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Damping-in-Roll Characteristics of a 42.7 Degree Sweptback Wing as Determined From a Wind-Tunnel Investigation of a Twisted Semispan Wing

Description: Report presenting an investigation to determine the damping-in-roll characteristics of a 42.7 degree sweptback wing using a linearly twisted wing to represent a rolling wing. Results regarding the effect of the airfoil contour, damping-in-roll coefficient, wing-tip helix angle, and theoretical results are provided.
Date: August 8, 1949
Creator: Lockwood, Vernard E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Forces and moments on pointed blunt-nosed bodies of revolution at Mach numbers from 2.75 to 5.00

Description: Results of tests to determine the aerodynamic forces and moments on bodies of revolution at angles of attack from 0 degrees to 25 degrees are presented and compared with theory. Cones and ogives of fineness ratios 3 to 7 and two blunt-nosed body shapes with fineness ratios 3 and 5 were tested at Mach numbers from 2.75 to 5.00. Reynolds numbers were from 0.5 million to 6.4 million, depending on Mach number and body fineness ratio.
Date: August 8, 1952
Creator: Dennis, David H. & Cunningham, Bernard E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability and Control Characteristics of a Canard Missile Configuration for Mach Numbers From 1.1 to 1.93 as Determined From Free-Flight and Wind-Tunnel Investigation

Description: Report presenting a study of the supersonic longitudinal stability and control characteristics of a canard missile configuration using flight tests and wind-tunnel tests at a range of Mach numbers and Reynolds numbers. Good correlation was noted for the two techniques for slopes of lift and moment coefficients against angle of attack and for aerodynamic-center location.
Date: August 8, 1952
Creator: Curfman, Howard J., Jr. & Grigsby, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lateral-control investigation at transonic speeds of retractable spoiler and plug-type spoiler-slot ailerons on a tapered 60 degree sweptback wing of aspect ratio 2 : transonic-bump method

Description: Report presenting an investigation utilizing the transonic-bump technique through a range of Mach numbers in the high-speed 7- by 10-foot tunnel to determine the lateral control characteristics of retractable spoiler and plug-type spoiler-slot ailerons. The wing had a sweepback of 60 degrees at the quarter-chord line, an aspect ratio of 2, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The plug-type spoiler-slot aileron was found to be more effective in pr… more
Date: August 8, 1952
Creator: Hammond, Alexander D. & Watson, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Experimental Investigation of Flutter Characteristics of M and W Wings

Description: Report presenting the results of nine experimental flutter tests involving two flat-plate models and two rib and spar models of NACA 0012 airfoil sections in order to give a comparison of the flutter characteristics of wings with M and W type plan forms. The W plan form generally gave higher flutter speeds than the M plan forms.
Date: August 8, 1951
Creator: Herr, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of airfoil sections on two triangular-wing-fuselage configurations at transonic speeds from tests by the NACA wing-flow method

Description: Report presenting tests using the NACA wing-flow method at a range of Mach numbers to determine the aerodynamic characteristics of four triangular-wing-fuselage models. Measurements of the normal force, chord force, and pitching moment for various angles of attack. Two models had wings of aspect ratio 2.31, one with an NACA 65-009 airfoil section and one with a 9-percent-thick biconvex section, and two with wings of aspect ratio 4, one with an NACA 65-006 airfoil and one with a 6-percent-thick … more
Date: August 8, 1951
Creator: Hall, Albert W. & McKay, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of effect of interference on lateral-stability characteristics of four NACA 23012 wings, an elliptical and a circular fuselage and vertical fins

Description: Report presents the results of a wind-tunnel investigation of the effect of wing-fuselage interference on lateral-stability characteristics made in the NACA 7 by 10-foot wind tunnel on four fuselages and two fins, representing high-wing, low-wing, and midwing monoplanes. The fuselages are of circular and elliptical cross section. The wings have rounded tips and, in plan form, one is rectangular and the three are tapered 3:1 with various amounts of sweep. The rate of change in the coefficients o… more
Date: August 8, 1940
Creator: House, Rufus O. & Wallace, Arthur R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison between prediction and experiment for all-movable wing and body combinations at supersonic speeds: Lift, pitching moment, and hinge moment

Description: From Summary: "A simple method is presented for estimating lift, pitching-moment, and hinge-moment characteristics of all-movable wings in the presence of a body as well as the characteristics of wing-body combinations employing such wings. In general, good agreement between the method and experiment was obtained for the lift and pitching moment of the entire wing-body combination and for the lift of the wing in the presence of the body. The method is valid for moderate angles of attack, wing d… more
Date: August 8, 1952
Creator: Nielsen, Jack N.; Kaattari, George E. & Drake, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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