National Advisory Committee for Aeronautics (NACA) - 13,806 Matching Results

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Wind-tunnel interference with particular reference to off-center positions of the wing and to the downwash at the tail

Description: The theory of wind tunnel boundary influence on the downwash from a wing has been extended to provide more complete corrections for application to airplane test data. The first section of the report gives the corrections of the lifting line for wing positions above or below the tunnel center line; the second section shows the manner in which the induced boundary influence changes with distance aft of the lifting line. Values of the boundary corrections are given for off-center positions of the wing in circular, square, 2:1 rectangular, and 2:1 elliptical tunnels. Aft of the wing the corrections are presented for only the square and the 2:1 rectangular tunnels, but it is believed that these may be applied to jets of circular and 2:1 elliptical cross sections. In all cases results are included for both open and closed tunnels.
Date: January 1, 1937
Creator: Silverstein, Abe & White, James A
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at a Mach number of 1.53 of an airplane with a triangular wing

Description: Report discusses the results of an investigation into the aerodynamic characteristics of models of a tailless, pursuit-type, supersonic airplane employing a wing of triangular plan form. Measurements of lift, drag, and pitching moment, side force, drag, and yawing moment are described for several angles of attack and angles of yaw. Information about elevator and rudder behavior is also described.
Date: January 23, 1948
Creator: Scherrer, Richard & Wimbrow, William R.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls

Description: An investigation of the aerodynamic characteristics of several hypersonic missile configurations with various canard controls for an angle-of-attack range from 0 deg to about 28 deg at sideslip angles of about 0 deg and 4 deg at a Mach number of 2.01 has been made in the Langley 4- by 4-foot supersonic pressure tunnel. The configurations tested were a body alone which had a ratio of length to diameter of 10, the body with a 10 deg flare, the body with cruciform fins of 5 deg or 15 deg apex angle, and a flare-stabilized rocket model with a modified Von Karman nose. Various canard surfaces for pitch control only were tested on the body with the 10 deg flare and on the body with both sets of fins. The results indicated that the addition of a flared afterbody or cruciform fins produced configurations which were longitudinally and directionally stable. The body with 5 deg fins should be capable of producing higher normal accelerations than the flared body. A l l of the canard surfaces were effective longitudinal controls which produced net positive increments of normal force and pitching moments which progressively decreased with increasing angle of attack.
Date: March 10, 1958
Creator: Robinson, R. B.
Partner: UNT Libraries Government Documents Department

Wind tunnel investigation at high subsonic speeds of drag at 0 degrees angle of attack of swept-wing fuselage models with pylon mounted and semisubmerged missiles

Description: Report discussing testing on two wing-fuselage models with 45 degree sweptback wings and various missile arrangements, one with pylons underneath the wing and one with the missiles semisubmerged in the sides of the fuselage. A comparison of the drag of both types of models was made.
Date: October 8, 1956
Creator: King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department

A wind-tunnel investigation at high subsonic speeds of the lateral control characteristics of various plain spoiler configurations on a 3-percent-thick 60 degree delta wing

Description: Results are presented of wind-tunnel investigations at Mach numbers of 0.60 to 0.94 and angles of attack of -2 degrees to about 24 degrees to determine the lateral control characteristics of spoilers with various wing chord-wise and spanwise locations and spoiler spans and deflections on thin 60 degree delta wing of NACA 65a003 airfoil section parallel to free stream.
Date: May 26, 1954
Creator: Wiley, Harleth G
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speed of a wing having 63 degree sweepback and a drooped tip

Description: From Summary: "The results of force tests made at low speed are presented to show the effect of longitudinal static stability produced by drooping the tip of a 63 degree sweptback wing. Five semispan wing models were tested: two incorporated curved drooped tips, two with abruptly drooped tips, and one without droop. The most favorable stability characteristics were measured for a model with an abruptly drooped tip, a fence, and a leading-edge flap; however, the use of these same auxiliary devices on the undrooped wing was nearly as effective."
Date: April 7, 1955
Creator: Blackaby, James R.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speed of a wing swept-back 63 degrees and twisted and cambered for a uniform load at a lift coefficient of 0.5

Description: Report discusses the results of testing to determine the low-speed longitudinal stability characteristics and spanwise distribution of load of a wing model with the leading edge swept back 63 degrees, an aspect ratio of 3.5, and a large amount of twist and camber. The results are compared to tests of a model of an untwisted and uncambered wing of identical plan form. Measurements of force, pressure-distribution, and comparison of theoretical and experimental span loading are described.
Date: May 9, 1950
Creator: Weiberg, James A. & Carel, Hubert C.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speed of a wing swept back 63 degrees and twisted and cambered for uniform load at a lift coefficient of 0.5 and with a thickened tip section

Description: Report discusses the result of tests determining the longitudinal-stability characteristics and spanwise distribution of load of a wing model with the leading edge swept back 63 degrees, a thickened tip section, and a twisted and cambered shape. The wing was tested with a fuselage and various devices for altering stall and spanwise boundary-layer flow. Measurements of force, pressure-distribution, and span load distribution are described.
Date: November 21, 1950
Creator: Weiberg, James A. & Carel, Hubert C.
Partner: UNT Libraries Government Documents Department

Wind Tunnel Investigation at Low Speed of Aerodynamic Characteristics of Army Chemical Corps Model E-112 Bomblets with Span Chord Ratio of 2 - 1

Description: An experimental investigation has been made in the Langley stability tunnel to determine the aerodynamic characteristics of the Army Chemical Corps model E-112 bomblets with span-chord ratio of 2:1. A detailed analysis has not been made; however, the results showed that all the models were spirally unstable and that a large gap between the model tips and end plates tended to reduce the instability.
Date: December 26, 1956
Creator: Letko, W.
Partner: UNT Libraries Government Documents Department