1953
Creator: Abramovitz, Marvin
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of stick-force gradient and stick gearing on the tracking accuracy of a fighter airplane

The effect of stick-force gradient and stick gearing on the tracking accuracy of a fighter airplane

Date: December 17, 1954
Creator: Abramovitz, Marvin & Van Dyke, Rudolph D , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of the use of a stick force proportional to pitching acceleration for normal-acceleration warning

Investigation of the use of a stick force proportional to pitching acceleration for normal-acceleration warning

Date: August 14, 1953
Creator: Abramovitz, Marvin; Schmidt, Stanley F & Van Dyke, Rudolph D , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical Investigation of the Effects of the Artificial-Feel System on the Maneuvering Characteristics of the F-89 Airplane

Theoretical Investigation of the Effects of the Artificial-Feel System on the Maneuvering Characteristics of the F-89 Airplane

Date: December 31, 1952
Creator: Abramovitz, Marvin; Schmidt, Stanley F. & Belsley, Steven E.
Description: The possibility of overshooting the anticipated normal acceleration as a result of the artificial-feel characteristics of the F-89C airplane at a condition of minimum static stability was investigated analytically by means of an electronic simulator. Several methods of improving the stick-force characteristics were studied. It is shown that, due to the lag in build-up of the portion of the stick force introduced by the bobweight, it would be possible for excessive overshoots of normal acceleration to occur in abrupt maneuvers with reasonable assumed control movements. The addition of a transient stick force proportional to pitching acceleration (which leads the normal acceleration) to prevent this occurring would not be practical due to the introduction of an oscillatory mode to the stick-position response. A device to introduce a viscous damping force would Improve the stick-force characteristics so that normal acceleration overshoots would not be likely, and the variation of the maximum stick force in rapid pulse-type maneuvers with duration of the maneuver then would have a favorable trend.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of internal film cooling of exhaust nozzle of a 1000-pound-thrust liquid-ammonia liquid-oxygen rocket

Investigation of internal film cooling of exhaust nozzle of a 1000-pound-thrust liquid-ammonia liquid-oxygen rocket

Date: June 17, 1952
Creator: Abramson, Andrew E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Variation in the number of revolutions of air propellers

Variation in the number of revolutions of air propellers

Date: March 1, 1923
Creator: Achenbach, W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Natural icing of an axial-flow turbojet engine in flight for a single icing condition

Natural icing of an axial-flow turbojet engine in flight for a single icing condition

Date: August 12, 1948
Creator: Acker, L. W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary results of natural icing of an axial-flow turbojet engine

Preliminary results of natural icing of an axial-flow turbojet engine

Date: August 6, 1948
Creator: Acker, L. W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of a liquid hydrogen fuel system

Flight investigation of a liquid hydrogen fuel system

Date: August 19, 1957
Creator: Acker, L. W.; Christenson, H. H.; Gough, W. V. & Mulholland, D. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary results of natural icing of an axial-flow turbojet engine

Preliminary results of natural icing of an axial-flow turbojet engine

Date: August 6, 1948
Creator: Acker, Loren W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of flight performance of AN-F-58 and AN-F-32 fuels in J35 turbojet engine

Comparison of flight performance of AN-F-58 and AN-F-32 fuels in J35 turbojet engine

Date: April 7, 1949
Creator: Acker, Loren W & Kleinknecht, Kenneth S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of inlet icing on performance of axial-flow turbojet engine in natural icing conditions

Effects of inlet icing on performance of axial-flow turbojet engine in natural icing conditions

Date: May 25, 1950
Creator: Acker, Loren W & Kleinknecht, Kenneth S
Description: A flight investigation in natural icing conditions was conducted to determine the effect of inlet ice formations on the performance of axial-flow turbojet engines. The results are presented for icing conditions ranging from a liquid-water content of 0.1 to 0.9 gram per cubic meter and water-droplet size from 10 to 27 microns at ambient-air temperature from 13 to 26 degrees F. The data show time histories of jet thrust, air flow, tail-pipe temperature, compressor efficiency, and icing parameters for each icing encounter. The effect of inlet-guide-vane icing was isolated and shown to account for approximately one-half the total reduction in performance caused by inlet icing.
Contributing Partner: UNT Libraries Government Documents Department