National Advisory Committee for Aeronautics (NACA) - 5,157 Matching Results

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Aerodynamic characteristics at transonic speeds of a 60 degree delta wing equipped with a constant-chord flap-type control with and without an unshielded horn balance: transonic-bump method

Description: Report presenting an investigation to determine the control hinge moments and effectiveness at transonic speeds of a delta wing equipped with a constant-chord flap-type control with and without an unshielded triangular horn balance in the 7- by 10-foot tunnel using the transonic-bump method. The data indicated that the horn balance control was consistently more effective in changing lift at all Mach numbers than was the plain control but there was no appreciable difference in pitching-moment ef… more
Date: September 16, 1952
Creator: Wiley, Harleth G. & Zontek, Leon
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at transonic speeds of a 69 degree delta wing with a triangular plan-form control having a skewed hinge axis and an overhang balance: transonic-bump method

Description: From Introduction: "Presented in this paper are the results of an investigation of a semispan model of a delta wing with 60^o sweepback at the leading edge which was equipped with a large triangular control having an overhang balance mounted on a skewed hinge axis. The purpose of this investigation was to determine the aerodynamic characteristics of a delta wing with a control which was designed to provide aerodynamic balance at zero control deflection based on the span load distribution of ref… more
Date: February 6, 1951
Creator: Wiley, Harleth G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The aerodynamic characteristics at transonic speeds of a model with a 45 degree sweptback wing, including the effect of leading edge slats and a low horizontal tail

Description: Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge slats on the aerodynamic and longitudinal stability characteristics of a model of a swept-wing fighter-type airplane. Two different spanwise extents of leading-edge slats were tested, from 35 to 95 percent semispan and from 46 to 95 percent semispan. Results regarding the lift characteristics, drag characteristics and lift-drag ratios, stability characteristics, and flow-study pictures ar… more
Date: April 5, 1954
Creator: Runckel, Jack F. & Schmeer, James W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics at Transonic Speeds of a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3 Having a Full-Span Flap Type of Control With Overhang Balance: Transonic-Bump Method

Description: From Introduction: "This paper presents the aerodynamic characteristics of low-aspect-ratio sweptback wing having a full-span flap type of control employing an overhanging balance of 50 percent of the flap chord.The main purpose of this investigation was to determine if overhang balances are an effective means of reducing the hinge moments of flap type of controls at transonic speeds."
Date: January 25, 1952
Creator: Lockwood, Vernard E. & Hagerman, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at transonic speeds of a wing having a 45 degree sweep, aspect ratio 8, taper ratio 0.45, and airfoil sections varying from the NACA 63A010 section at the root to the NACA 63A006 section at the tip.

Description: Report presenting an investigation in the 7- by 10-foot tunnel to determine the transonic aerodynamic characteristics of a wing with a spanwise variation in thickness ratio. The wings investigated had 45 degrees of sweepback, aspect ratio 8, taper ratio 0.45, and airfoil sections tapered from an NACA 63A010 section at the root chord to an NACA 63A006 section at the tip chord. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.
Date: January 15, 1952
Creator: Morrison, William D., Jr. & Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Aerodynamic Characteristics at Transonic Speeds of an All-Movable, Tapered, 45 Degree Sweptback, Aspect-Ratio-4 Tail Deflected About a Skewed Hinge Axis and Equipped with an Inset Unbalancing Tab

Description: From Introduction: "The present investigation presents the lift and moment characteristics of an aspect-ratio-4.0 tail, sweptback 45^o at the quarter-chord line and pivoted about an axis sweptback 55.5^o and passing through the leading edge of the root-chord line."
Date: September 29, 1953
Creator: Watson, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The aerodynamic characteristics at transonic speeds of an all-movable, tapered, 45 degrees sweptback, aspect-ratio-4 tail surface deflected about a skewed hinge axis

Description: From Introduction: "The purpose of the present paper was to determine whether the characteristics about a skewed axis could be predicted from data about the normal angle-of-attack axis, and whether such a configuration offered any aerodynamic advantages over the conventional hinge location normal to the pane of symmetry."
Date: July 3, 1952
Creator: Hammond, Alexander D. & Watson, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics extended to high angles of attack at transonic speeds of a small-scale 0 degree sweep wing, 45 degree sweptback wing, and 60 degree delta wing

Description: Report presenting an investigation of a series of wings of various plan forms in the high-velocity field of the side-wall reflection plate of the 7- by 10-foot tunnel at a range of angles of attack and Mach numbers. The results indicated that the maximum lift coefficients obtainable increased with increase in sweep angle and decreased with Mach number at the lower subsonic Mach numbers.
Date: November 18, 1952
Creator: Wiley, Harleth G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a 1/14-Scale Model of the Grumman XF104 Airplane with Wing Sweepback of 42.5 Degrees

Description: "An investigation has been made at high subsonic speeds of the aerodynamic characteristics in pitch and sideslip of a 1/l4-scale model of the Grumman XF10F airplane with a wing sweepback angle of 42.5. The longitudinal stability characteristics (with the horizontal tail fixed) indicate a pitch-up near the stall; however, this was somewhat alleviated by the addition of fins to the side of the fuselage below the horizontal tail. The original model configuration became directionally unstable for s… more
Date: August 18, 1953
Creator: Kuhn, Richard E. & Draper, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Aerodynamic Characteristics in Pitch of a 1/15-Scale Model of the Grumman F11F-1 Airplane at Mach Numbers of 1.41, 1.61, and 2.01, TED No. NACA DE 390

Description: "Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined" (p. 1).
Date: May 23, 1956
Creator: Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics in pitch of a series of cruciform-wing missiles with canard controls at a Mach number of 2.01

Description: From Introduction: "This paper presents the results of tests made at a Mach number of 2.01 to determine the effect of body length on the longitudinal characteristics (zero roll angle) for five complete configurations as well as for the bodies alone, the bodies plus wings, and the bodies plus canard surfaces. The experimental results are compared with some simple theoretical estimates."
Date: October 30, 1953
Creator: Spearman, M. Leroy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics including effects of wing fixes of a 1/20-scale model of the Convair F-102 airplane at transonic speeds

Description: From Introduction: "Results from the tests in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 are presented in reference 1. Reported herein are results obtained from the tests in the Langley 8-foot transonic tunnel of the model with no control deflections at Mach numbers 0.6 to 1.12 for angles of attack up to 34^o
Date: March 18, 1954
Creator: Osborne, Robert S. & Wornom, Dewey E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

Description: From Introduction: "The wings were tested in combination with fuselage similar to the one used in the 7- by 10-foot wind-tunnel investigations. The results are reported herein and are compared with results for three similar model wings on the transonic bump (references 1, 2, and 3)."
Date: February 6, 1951
Creator: Sutton, Fred B. & Martin, Andrew
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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 model 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" (p. 1).
Date: September 28, 1949
Creator: Martin, Andrew & Hunter, Harlo A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Mach Numbers of 1.41, 1.61, and 2.01

Description: "Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 of various arrangements of a 0.04956-scale model of the Convair F-102A airplane with faired inlets. Tests made of the model equipped with a plain wing, a wing with 6.4 percent conical camber, and a wing with 15 percent conical camber. Body modifications including an extended nose, a modified canopy, and extended afterbody fillets were evaluated" (p. 1).
Date: September 30, 1955
Creator: Spearman, M. Leroy & Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Transonic Speeds

Description: "Tests have been conducted in the Langley 8-foot transonic tunnel on a 0.04956-scale model of the Convair F-102A airplane which employed an indented and extended fuselage, cambered wing leading edges, and deflected wing tips. Force and moment characteristics were obtained for Mach numbers from 0.60 to 1.135 at angles of attack up to 20 degrees. In addition, tests were made over a limited angle-of-attack range to determine the effects of the cambered leading edges, deflected tips, and a nose sec… more
Date: April 11, 1955
Creator: Tempelmeyer, Kenneth E. & Osborne, Robert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102B Airplane at Mach Numbers of 1.41, 1.61, and 2.01: Coord No. AF-231

Description: Report discussing testing of a scale model of the Convair F-102B to determine its aerodynamic characteristics at several Mach numbers. Four basic body modifications and two afterbody configurations were evaluated.The body modifications were all found to slightly reduce values of minimum drag, but did not cause a change in the static stability and lift-curve-slope values compared to the F-102A.
Date: February 7, 1956
Creator: Driver, Cornelius & Robinson, Ross B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair TF-102A Airplane at Transonic Speeds, Coord. No. AF-120

Description: "The basic aerodynamic characteristics of a 0.04956-scale model of the Convair TF-102A airplane with controls undeflected have been determined at Mach numbers from 0.60 to 1.135 for angles of attack up to approximately 22 deg in the Langley 8-foot transonic tunnel. In addition, comparisons have been made with data obtained from a previous investigation of a 0.04956-scale model of the Convair F-102A airplane. The results indicated the TF-102A airplane was longitudinally stable for all conditions… more
Date: 1957~
Creator: Osborne, Robert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a 1/4-Scale Model of the Duct System for the General Electric P-1 Nuclear Powerplant for Aircraft

Description: Report discussing testing on a model of the General Electric P-1 nuclear powerplant to determine its internal aerodynamic characteristics. The main purposes of testing were to measure the mass-flow distribution of air, to measure the total-pressure losses for the duct components and complete model, and to determine modifications necessary to attain the desired performance characteristics.
Date: July 29, 1955
Creator: Wood, Charles C. & Henry, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a 6-Percent-Thick Symmetrical Circular-Arc Airfoil Having a 30-Percent-Chord Trailing-Edge Flap at a Mach Number of 6.9

Description: Memorandum presenting an investigation of the flow characteristics over a 6-percent-thick symmetrical circular-arc airfoil section with a 30-percent-chord trailing-edge flap at a Mach number of 6.90 and a Reynolds number of 1.65 x 10(sub 6). The model was tested over an angle-of-attack range of 0 to 16 degrees and a flap-deflection range of -16 degrees to 16 degrees. Results regarding pressure results and aerodynamic characteristics are provided.
Date: June 5, 1956
Creator: Ridyard, Herbert W. & Fetterman, David E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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