You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Tests in the Variable Density Wind Tunnel to Investigate the Effects of Scale and Turbulence on Airfoil Characteristics

Tests in the Variable Density Wind Tunnel to Investigate the Effects of Scale and Turbulence on Airfoil Characteristics

Date: February 1, 1931
Creator: Stack, John
Description: The effect of scale and turbulence on the lift and drag of five airfoils the NACA 0006, the NACA 0021, the Clark Y and the USA 35-A, and the USN PS6, have been investigated in the Variable Density Wind Tunnel of the NACA. Tests were made over a wide scale range for only two different conditions of turbulence.
Contributing Partner: UNT Libraries Government Documents Department
Tests of 10-inch 24S-T aluminum-alloy shear panels with 1-1/2-inch holes I

Tests of 10-inch 24S-T aluminum-alloy shear panels with 1-1/2-inch holes I

Date: June 1, 1943
Creator: Levin, L Ross
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of 10 inch 24S-T aluminum-alloy shear panels with 1-1/2 inch holes II : panels having holes with notched edges

Tests of 10 inch 24S-T aluminum-alloy shear panels with 1-1/2 inch holes II : panels having holes with notched edges

Date: April 1, 1944
Creator: Levin, L Ross
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of 16 related airfoils at high speed

Tests of 16 related airfoils at high speed

Date: January 1, 1935
Creator: Stack, John & Von Doenhoff, Albert E
Description: In order to provide information that might lead to the development of better propeller section, 13 related symmetrical airfoils were tested in the NACA high-speed wind tunnel for a study of the effect of thickness form on the aerodynamic characteristics. The thickness-form variables studies were the value of the maximum thickness, the position along the chord at which the maximum thickness occurs, and the value of the leading-edge radius. The tests were conducted through the low angle-of-attack range for speeds extending from 35 percent of that of sound to slightly in excess of the speed at which a compressibility burble, or breakdown of flow, occurs. The corresponding Reynolds number range is 350,000 to 750,000.
Contributing Partner: UNT Libraries Government Documents Department
Tests of a 0.30 scale semispan model of the Douglas XTB2D-1 airplane wing and fuselage combination in the NACA 19-foot pressure tunnel I : full-span flap and air-brake investigation

Tests of a 0.30 scale semispan model of the Douglas XTB2D-1 airplane wing and fuselage combination in the NACA 19-foot pressure tunnel I : full-span flap and air-brake investigation

Date: September 1, 1944
Creator: Russell, Robert T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a 0.30-scale semispan model of the Douglas XTB2D-1 airplane wing and fuselage combination in the NACA 19-foot pressure tunnel II : roll-flap positioning and lateral-control investigation

Tests of a 0.30-scale semispan model of the Douglas XTB2D-1 airplane wing and fuselage combination in the NACA 19-foot pressure tunnel II : roll-flap positioning and lateral-control investigation

Date: September 1, 1944
Creator: Russell, Robert T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a 0.1475c aileron with a tab on low-drag section for Curtiss XP-60 airplane in the low-turbulence tunnel

Tests of a 0.1475c aileron with a tab on low-drag section for Curtiss XP-60 airplane in the low-turbulence tunnel

Date: November 1, 1941
Creator: Underwood, W J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a 1/7-scale powered model of the Kaiser tailless airplane in the Langley full-scale tunnel

Tests of a 1/7-scale powered model of the Kaiser tailless airplane in the Langley full-scale tunnel

Date: March 1, 1946
Creator: Rickey, E A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a 1/7-Scale Semispan Model of the XB-35 Airplane in the Langley 19-Foot Pressure Tunnel

Tests of a 1/7-Scale Semispan Model of the XB-35 Airplane in the Langley 19-Foot Pressure Tunnel

Date: January 16, 1946
Creator: Teplitz, Jerome; Kayten, Gerald G. & Cancro, Patrick A.
Description: A 1/7 scale semispan model of the XB-35 airplane was tested in the Langley 10 foot pressure tunnel, primarily for the purpose of investigating the effectiveness of a leading-edge slot for alleviation of stick-fixed longitudinal instability at high angles of attack caused by early tip stalling and a device for relief of stick-free instability caused by elevon up-floating tendencies at high angles of attack. Results indicated that the slot was not adequate to provide the desired improvement in stick-fixed stability. The tab-flipper device provided improvement in stick-free stability abd two of the linkage combinations tested gave satisfactory variations of control force with airspeed for all conditions except that in which the wing-tip "pitch-control" flap was fully deflected. However, the improvement in control force characteristics was accompanied by a detrimental effect on stick-fixed stability because of the pitching moments produced by the elevon tab deflection.
Contributing Partner: UNT Libraries Government Documents Department
Tests of a 1/14-scale powered model of the XB-36 airplane in the Langley 19-foot pressure tunnel I : stalling characteristics and aileron effectiveness of several wing and flap arrangements

Tests of a 1/14-scale powered model of the XB-36 airplane in the Langley 19-foot pressure tunnel I : stalling characteristics and aileron effectiveness of several wing and flap arrangements

Date: February 1, 1945
Creator: Sivells, James C
Description: None
Contributing Partner: UNT Libraries Government Documents Department