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[News Clip: Sable road test]

Description: Video footage from the KXAS-TV/NBC station in Fort Worth, Texas, to accompany a news story.
Date: January 3, 1986
Duration: 3 minutes 12 seconds
Creator: KXAS-TV (Television station : Fort Worth, Tex.)
Item Type: Refine your search to only Video
Partner: UNT Libraries Special Collections
open access

Evaluation of the carbon content of aerosols from the burn- ing of biomass in the Brazilian Amazon using thermal, op- tical and thermal-optical analysis methods

Description: Aerosol samples were collected at a pasture site in the Amazon Basin as part of the project LBA-SMOCC-2002 (Large-Scale Biosphere-Atmosphere Experiment in Amazonia - Smoke Aerosols, Clouds, Rainfall and Climate: Aerosols from Biomass Burning Perturb Global and Regional Climate). Sampling was conducted during the late dry season, when the aerosol composition was dominated by biomass burning emissions, especially in the submicron fraction. A 13-stage Dekati low-pressure impactor (DLPI) was used t… more
Date: June 3, 2011
Creator: Soto-Garcia, Lydia L.; Andreae, Meinrat O.; Andreae, Tracey W.; taxo, Paulo Ar-; Maenhaut, Willy; Kirchstetter, Thomas et al.
Item Type: Refine your search to only Article
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of the effect of clipping the tips of triangular wings of different thickness, camber, and aspect ratio - transonic bumb method

Description: Report presenting an investigation on a transonic bump to determine the aerodynamic characteristics of a series of triangular wings. Four basic triangular-wing plan forms with different aspect ratios, taper ratios, and combinations of tip clipping were tested over a range of Mach and Reynolds numbers. Results regarding angle of attack, drag coefficient, pitching-moment coefficient with lift coefficient, and various curves are provided.
Date: February 3, 1954
Creator: Emerson, Horace F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Force, moment, and pressure characteristics of several annular nose inlets at Mach number 3.85

Description: Report presenting an investigation to evaluate the overall performance characteristics of several annular nose inlets in the supersonic wind tunnel at a Mach number of 3.85. The four experimental configurations investigated consisted of a one-cone, a one-cone with low angle cowl, a two-cone, and an isentropic inlet. Results regarding the internal-flow performance, force measurements at zero angle of attack, overall performance comparison at zero angle of attack, and angle-of-attack force measur… more
Date: February 3, 1954
Creator: Connors, James F. & Woollett, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a Ram-Jet-Powered Helicopter Rotor on the Langley Helicopter Test Tower

Description: Report discussing tests on a helicopter rotor powered by ram-jet engines located at the rotor blade tips. Information about the basic hovering characteristics of the rotor and the propulsive characteristics of the ram-jet engine were obtained over a range of speeds and fuel rates. Results were also obtained in the power-off condition and with the engines removed.
Date: June 3, 1953
Creator: Carpenter, Paul J. & Radin, Edward J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Wind Tunnel Investigation of Several Wingless Missile Configurations at Supersonic Speeds

Description: Report presenting an investigation of several wingless missile configurations for a range of Mach numbers to determine their lift, drag, and pitching-moment coefficients. Results for missiles having nose controls and missiles having tail controls are provided. The results were also compared to a conventional missile with wings.
Date: February 3, 1958
Creator: Reese, David E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin NACA airfoil sections

Description: Report presenting a wind-tunnel investigation to determine the effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin symmetrical NACA 4-digit-series airfoil sections. The variations with Mach number of the lift, drag, and pitching moment for a 4-percent-chord-thick airfoil section are not significantly affected by a change of leading-edge radius from 0.18 to 0.53 percent of the chord. Results regardi… more
Date: July 3, 1950
Creator: Berggren, Robert E. & Graham, Donald J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Static Longitudinal Stability and Control Characteristics at a Mach Number of 1.40

Description: Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic tunnel to determine the longitudinal stability and control characteristics of a model of a supersonic airplane configuration at Mach number 1.40. The model had a 40 degree sweptback wing with 10-percent-thick circular-arc sections normal to the quarter-chord line. The results indicated a high degree of longitudinal stability that was fairly constant throughout the trim-lift-coefficient range.
Date: April 3, 1950
Creator: Spearman, M. Leroy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effect of aspect ratio on the subsonic aerodynamic characteristics of wings with NACA 65(sub 1)-210 sections

Description: Report presenting the results of tests of four model wings of aspect ratios 1, 2, 4, and 6 and with NACA 65(sub 1)-210 sections. The experimental lift-curve slope is compared with predictions from theory. Results regarding lift, drag, and pitching moment, lift-curve slope, drag divergence, minimum drag, and pitching moment are provided.
Date: February 3, 1950
Creator: Nelson, Warren H. & Erickson, Albert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of the effects of viscosity on the drag of bodies of revolution at a Mach number 1.5

Description: Report presenting testing to determine the effects of viscosity on the drag and base pressure characteristics of various bodies of revolution at a Mach number of 1.5. The models were tested with smooth surfaces and roughness to evaluate the effects of Reynolds number for both laminar and turbulent boundary layers. Results regarding the reduction of data, precision, effects of support interference, Schileren photographs, and theoretical calculations are provided.
Date: April 3, 1947
Creator: Chapman, Dean R. & Perkins, Edward W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure Distributions Over a Wing-Fuselage Model at Mach Numbers of 0.4 to 0.99 and at 1.2

Description: Report presenting pressure distributions over a prolate spheroid of fineness ratio 6 and over a combination of this body with an NACA 65-010 wing section for a range of Mach numbers. Results regarding wall and sting interference, nature of flow over a model in the transonic region, development of supersonic flow from subsonic flow, and a comparison of experimental and theoretical flow at subsonic stream Mach numbers are provided.
Date: November 3, 1948
Creator: Matthews, Clarence W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Horn Balances on a 45 Degree Sweptback Horizontal Tail Surface at High Subsonic Speeds

Description: A wind-tunnel investigation of horn balances on a 45 degree sweptback, semispan, horizontal tail surface was made to determine the effects of horn size and inboard-edge fairing at a Mach number of 0.30 and to determine the effects of compressibility up to a Mach number of 0.89. Presented are lift, drag, pitching-moment, and hinge-moment data and lift and hinge-moment parameters.
Date: December 3, 1948
Creator: Johnson, Harold S. & Thompson, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Transonic Investigation of the Aerodynamic Characteristics of Plate- and Bell- Type Outlets for Auxiliary Air

Description: Report presenting an investigation of the aerodynamic characteristics of several plate- and bell-type outlets discharging air into a transonic stream. The variation in discharge coefficient of the outlets is presented as a function of the rate of discharge. The discharge coefficient, jet wake, and surface pressure distribution are also provided.
Date: September 3, 1952
Creator: Nelson, William J. & Dewey, Paul E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A correlation with flight tests of results obtained from the measurement of wing pressure distributions on a 1/4-scale model of the X-1 airplane (10-percent-thick wing)

Description: Report presenting an investigation in the transonic tunnel of the aerodynamic characteristics of a scale model of an X-1 airplane in order to correlate wing pressure-distribution results obtained in a slotted wind tunnel with flight test data on the full-scale airplane. Results regarding basic pressure measurements, and correlation of pressure measurements are provided.
Date: September 3, 1952
Creator: Runckel, Jack F. & Henderson, James H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-speed static longitudinal and lateral stability characteristics of a model with leading-edge chord-extensions incorporated on a 40 degree sweptback circular-arc wing of aspect ratio 4 and taper ratio 0.50

Description: Report presenting an investigation to determine the aerodynamic effects at low speed of several wing leading-edge chord-extensions incorporated on a complete model with a 40 degree sweptback circular-arc wing of aspect ratio 4 and taper ratio 0.50. Testing indicated that the effectiveness of the chord-extension in increasing the stability is mainly dependent on the spanwise inboard-end location of the device. Results regarding the static longitudinal characteristics and effect of chord-extensio… more
Date: November 3, 1952
Creator: Goodson, Kenneth W. & Few, Albert G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A study of the zero-lift drag-rise characteristics of wing-body combinations near the speed of sound

Description: Comparisons of the shock phenomena and drag-rise increments for representative wing and central-body combinations with those for bodies of revolution with the same axial distributions of cross-sectional area normal to the air stream. An investigation was also presented of representative wing-body combinations with the body so indented that the axial distributions of cross-sectional areas for the combinations were the same as that for the original body. Results regarding unswept wing and cylindr… more
Date: September 3, 1952
Creator: Whitcomb, Richard T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of sweep on the maximum-lift characteristics of four aspect-ratio-4 wings at transonic speeds

Description: Report presenting an investigation at transonic speeds in the high-speed 7- by 10-foot tunnel to determine the effect of wing sweep on the maximum-lift characteristics of a series of wings with aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil sections. Testing occurred over a range of Mach and Reynolds numbers. Maximum lift coefficients were found to increase with increased sweep at lower Mach numbers but decreased with increase sweep at higher Mach numbers.
Date: October 3, 1950
Creator: Turner, Thomas R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical Calculation of the Effect of the Fuselage on the Spanwise Lift Distribution on a Wing

Description: Report presenting a method for calculating the effect of the fuselage on the spanwise lift distribution on a wing by applying a conformal-mapping procedure to the simplified lifting-surface theory. The calculations are also compared with experimental data and are found to generally agree.
Date: March 3, 1952
Creator: Zlotnick, Martin & Diederich, Franklin W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wing-flow measurements of longitudinal stability and control characteristics of a supersonic airplane configuration having a 42.8 degree sweptback circular arc wing with aspect ratio 4.0, taper ratio 0.50, and sweptback tail surfaces

Description: Report presenting the results of an investigation at transonic speeds by the wing-flow method of the longitudinal stability characteristics of a 42.8 degree sweptback supersonic airplane configuration. Lift, pitching-moment, and rolling-moment characteristics of the semispan model as well as stabilizer hinge moments and effective downwash at the tail were measured over a range of Mach numbers. The wing-flow data is compared to data for the same configuration from other research facilities.
Date: April 3, 1950
Creator: Crane, Harold L. & Adams, James J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Comparison of Two Techniques Utilizing Rocket-Propelled Vehicles for the Determination of the Damping-in-Roll Derivative

Description: Report presenting rocket-powered flight investigations for the purpose of comparing damping-in-roll results obtained from a torque-nozzle technique. Results regarding basic aerodynamic quantities, data from the torque-nozzle technique, wing-dropping phenomenon, and comparison of the values of the two techniques are provided.
Date: May 3, 1951
Creator: Stone, David G. & Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics 2: effect of compressor interstage air bleed

Description: Report presenting an analytical investigation to determine the effect of compressor interstage air bleed with the use of constant-area bleed ports on the acceleration characteristics of a typical high-pressure-ratio single-spool turbojet engine. Constant-area interstage bleed, properly located, gave smaller acceleration times than variable-area compressor exit bleed. Results regarding acceleration with interstage bleed, acceleration using constant-area interstage bleed in combination with compr… more
Date: July 3, 1953
Creator: Rebeske, John J., Jr. & Dugan, James F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of Lift and Drag for the Bell X-1 Research Airplane Having a 10-Percent-Thick Wing

Description: Report presenting drag coefficients during power-off transonic flight for the Bell X-1 airplane with a 10-percent-thick wing over a range of Mach numbers and pressure altitudes. The data was compared to an X-1 with an 8-percent-thick wing and a wind tunnel test with a 10-percent-thick wing. Information about necessary angle of attack, drag-rise Mach number, maximum lift-drag ratio, and drag coefficient at zero lift is provided.
Date: September 3, 1953
Creator: Saltzman, Edwin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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