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Technical Report Archive and Image Library
Wind-tunnel investigation of two airfoils with 25-percent-chord Gwinn and plain flaps
Date: May 1, 1940
Creator: Ames, Milton B , Jr
Description: Aerodynamic force tests of an NACA 23018 airfoil with a Gwinn flap having a chord 25 percent of the overall chord and of an NACA 23015 airfoil with a plain flap having a 25-percent chord were conducted to determine the relative merits of the Gwinn and the plain flaps. The tests indicated that, based on speed-range ratios, the plain flap was more effective than the Gwinn flap. At small flap deflections, the plain flap had lower drag coefficients at lift-coefficient values less than 0.70. For lift coefficients greater than 0.70, however, the Gwinn flap at all downward flap deflections had the lower drag coefficients.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc54647/
Wind-tunnel investigation of two vertical-takeoff-and-landing jet bomber airplane configurations at Mach numbers of 1.94 and 2.40
Date: October 31, 1956
Creator: Jones, Robert A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc63098/
Wind-tunnel investigation of unshielded horn balances on a horizontal tail surface
Date: July 1, 1947
Creator: Lowry, John G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc55432/
Wind-tunnel investigation of wing ducts on a single engine pursuit airplane
Date: October 1, 1943
Creator: Czarnecki, K R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61163/
Wind-tunnel investigation of wing inlets for a four-engine airplane
Date: March 11, 1947
Creator: Bartlett, Walter A , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc58127/
Wind-tunnel investigation of wings with ordinary ailerons and full-span external-airfoil flaps
Date: January 1, 1937
Creator: Platt, Robert C
Description: Report presents an investigation carried out in the NACA 7- by 10-foot wind tunnel of an NACA 23012 airfoil equipped, first, with a full-span NACA 23012 external-airfoil flap having a chord 0.20 of the main airfoil chord and with a full-span aileron with a chord 0.12 of the main airfoil chord on the trailing edge of the main airfoil and equipped second, with a 0.30-chord full-span NACA 23012 external-airfoil flap and a 0.13-chord full-span aileron. The results are arranged in three groups, the first two of which deal with the airfoil characteristics of the two airfoil-flap combinations and with the internal-control characteristics of the airfoil-flap-aileron combinations. The third group of tests deals with several means for balancing ailerons mounted on a special large-chord NACA 23012 external-airfoil flap. The tests included an ordinary aileron, a curtained-nose balance, a frise balance, and a tab.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc66260/
Wind-tunnel investigation to determine the aerodynamic characteristics in steady roll of a model at high subsonic speeds
Date: January 21, 1953
Creator: Kuhn, Richard E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc59470/
A Wind-Tunnel Investigation to Determine the Effect of Various Head Designs on the Aerodynamic Characteristics in Pitch of the Army Ordnance Corps T205 3.5-Inch Heat Rocket
Date: January 1, 1952
Creator: Morrison, William D., Jr.
Description: The aerodynamic characteristics in pitch of the Army Ordnance Corps T205 3.5-inch HEAT rocket with various head designs and one fin modification have been determined at velocities of 500, 700 and 900 feet per second in the Langley high-speed 7- by 10-foot tunnel. The results presented are those of the full-scale model. Comparison of results obtained at 500 feet per second shows, in general, that for changes on the forward portion of the head the missile configurations having the greatest stability - most rearward center-of-loads location - were those having the highest drag. However, very limited comparisons indicate that the shape of the rear position of the head may be an important factor in reducing the drag and increasing the restoring moments. Generally, large increases in drag were noted for the various head designs with an increase in Mach number from 0.62 to 0.82. Pitching-moment-curve slopes increased with Mach number on all models except those having reasonably well-faired forward sections. These models showed a decrease in stability with increases in Mach number.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc64690/
Wind-tunnel investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability characteristics of a complete-model swept-wing configuration at high subsonic speeds
Date: November 1, 1956
Creator: Wiggins, James W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc56213/
Wind-Tunnel Investigations of Diving Brakes
Date: November 1, 1942
Creator: Fucha, D.
Description: Unduly high diving speeds can be effectively controlled by diving brakes but their employment involves at the same time a number of disagreeable features: namely, rotation of zero lift direction, variation of diviving moment, and, the creation of a potent dead air region.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc64005/