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100 Areas technical activities report - physics, July 1951

Description: This is the monthly 100 areas technical activities report for the physics group for the month of July 1951. This group was concerned with pile related studies. Work discussed includes neutron attenuation measurements in pile shielding test facilities, studies of physical properties of shielding materials (concrete), work on a xenon generator and separation facility, further development and shielding work for a neutron spectrometer, continued work on a magnetic spectrometer, and counting equipment. Studies of neutron fluxes from exponential piles, and criticality studies are also discussed.
Date: August 3, 1951

Acid-Mine-Drainage Problems: Anthracite Region of Pennsylvania

Description: Report from the U.S. Bureau of Mines discussing the anthracite region of Pennsylvania and the efforts to prevent coal-mine drainage into nearby streams. According to the introduction, "The purpose of this report is not to develop a practicable or feasible method or process of treating acid mine water but rather to present available factual and deduced data that may be useful in showing pH range over which the treatment is to take place and the sludge products most likely to be handled" (p. 2).
Date: 1951
Creator: Ash, S. H. (Simon Harry), b. 1889; Felegy, E. W.; Kennedy, D. O. & Miller, P. S.

Adaptation of a Cascade Impactor to Flight Measurement of Droplet Size in Clouds

Description: A cascade impactor, an instrument for obtaining: the size distribution of droplets borne in a low-velocity air stream, was adapted for flight cloud droplet-size studies. The air containing the droplets was slowed down from flight speed by a diffuser to the inlet-air velocity of the impactor. The droplets that enter the impactor impinge on four slides coated with magnesium oxide. Each slide catches a different size range. The relation between the size of droplet impressions and the droplet size was evaluated so that the droplet-size distributions may be found from these slides. The magnesium oxide coating provides a permanent record. of the droplet impression that is not affected by droplet evaporation after the. droplets have impinged.
Date: September 18, 1951
Creator: Levine, Joseph & Kleinknecht, Kenneth S.

Addition of standard quantities of chemicals in certain reduction operations in the 234-5 Building

Description: A proposal by ``S`` Division that operations be simplified by adding fixed amounts of calcium and iodine in the reduction step as a time saving device has been investigated. Ten test runs in the 410--430 gram range have been compared with twenty normal runs made in this period. The average yields were 98.27% for the normal method and 98.26% for the test runs. No effect on individual yields by the variance in percent calcium and the iodine ratio was observed. Seventy percent of the runs normally fall into the 410--430 gram range. By controlled compositing of the feed batches, it should be possible to increase the percentage of the PuF{sub 4} runs that fall in this range.
Date: September 28, 1951
Creator: Desposato, F.E.

Additional studies of the stability and controllability of an unswept-wing vertically rising airplane model in hovering flight including studies of various tethered landing techniques

Description: Report discussing the results of an investigation to determine the stability and control characteristics of a flying model of an unswept-wing vertically rising airplane. Information about stabilization, maneuverability, rolling motions, and landings is provided.
Date: November 6, 1951
Creator: Bates, William R.; Lovell, Powell M., Jr. & Smith, Charles C., Jr.

Aerodynamic characteristics at transonic speeds of a 69 degree delta wing with a triangular plan-form control having a skewed hinge axis and an overhang balance : transonic-bump method

Description: From Introduction: "Presented in this paper are the results of an investigation of a semispan model of a delta wing with 60^o sweepback at the leading edge which was equipped with a large triangular control having an overhang balance mounted on a skewed hinge axis. The purpose of this investigation was to determine the aerodynamic characteristics of a delta wing with a control which was designed to provide aerodynamic balance at zero control deflection based on the span load distribution of reference 1."
Date: February 6, 1951
Creator: Wiley, Harleth G

Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

Description: From Introduction: "The wings were tested in combination with fuselage similar to the one used in the 7- by 10-foot wind-tunnel investigations. The results are reported herein and are compared with results for three similar model wings on the transonic bump (references 1, 2, and 3)."
Date: February 6, 1951
Creator: Sutton, Fred B & Martin, Andrew

Aerodynamic Characteristics of a Flying-Boat Hull Having a Length-Beam Ratio of 15, TED No. NACA 2206

Description: An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of a flying-boat hull of a length-beam ratio of 15 in the presence of a wing. The investigation was an extension of previous tests made on hulls of length-beam ratios of 6, 9, and 12; these hulls were designed to have approximately the same hydrodynamic performance with respect to spray and resistance characteristics. Comparison with the previous investigation at lower length-beam ratios indicated a reduction in minimum drag coefficients of 0.0006 (10 peroent)with fixed transition when the length-beam ratio was extended from 12 to 15. As with the hulls of lower length-beam ratio, the drag reduction with a length-beam ratio of 15 occurred throughout the range of angle of attack tested and the angle of attack for minimum drag was in the range from 2deg to 3deg. Increasing the length-beam ratio from 12 to 15 reduced the hull longitudinal instability by an mount corresponding to an aerodynamic-center shift of about 1/2 percent of the mean aerodynamic chord of the hypothetical flying boat. At an angle of attack of 2deg, the value of the variation of yawing-moment coefficient with angle of yaw for a length-beam ratio of 15 was 0.00144, which was 0.00007 larger than the value for a length-beam ratio of 12.
Date: January 23, 1951
Creator: Riebe, John M. & Naeseth, Rodger L.

Aerodynamic characteristics of a slender cone-cylinder body of revolution at a Mach number of 3.85

Description: An experimental investigation of the aerodynamics of a slender cone-cylinder body of revolution was conducted at a Mach number of 3.85 for angles of attack of 0 degree to 10 degrees and a Reynolds number of 3.85x10(exp 6). Boundary-layer measurements at zero angle of attack are compared with the compressible-flow formulations for predicting laminar boundary-layer characteristics. Comparison of experimental pressure and force values with theoretical values showed relatively good agreement for small angles of attack. The measured mean skin-friction coefficients agreed well with theoretical values obtained for laminar flow over cones.
Date: November 5, 1951
Creator: Jack, John R

Aerodynamic Characteristics of Bodies at Supersonic Speeds: A Collection of Three Papers

Description: The three papers collected here are: 'The Effect of Nose Shape on the Drag of Bodies of Revolution at Zero Angle of Attack.', 'Base Pressure on Wings and Bodies with Turbulent Boundary Layers', and 'Flow over Inclined Bodies'. The subject of the first paper is the drag of the nose section of bodies of revolution at zero angle of attack. The main object of the second paper is to summarize the prinicpal results of the many wind tunnel and free flight measurements of base pressure on both bodies of revolution and blunt trailing edge airfoils.
Date: November 9, 1951

Aerodynamic characteristics of four bodies of revolution showing some effects of afterbody shape and fineness ratio at free-stream Mach numbers from 1.50 to 1.99

Description: The effects of fineness ratio (14.2 and 12.2) and boattailing on aerodynamic characteristics of four bodies of revolution at Mach numbers from 1.50 to 1.99 within a range of angles of attack from 0 degrees 10 degrees at an approximate Reynolds number of 35x10(superscript)6 based on body length were investigated. A comparison of experimental data with available theory is included. At zero angle of attack, fineness ratio has no appreciable effect on model characteristics while boattailing and boattail convergence significantly affect fore drag and base drag. At angle of attack the effects are singular. The theory presented by H. J. Allen is a significant improvement over linearized potential theory in predicting aerodynamic characteristics.
Date: May 22, 1951
Creator: Cohen, Robert J.

Aerodynamic characteristics of four wings of sweepback angles 0 degrees, 35 degrees, 45 degrees, and 60 degrees, NACA 65A006 airfoil section, aspect ratio 4, and taper ratio 0.6 in combination with a fuselage at high subsonic Mach numbers and at a Mach number of 1.2

Description: Report discussing an investigation of the effect of sweepback angle on wing-fuselage characteristics at a subsonic and a supersonic Mach number. Lift, drag, and pitching-moment coefficients, downwash-angle, and total-pressure measurements are all provided.
Date: June 6, 1951
Creator: Luoma, Arvo A.

Aerodynamic characteristics of tapered wings having aspect ratios of 4, 6, and 8, quarter-chord lines swept back 45 degrees, and NACA 63(sub 1)A012 airfoil sections: transonic-bump method

Description: Report presenting testing of a series of three wings over a range of Mach numbers by the use of the transonic-bump technique. The lift, drag, pitching-moment, and root-bending-moment data of wings of a variety of aspect ratios but with the same quarter-chord lines and airfoil sections were obtained.
Date: June 13, 1951
Creator: Polhamus, Edward C. & King, Thomas J., Jr.

Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) : body of revolution with near-parabolic forebody and cylindrical afterbody

Description: An experimental investigation of the aerodynamic characteristics of a slender, square-based body of revolution was conducted at a Mach number of 3.12 for angles of attack from 0 degree to 10 degrees and for Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6). Boundary-layer measurements at zero angle of attack are compared with several compressible flow formulating for predicting boundary-layer characteristics. Comparison of experimental pressure and force values with theoretical values showed good agreement for low angles of attack. The measured mean skin-friction coefficients agreed well with those predicted by Mangler's transformation for laminar flow over cones.
Date: November 13, 1951
Creator: Jack, John R & Burgess, Warren C

Airborne Radioactivity Survey of the Red Desert Region, Sweetwater County, Wyoming

Description: From abstract: An airborne radioactivity survey of a selected area in the Red Desert, Sweetwater County, Wyoming, containing outcrops of radioactive lignites and shales of known surface extent and uranium content, was flown on flight lines at three levels, respectively 250, 500, and 1,000 feet above the ground and spaced at one-quarter mile intervals. Measurements from three identical dual-channel radiation detectors were simultaneously recorded to obtain data at various distances from natural radioactive sources of known configuration. The radiation intensity measurements were fully corrected for all extraneous effects and were compiled as profiles of radiation intensity, as an isoradioactivity contour map, and as curves showing the relationship between radiation intensity and distance from the source.
Date: July 1951
Creator: Nelson, R. A.; Sharp, William N. & Stead, Frank W.

Altitude investigation of 16 flame-holder and fuel-system configurations in tail-pipe burner

Description: From Introduction: "The data obtained for each configuration are presented in a manner to show the effects of fuel distribution and flame-holder design on net thrust, specific fuel consumption, exhaust-gas temperature, combustion efficiency, operable range of tail-pipe-burner fuel-air ratios, and maximum altitude limit."
Date: December 12, 1951
Creator: Grey, Ralph E.; Krull, H. G. & Sargent, A. F.