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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
Development of a supersonic area rule and an application to the design of a wing-body combination having high lift-to-drag ratios

Development of a supersonic area rule and an application to the design of a wing-body combination having high lift-to-drag ratios

Date: January 1, 1953
Creator: Fischetti, T. L. & Whitcomb, R. T.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wing pressure distributions over the lift range of the convair xf-92a delta-wing airplane at subsonic and transonic speeds

Wing pressure distributions over the lift range of the convair xf-92a delta-wing airplane at subsonic and transonic speeds

Date: November 30, 1955
Creator: Jordan, G. H. & Keener, E. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of rate, area, and distribution of impingement of waterdrops on various airfoils from trajectories obtained on the differential analyzer

Determination of rate, area, and distribution of impingement of waterdrops on various airfoils from trajectories obtained on the differential analyzer

Date: February 16, 1949
Creator: Guibert, A. G.; Janssen, E. & Robbins, W. M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Compilation and Analysis of US Turbojet and Ram-Jet Engine Characteristics

Compilation and Analysis of US Turbojet and Ram-Jet Engine Characteristics

Date: November 27, 1956
Creator: Cesaro, R. S. & Walker, C. L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Material compatibility with gaseous fluorine

Material compatibility with gaseous fluorine

Date: January 1, 1957
Creator: Douglass, H. W. & Price, H. G., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of Ice Formations on Section Drag of Swept NACA 63A-009 Airfoil with Partial-Span Leading-Edge Slat for Various Modes of Thermal Ice Protection

Effect of Ice Formations on Section Drag of Swept NACA 63A-009 Airfoil with Partial-Span Leading-Edge Slat for Various Modes of Thermal Ice Protection

Date: March 15, 1954
Creator: VonGlahn, Uwe H. & Gray, Vernon H.
Description: The effects of primary and runback ice formations on the section drag of a 36 deg swept NACA 63A-009 airfoil section with a partial-span leading-edge slat were studied over a range of angles of attack from 2 to 8 deg and airspeeds up to 260 miles per hour for icing conditions with liquid-water contents ranging from 0.39 to 1.23 grams per cubic meter and datum air temperatures from 10 to 25 F. The results with slat retracted showed that glaze-ice formations caused large and rapid increases in section drag coefficient and that the rate of change in section drag coefficient for the swept 63A-009 airfoil was about 2-1 times that for an unswept 651-212 airfoil. Removal of the primary ice formations by cyclic de-icing caused the drag to return almost to the bare-airfoil drag value. A comprehensive study of the slat icing and de-icing characteristics was prevented by limitations of the heating system and wake interference caused by the slat tracks and hot-gas supply duct to the slat. In general, the studies showed that icing on a thin swept airfoil will result in more detrimental aerodynamic characteristics than on a thick unswept airfoil.
Contributing Partner: UNT Libraries Government Documents Department
Determination of rate, area, and distribution of impingement of of waterdrops on various airfoils from trajectories obtained on the differential analyzer

Determination of rate, area, and distribution of impingement of of waterdrops on various airfoils from trajectories obtained on the differential analyzer

Date: February 16, 1949
Creator: Guibert, A. G.; Janssen, E. & Robbins, W. M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effectiveness of Thermal-Pneumatic Airfoil-Ice-Protection System

Effectiveness of Thermal-Pneumatic Airfoil-Ice-Protection System

Date: April 13, 1951
Creator: Gowan, William H., Jr. & Mulholland, Donald R.
Description: Icing and drag investigations were conducted in the NACA Lewis icing research tunnel employing a combination thermal-pneumatic de-icer mounted on a 42-inch-chord NACA 0018 airfoil. The de-icer consisted of a 3-inch-wide electrically heated strip symmetrically located about the leading edge with inflatable tubes on the upper and lower airfoil surfaces aft of the heated area. The entire de-icer extended to approximately 25 percent of chord. A maximum power density of 9.25 watts per square inch was required for marginal ice protection on the airfoil leading edge at an air temperature of 00 F and an airspeed of 300 miles per hour. Drag measurements indicated, that without icing, the de-icer installation increased the section drag to approximately 140 percent of that of the bare airfoil; with the tubes inflated, this value increased to a maximum of approximately 620 percent. A 2-minute tube-inflation cycle prevented excessive ice formation on the inflatable area although small scattered residual Ice formations remained after inflation and were removed intermittently during later cycles. Effects of the time lag of heater temperatures after initial application of power and the insulating effect of ice formations on heater temperatures were also determined.
Contributing Partner: UNT Libraries Government Documents Department
Effects of surface roughness and extreme cooling on boundary-layer transition for 15 deg cone-cylinder in free flight at Mach numbers to 7.6

Effects of surface roughness and extreme cooling on boundary-layer transition for 15 deg cone-cylinder in free flight at Mach numbers to 7.6

Date: March 5, 1958
Creator: Rabb, L. & Krasnican, M. J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls

Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls

Date: March 10, 1958
Creator: Robinson, R. B.
Description: An investigation of the aerodynamic characteristics of several hypersonic missile configurations with various canard controls for an angle-of-attack range from 0 deg to about 28 deg at sideslip angles of about 0 deg and 4 deg at a Mach number of 2.01 has been made in the Langley 4- by 4-foot supersonic pressure tunnel. The configurations tested were a body alone which had a ratio of length to diameter of 10, the body with a 10 deg flare, the body with cruciform fins of 5 deg or 15 deg apex angle, and a flare-stabilized rocket model with a modified Von Karman nose. Various canard surfaces for pitch control only were tested on the body with the 10 deg flare and on the body with both sets of fins. The results indicated that the addition of a flared afterbody or cruciform fins produced configurations which were longitudinally and directionally stable. The body with 5 deg fins should be capable of producing higher normal accelerations than the flared body. A l l of the canard surfaces were effective longitudinal controls which produced net positive increments of normal force and pitching moments which progressively decreased with increasing angle of attack.
Contributing Partner: UNT Libraries Government Documents Department
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