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 Decade: 1940-1949
 Year: 1947
 Month: March
 Collection: National Advisory Committee for Aeronautics Collection
Aerodynamic Characteristics of Three Deep-Stepped Planing-Tail Flying-Boat Hulls

Aerodynamic Characteristics of Three Deep-Stepped Planing-Tail Flying-Boat Hulls

Date: March 13, 1947
Creator: Riebe, John M.
Description: An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of three deep-stepped planing-tail flying-boat hulls differing only in the amount of step fairing. The hulls were derived by increasing the unfaired step depth of a planing-tail hull of a previous aerodynamic investigation to a depth about 92 percent of the hull beam. Tests were also made on a transverse-stepped hull with an extended afterbody for the purpose of comparison and in order to extend and verify the results of a previous investigation. The investigation indicated that the extended afterbody hull had a minimum drag coefficient about the same as a conventional hull, 0.0066, and an angle-of-attack range for minimum drag coefficient of 0.0057 which was 14 percent less than the transverse stepped hull with extended afterbody; the hulls with step fairing had up to 44 percent less minimum drag coefficient than the transverse-stepped hull, or slightly more drag than a streamlined body having approximately the same length and volume. Longitudinal and lateral instability varied little with step fairing and was about the same as a conventional hull.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic measurements made during Navy investigation of human tolerance to wind blasts

Aerodynamic measurements made during Navy investigation of human tolerance to wind blasts

Date: March 11, 1947
Creator: Loving, Donald L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Wind-Tunnel Investigation of R-4360-18 Power-Plant Installation for XR60 Airplane, 3, Performance of Induction and Exhaust Systems

Altitude-Wind-Tunnel Investigation of R-4360-18 Power-Plant Installation for XR60 Airplane, 3, Performance of Induction and Exhaust Systems

Date: March 26, 1947
Creator: Dupree, David T.
Description: A study has been made of the performance of the induction and the exhaust systems on the XR60 power-plant installation as part of an investigation conducted in the Cleveland altitude wind tunnel. Altitude flight conditions from 5000 to 30,000 feet were simulated for a range of engine powers from 750 to 3000 brake horsepower. Slipstream rotation prevented normal pressure recoveries in the right side of the main duct in the region of the right intercooler cooling-air duct inlet. Total-pressure losses in the charge-air flow between the turbosupercharger and the intercoolers were as high as 2.1 inches of mercury. The total-pressure distribution of the charge air at the intercooler inlets was irregular and varied as much as 1.0 inch of mercury from the average value at extreme conditions, Total-pressure surveys at the carburetor top deck showed a variation from the average value of 0.3 inch of mercury at take-off power and 0.05 inch of mercury at maximum cruising power, The carburetor preheater system increased the temperature of the engine charge air a maximum of about 82 F at an average cowl-inlet air temperature of 9 F, a pressure altitude of 5000 feet, and a brake horsepower of 1240.
Contributing Partner: UNT Libraries Government Documents Department
Buckling stresses of simply supported rectangular flat plates in shear

Buckling stresses of simply supported rectangular flat plates in shear

Date: March 1, 1947
Creator: Stein, Manuel
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Calculation of Compressible Flows with Local Regions of Supersonic Velocity

The Calculation of Compressible Flows with Local Regions of Supersonic Velocity

Date: March 1, 1947
Creator: Goethert, B.
Description: This report addresses a method for the approximate calculation of compressible flows about profiles with local regions of supersonic velocity. The flow around a slender profile is treated as an example.
Contributing Partner: UNT Libraries Government Documents Department
A collection of the collapsed results of general tank tests of miscellaneous flying-boat-hull models

A collection of the collapsed results of general tank tests of miscellaneous flying-boat-hull models

Date: March 1, 1947
Creator: Locke, F W S , Jr
Description: Presented here are the summary charts of the collapsed results of general tank tests of about 100 flying boat hull models. These summary charts are intended to be used as an engineering tool to enable a flying boat designer to grasp more quickly the significance of various hull form parameters as they influence his particular airplane. The form in which the charts are prepared is discussed in some detail in order to make them clearer to the designer. This is a data report, and no attempt has been made to produce conclusions or correlations of the usual sort. However, some generalizations are put forward on the various methods in which summary charts may be used.
Contributing Partner: UNT Libraries Government Documents Department
Comparative drag measurements at transonic speeds of an NACA 65-006 airfoil and a symmetrical circular-arc airfoil

Comparative drag measurements at transonic speeds of an NACA 65-006 airfoil and a symmetrical circular-arc airfoil

Date: March 6, 1947
Creator: Thompson, Jim Rogers
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparative tests on extruded 14S-T and extruded 24S-T hat-shape stiffener sections

Comparative tests on extruded 14S-T and extruded 24S-T hat-shape stiffener sections

Date: March 1, 1947
Creator: Holt, Marshall
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cooling of Gas Turbines, 2, Effectiveness of Rim Cooling of Blades

Cooling of Gas Turbines, 2, Effectiveness of Rim Cooling of Blades

Date: March 18, 1947
Creator: Wolfenstein, Lincoln
Description: An analysis is presented of rim cooling of gas-turbine blades; that is, reducing the temperature at the base of the blade (wheel rim), which cools the blade by conduction alone. Formulas for temperature and stress distributions along the blade are derived and, by the use of experimental stress-rupture data for a typical blade alloy, a relation is established between blade life (time for rupture), operating speed, and amount of rim cooling for several gas temperatures. The effect of blade parameter combining the effects of blade dimensions, blade thermal conductivity, and heat-transfer coefficient is determined. The effect of radiation on the results is approximated. The gas temperatures ranged from 1300F to 1900F and the rim temperature, from 0F to 1000F below the gas temperature. This report is concerned only with blades of uniform cross section, but the conclusions drawn are generally applicable to most modern turbine blades. For a typical rim-cooled blade, gas temperature increases are limited to about 200F for 500F of cooling of the blade base below gas temperature, and additional cooling brings progressively smaller increases. In order to obtain large increases in thermal conductivity or very large decreases in heat-transfer coefficient or blade length or necessary. The increases ...
Contributing Partner: UNT Libraries Government Documents Department
Critical combinations of shear and direct stress for simply supported rectangular flat plates

Critical combinations of shear and direct stress for simply supported rectangular flat plates

Date: March 1, 1947
Creator: Batdorf, S B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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