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 Collection: National Advisory Committee for Aeronautics Collection
Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50

Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50

Date: September 15, 1958
Creator: Anderson, B. H. & Bowditch, D. N.
Description: Performance of internal contraction, axisymmetric inlet with isentropic compression surfaces on cowl and centerbody at Mach 2.0 to 2.7.
Contributing Partner: UNT Libraries Government Documents Department
The static and dynamic-rotary stability derivatives at subsonic speeds of a model of the X-15 research airplane

The static and dynamic-rotary stability derivatives at subsonic speeds of a model of the X-15 research airplane

Date: September 15, 1958
Creator: Lopez, Armando E & Tinling, Bruce E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the low-speed aerodynamic characteristics of a hypersonic glider configuration

Wind-tunnel investigation of the low-speed aerodynamic characteristics of a hypersonic glider configuration

Date: September 15, 1958
Creator: Kelly, Mark W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Mach numbers from 2.5 to 3.5 of a canard bomber configuration designed for supersonic cruise flight

Aerodynamic characteristics at Mach numbers from 2.5 to 3.5 of a canard bomber configuration designed for supersonic cruise flight

Date: September 10, 1958
Creator: Carmel, Melvin R; Kelly, Thomas C & Gregory, Donald T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10

Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10

Date: September 10, 1958
Creator: Swanson, A. G.
Description: Heat-transfer measurements were made on a simulated glide-rocket shape in free flight at Mach numbers up to 10 and free-stream Reynolds numbers of 2 x 10 based on distance along surface from apex and 3 x 10 based on nominal leading-edge diameter. The model simulated the bottom of a 75 deg delta wing at 8O deg angle of attack. The data indicated that for the test conditions a modified three-dimensional stagnation-point theory will predict to reasonable engineering accuracy the heating on a highly swept wing leading edge, the heating being reduced by sweep by the 3/2 power of the cosine of the sweep angle. The data also indicate that laminar heating rates over the windward surface of a highly swept flat glider wing at moderate angles of attack can be predicted with reasonable engineering accuracy by flat-plate theory using wedge local flow conditions and basing Reynolds numbers on lengths from the wing leading edge parallel to the surface center line.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at Mach numbers from 0.6 to 1.4 of several ejected pilot-seat models

Wind-tunnel investigation at Mach numbers from 0.6 to 1.4 of several ejected pilot-seat models

Date: September 10, 1958
Creator: Summers, James L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane

Wind-tunnel investigation of the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane

Date: September 10, 1958
Creator: Cocke, Bennie W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Hovering and Transition Flight Tests of a 1/5-Scale Model of the Ryan X-13 VTOL Airplane

Hovering and Transition Flight Tests of a 1/5-Scale Model of the Ryan X-13 VTOL Airplane

Date: September 9, 1958
Creator: Smith, C. C., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Calculated and Experimental Temperatures and Coolant Pressure Losses for a Cascade of Small Air-Cooled Turbine Rotor Blades

Comparison of Calculated and Experimental Temperatures and Coolant Pressure Losses for a Cascade of Small Air-Cooled Turbine Rotor Blades

Date: September 4, 1958
Creator: Stepka, Francis S
Description: Average spanwise blade temperatures and cooling-air pressure losses through a small (1.4-in, span, 0.7-in, chord) air-cooled turbine blade were calculated and are compared with experimental nonrotating cascade data. Two methods of calculating the blade spanwise metal temperature distributions are presented. The method which considered the effect of the length-to-diameter ratio of the coolant passage on the blade-to-coolant heat-transfer coefficient and assumed constant coolant properties based on the coolant bulk temperature gave the best agreement with experimental data. The agreement obtained was within 3 percent at the midspan and tip regions of the blade. At the root region of the blade, the agreement was within 3 percent for coolant flows within the turbulent flow regime and within 10 percent for coolant flows in the laminar regime. The calculated and measured cooling-air pressure losses through the blade agreed within 5 percent. Calculated spanwise blade temperatures for assumed turboprop engine operating conditions of 2000 F turbine-inlet gas temperature and flight conditions of 300 knots at a 30,000-foot altitude agreed well with those obtained by the extrapolation of correlated experimental data of a static cascade investigation of these blades.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Injectors With a 200-pound-thrust Ammonia-oxygen Engine

Comparison of Injectors With a 200-pound-thrust Ammonia-oxygen Engine

Date: September 4, 1958
Creator: Clark, B. J. & Priem, R. J.
Description: Injection techniques for 200-pound thrust ammonia- oxygen rocket engine.
Contributing Partner: UNT Libraries Government Documents Department