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A comparison of the experimental and theoretical loading over triangular wings in sideslip at supersonic speeds

Description: The results of an experimental investigation of the load distribution over two triangular wings in sideslip at Mach numbers from 1.20 to 1.79 are presented and compared with theory. The two wings tested have identical plan form, 45 degrees sweepback of the leading edge, and an aspect ratio of 4.0. One model was composed of round-nose airfoil sections and the other of sharp-nose, biconvex sections. For both wings the maximum thickness of streamwise sections was 6 percent and was located at the 30-percent chord.
Date: May 18, 1951
Creator: Boyd, John W.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of two 25-percent-area trailing-edge flaps on an aspect ratio 2 triangular wing at subsonic and supersonic speeds

Description: Report presenting the results of an investigation of flap-type controls on a low-aspect-ratio triangular wing using NACA 0005-63 sections for a constant-chord and a constant-percent-chord control surface. Two flap profiles were investigated: one with a true contour and the other with a blunt trailing edge. Results regarding lift, drag, pitching moment, hinge moment, and rolling moments were obtained for several Mach numbers, a constant Reynolds number, and a range of angles of attack.
Date: July 22, 1952
Creator: Boyd, John W.
Partner: UNT Libraries Government Documents Department

Technical Support and Transfer of Geothrmal Technical Knowledge and Information

Description: The Geo-Heat Center (GHC) staff provided responses to 1442 technical support requests during the contract period (April 1, 2006 to September 30, 2007), which were six quarters under this contract. Our website, consisting of 1900 files, also contributes to our technical assistance activity. Downloaded files were 1,889,323 (3,448 per day) from our website, the total number of users was 1,365,258 (2,491 per day), and the total number of hits were 6,008,500 (10,064 per day). The GHC staff attended 60 workshops, short course and professional meeting and made 29 technical presentations. The staff also prepared and mailed out 2,000 copies of each of five issues of the GHC Quaterly Bulletin which contained 26 articles. We also mailed out approximately 5,000 papers and publications to interested individuals and organizations.
Date: November 14, 2007
Creator: Boyd, John W. Lund Tonya "Toni"
Partner: UNT Libraries Government Documents Department

Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22: triangular wing and canard on an extended body

Description: Report presenting an investigation of the static stability and control characteristics of a canard airplane configuration without analysis for a range of Mach numbers from 0.70 to 2.22. This configuration consisted of a triangular wing and triangular canard, a low aspect ratio vertical tail, and a modified Sears-Haack body. Data are presented for various combinations of the body, canard, wing, and vertical tail at severla angles of sideslip, angles of attack, and canard deflection angles.
Date: February 10, 1958
Creator: Boyd, John W. & Peterson, Victor L.
Partner: UNT Libraries Government Documents Department

Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22: longitudinal characteristics of an unswept wing and canard

Description: Report presenting the results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration without analysis for a range of Mach numbers. The configuration had an unswept wing, an unswept canard, a low aspect ratio vertical tail, and a Sears-Haack body. Data are presented for various combinations of the canard, wing, and vertical tail for a range of angles of attack and canard deflection angles.
Date: February 17, 1958
Creator: Peterson, Victor L. & Boyd, John W.
Partner: UNT Libraries Government Documents Department

Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22 : longitudinal characteristics of a triangular wing and canard

Description: Report presenting the results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration without analysis for a range of Mach numbers. Data are presented for a variety of angles of attack and canard angles.
Date: January 22, 1958
Creator: Boyd, John W. & Peterson, Victor L.
Partner: UNT Libraries Government Documents Department

A comparison of the experimental and theoretical loading over triangular wings at supersonic speeds

Description: Report presenting the results of an experimental investigation of the pressure distribution over two triangular wings at supersonic speeds. The two wings which were tested had identical plan forms, 45 degrees of sweepback of the leading edge, and an aspect ratio of 4.0, but different airfoil sections. Results regarding the pressure distribution at zero lift, flow characteristics and pressure distribution at angles of attack, normal-force coefficients, and application of results to other triangular wings are provided.
Date: January 3, 1951
Creator: Boyd, John W. & Phelps, E. Ray
Partner: UNT Libraries Government Documents Department

A comparison of theoretical and experimental loading on a 63 degrees swept-back wing at supersonic speeds

Description: Report presenting the pressure distribution over a highly swept wing at supersonic speeds to provide data for a comparison of measured and predicted loadings. The wing for this investigation had 63 degrees of sweepback of the leading edge, an aspect ratio of 3.5, and a taper ratio of 0.25. Over the regions influenced by the wing tip and trailing edge, the effects of viscosity apparently are responsible for the poorer agreement between theory and experiment.
Date: September 14, 1949
Creator: Stevens, Victor I. & Boyd, John W.
Partner: UNT Libraries Government Documents Department

Investigation at supersonic speed (M = 1.53) of the pressure distribution over a 63 degrees swept airfoil of biconvex section at zero lift

Description: Report presenting an investigation of the distribution of pressure at zero lift over the surface of a swept airfoil of biconvex section. The measured pressures are compare with theoretical values calculated from thin-airfoil theory. Results regarding pressure distributions, drag, and boundary-layer studies are provided.
Date: June 10, 1948
Creator: Frick, Charles W. & Boyd, John W.
Partner: UNT Libraries Government Documents Department

Effects of conical camber on the lift, drag, and pitching-moment characteristics of a triangular wing of aspect ratio 3.0

Description: Report presenting the results of an investigation to determine the effects of conical camber on the lift, drag, and pitching-moment characteristics of a wing-body combination with a triangular wing of aspect ratio 3.0. At subsonic speeds, the use of camber was found to result in substantial reductions in drag coefficients at lift coefficients above 0.15.
Date: February 19, 1957
Creator: Peterson, Victor L. & Boyd, John W.
Partner: UNT Libraries Government Documents Department

Effects of canards on airplane performance and stability

Description: Report presenting an investigation on canard airplane configurations in preference to a trailing-edge flap or tail control. Wide ranges in control plan form, size, and position and in wing plan form were found. Interference effects between the canard and other configuration components were not serious, and those that might be can be reduced by rearrangement of the vertical tail.
Date: July 7, 1958
Creator: Hall, Charles F. & Boyd, John W.
Partner: UNT Libraries Government Documents Department

Experimental investigation of aerodynamically balanced trailing-edge control surfaces on an aspect ratio 2 triangular wing at subsonic and supersonic speeds

Description: Report presenting the results of an experimental investigation of several types of aerodynamically balanced trailing-edge flaps on an aspect ratio 2 triangular wing are presented. The balancing devices tested consisted of flap overhang, paddles, rectangular and triangular horns, and trailing-edge tabs. Results regarding the lift, drag, pitching moment, hinge moment, and rolling moment are presented for a range of Mach numbers and a constant Reynolds number.
Date: February 13, 1953
Creator: Boyd, John W. & Pfyl, Frank A.
Partner: UNT Libraries Government Documents Department

Investigation at supersonic speed (M = 1.53) of the pressure distribution over a 63 degrees swept airfoil of biconvex section at several angles of attack

Description: Report presenting the results of an investigation at supersonic speed of the distribution of pressure over the surface of a swept airfoil of biconvex section at various angles of attack. The measurements are compared with supersonic lifting-surface theory, which generally indicated good agreement except over the regions of the airfoil influenced by the subsonic trailing edge and the tips. Results regarding the pressure distribution, boundary-layer studies, and normal force and pitching moment are provided.
Date: September 24, 1948
Creator: Katzen, Elliott D.; Frick, Charles W. & Boyd, John W.
Partner: UNT Libraries Government Documents Department

A study of conical camber for triangular and sweptback wings

Description: Report presenting a theoretical and experimental study to determine the effectiveness of camber in reducing the drag due to lift resulting from pressure forces acting on low-aspect-ratio triangular and sweptback wings. Design charts are included which aid in the selection of camber for various sweepback angles and Mach numbers. Results regarding drag characteristics and lift and moment characteristics are provided.
Date: November 18, 1955
Creator: Boyd, John W.; Migotsky, Eugene & Wetzel, Benton E.
Partner: UNT Libraries Government Documents Department