National Advisory Committee for Aeronautics (NACA) - 4,115 Matching Results

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Aerodynamic Characteristics of a 0.5-Scale Model of the Fairchild XSAM-N-2 Lark Missile at High Subsonic Speeds

Description: An investigation was conducted to determine the longitudinal- and lateral-stability characteristics of a 0.5-scale moue1 of the Fairchild Lark missile, The model was tested with 0 deg and with 22.5 deg of roll. Three horizontal wings having NACA 16-009, 16-209, and 64A-209 sections were tested. Pressures were measured on both pointed and blunt noses. The wind-tunnel-test data indicate that rolling the missile 22.5 deg. had no serious effect on the static longitudinal stability. The desired maneuvering acceleration could not be attained with any of the horizontal wings tested, even with the horizontal wing flaps deflected 50 deg. The flaps on the 64A-209 wing (with small trailing-edge angles and flat sides) were effective at all flap deflections, while the flaps on the 16-series wings (with large trailing-edge angles) lost effectiveness at small flap deflections. The data showed that rolling moment existed when the vertical wing flaps were deflected with the model at other than zero angle of attack. A similar rolling moment probably would be found . with the horizontal wing flaps deflected and the model yawed.
Date: September 28, 1949
Creator: Martin, Andrew & Hunter, Harlo A.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a 6-percent-thick symmetrical double-wedge airfoil at transonic speeds from tests by the NACA wing-flow method

Description: From Introduction: "The investigation covered a range of Mach numbers from 0.66 to 1.12 and included measurements of angle of attack, pitching moment, normal force, and chord force. The drag at zero lift obtained in this investigation was reported in reference 1, but without the correction for tare of the end plate."
Date: March 4, 1949
Creator: Lina, Lindsay J
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a 42 degree swept-back wing with aspect ratio 4 and NACA 64(sub 1)-112 airfoil sections at Reynolds numbers from 1,700,000 to 9,500,000

Description: Report discussing testing on a 42 degree swept-back wing to determine its low-speed aerodynamic characteristics in pitch and yaw at high Reynolds numbers. The main effect of increasing the Reynolds number was delayed wing stalling to higher angles of attack. Roughness on the wing leading edge also had a large adverse effect on lift, drag, and pitching-moment characteristics at higher Reynolds numbers.
Date: May 23, 1947
Creator: Neely, Robert H. & Conner, D. William
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a 45 degree swept-back wing with aspect ratio of 3.5 and NACA 2S-50(05)-50(05) airfoil sections

Description: From Introduction: "The present paper presents the scale effect on the longitudinal aerodynamic characteristics, the aerodynamic characteristics in yaw, and the tuft studies for 0^o and 3.7^o yaw. The results of the effect of leading-edge and trailing-edge flaps on the aerodynamic characteristics of the wing will be presented in later reports."
Date: August 4, 1947
Creator: Proterra, Anthony J
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a flying-boat hull having a length-beam ratio of 15 and a warped forebody

Description: From Introduction: "The results of two phases of this investigation, presented in references 1 and 2, have indicated possible ways of reducing hull drag without causing large changes in aerodynamic stability and hydrodynamic performance."
Date: February 11, 1949
Creator: Macleod, Richard G
Partner: UNT Libraries Government Documents Department

Aerodynamic Characteristics of a Number of Modified NACA Four-Digit-Series Airfoil Sections

Description: Theoretical pressure distributions and measured lift, drag, and pitching moment characteristics at three values of Reynolds number are presented for a group of NACA four-digit-series airfoil sections modified for high-speed applications. The effectiveness of flaps applied to these airfoils and the effect of standard leading-edge roughness were also investigated at one value of Reynolds number. Results are also presented of tests of three conventional NACA four-digit-series airfoil sections.
Date: November 14, 1947
Creator: Loftin, Laurence K., Jr. & Cohen, Kenneth G.
Partner: UNT Libraries Government Documents Department

Aerodynamic Characteristics of a Portion of the Horizontal Tail from a Douglas C-74 Airplane with Fabric-Covered Elevators

Description: A Douglas C-74 airplane, during a test dive at about 0.525 Mach number, experienced uncontrollable longitudinal oscillations sufficient to cause shedding of the outer wing panels and the subsequent crash of the airplane. Tests of a section of the horizontal tail plane from a C-74 airplane were conducted in the Ames 16-foot high-speed wind tunnel to investigate the possibility of the tail as a contributing factor to the accident. The results of the investigations of fabric-covered elevators in various conditions of surface deformation are presented in this report.
Date: May 6, 1947
Creator: Perone, Angelo & Berthold, Cecil L.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a slot-lip aileron and slotted flap for dive brakes

Description: From Introduction: "As a part of this investigation, a study is being made of test results obtained during the development of devices designed primarily for other purposes, such as high lift or lateral control, but which may also be used for dive control. These results have been reanalyzed and are herein presented in a form that should make them convenient for design purposes."
Date: April 1941
Creator: Rogallo, F. M.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a wing with quarter-chord line swept back 35 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bumb method

Description: From Introduction: "This paper presents the results of the investigation of wing-alone and wing-fuselage combinations employing a wing with the quarter-chord line swept back 35^o, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section."
Date: April 21, 1949
Creator: Sleeman, William C , Jr & Becht, Robert E
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Description: Report discussing a particular wing-body combination that is part of a larger investigation to determine the lift, drag, pitching moment, and root bending moments for various configurations. Information about the aerodynamic characteristics at the tail plane is also provided.
Date: February 24, 1949
Creator: Weil, Joseph & Goodson, Kenneth W.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 6, taper ratio 0.6, and NACA 65A006 airfoil section

Description: Report discussing a wing-alone and wing-fuselage configuration with particular characteristics as part of a series of tests of wings using the transonic-bump test technique. Lift, drag, pitching moment, and root bending moment were obtained for the configurations. The effective downwash angles and dynamic-pressure characteristics in the tail region are also described.
Date: November 1, 1949
Creator: Goodson, Kenneth W. & Few, Albert G., Jr.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Description: From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuelage configurations employing a wing with the quarter-chord line swept back 60^o, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the free stream."
Date: September 6, 1949
Creator: King, Thomas J , Jr & Myers, Boyd C , II
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section

Description: From Introduction: "This paper presents the results of the investigation of the wing-alone and of the wing-fuselage configuration employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the air stream. The results of closely related sweptback-wing investigations, which are part of the present transonic programs, are presented in references 1 to 3."
Date: October 21, 1949
Creator: Goodson, Kenneth W & Morrison, William D , Jr
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of an 0.08-scale model of the Martin XB-51 Airplane at high subsonic speeds

Description: Report discussing tests of a scale model of the XB-51 airplane to determine its force, stability, and control characteristics in pitch and yaw at various Mach numbers. The effects of the dive breaks and the bomb bay are also described.
Date: October 7, 1949
Creator: Barnes, Robert H.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of an airfoil-forebody swept flying-boat hull with a wing and tail swept back 51.3 degrees at the leading edge

Description: Report discussing an investigation of the aerodynamic characteristics of an airfoil-forebody swept flying boat hull with a wing and tail swept back 51.3 degrees at the leading edge. The swept hull's minimum drag coefficient was about the same as the parent model or streamline model. Various combinations of flaps were also utilized.
Date: September 9, 1949
Creator: Naeseth, Rodger L. & MacLeod, Richard G.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of flying-boat hulls having length-beam ratios of 20 and 30

Description: Report discussing the aerodynamic effects of length-beam ratios 20 and 30 as compared to length-beam ratios from 6 to 15. There was slightly more longitudinal stability and slightly less directional stability than in the lower ratios and not much change in the minimum drag coefficient.
Date: November 10, 1948
Creator: Riebe, John M.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of four NACA airfoil sections designed for helicopter rotor blades

Description: From Introduction: "The purpose of the present work is to extend the previous investigation and to derive additional airfoil sections designed to minimize the undesirable characteristics of the previously tested airfoils. The tests of these additional airfoils were made in the Langley two-dimensional low-turbulence tunnel (LTT)."
Date: February 1946
Creator: Rice, Fred J , Jr
Partner: UNT Libraries Government Documents Department