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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1951
 Collection: Technical Report Archive and Image Library
Acid-Mine-Drainage Problems: Anthracite Region of Pennsylvania

Acid-Mine-Drainage Problems: Anthracite Region of Pennsylvania

Date: 1951
Creator: Ash, S. H. (Simon Harry), b. 1889
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).
Contributing Partner: UNT Libraries Government Documents Department
Adaptation of a Cascade Impactor to Flight Measurement of Droplet Size in Clouds

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

Date: September 18, 1951
Creator: Levine, Joseph
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.
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: November 6, 1951
Creator: Bates, William R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic behavior of a harmonically oscillating finite sweptback wing in supersonic flow

The aerodynamic behavior of a harmonically oscillating finite sweptback wing in supersonic flow

Date: October 1, 1951
Creator: Chang, Chieh-Chien
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: February 6, 1951
Creator: Wiley, Harleth G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

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

Date: February 6, 1951
Creator: Sutton, Fred B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a Flying-Boat Hull Having a Length-Beam Ratio of 15, TED No. NACA 2206

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

Date: January 23, 1951
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 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 ...
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a slender cone-cylinder body of revolution at a Mach number of 3.85

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

Date: November 5, 1951
Creator: Jack, John R
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.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of Bodies at Supersonic Speeds: A Collection of Three Papers

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

Date: November 9, 1951
Creator: unknown
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.
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: May 22, 1951
Creator: Cohen, Robert J
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.
Contributing Partner: UNT Libraries Government Documents Department
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