You limited your search to:

 Decade: 1950-1959
 Year: 1951
 Collection: National Advisory Committee for Aeronautics Collection
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 & Kleinknecht, Kenneth S.
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.; Lovell, Powell M., Jr. & Smith, Charles C., Jr.
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 & Martin, Andrew
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. & Naeseth, Rodger L.
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
Aerodynamic characteristics of four wings of sweepback angles 0 degree, 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 Mach num

Aerodynamic characteristics of four wings of sweepback angles 0 degree, 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 Mach num

Date: June 6, 1951
Creator: Luoma, Arvo A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: June 13, 1951
Creator: Polhamus, Edward C & King, Thomas J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of the NACA RM-10 research missile in the Ames 1- by 3-foot supersonic wind tunnel no. 2 : pressure and force measurements at Mach numbers of 1.52 and 1.98

Aerodynamic characteristics of the NACA RM-10 research missile in the Ames 1- by 3-foot supersonic wind tunnel no. 2 : pressure and force measurements at Mach numbers of 1.52 and 1.98

Date: September 19, 1951
Creator: Perkins, Edward W; Gowen, Forrest E & Jorgensen, Leland H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of wings designed for structural improvement

Aerodynamic characteristics of wings designed for structural improvement

Date: May 28, 1951
Creator: Weil, Joseph & Polhamus, Edward C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness at supersonic speeds of a 30-percent chord, 50-percent semispan elevon as a lateral control device

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness at supersonic speeds of a 30-percent chord, 50-percent semispan elevon as a lateral control device

Date: January 18, 1951
Creator: Olson, Robert N & Mead, Merrill H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: November 13, 1951
Creator: Jack, John R & Burgess, Warren C
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.
Contributing Partner: UNT Libraries Government Documents Department
Air forces and moments on triangular and related wings with subsonic leading edges oscillating in supersonic potential flow

Air forces and moments on triangular and related wings with subsonic leading edges oscillating in supersonic potential flow

Date: September 1, 1951
Creator: Watkins, Charles E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude-ignition limit of a turbojet engine using a condenser-discharge ignition system / John C. Armstrong

Altitude-ignition limit of a turbojet engine using a condenser-discharge ignition system / John C. Armstrong

Date: October 23, 1951
Creator: Armstrong, John C
Description: The altitude-ignition limits of a condenser-discharge ignition system installed on a turbojet engine were determined at a flight Mach number of 0.6 using 1.1-pound Reid vapor pressure fuel. Ignition was possible up to an altitude of 55,000 feet with 4.8 joules per spark and 6 sparks per second.
Contributing Partner: UNT Libraries Government Documents Department
Altitude investigation of 16 flame-holder and fuel-system configurations in tail-pipe burner

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

Date: December 12, 1951
Creator: Grey, Ralph E; Krull, H G & SARGENT A F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude operation of gas-turbine engine with variable-area fuel-nozzle system

Altitude operation of gas-turbine engine with variable-area fuel-nozzle system

Date: April 2, 1951
Creator: Gold, H & Rosenzweig, S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude-performance and Reynolds number investigation of centrifugal-flow-compressor turbojet engine

Altitude-performance and Reynolds number investigation of centrifugal-flow-compressor turbojet engine

Date: May 15, 1951
Creator: Wilsted, H D & Grey, R E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude Performance of J35-A-17 Turbojet Engine in an Altitude Chamber

Altitude Performance of J35-A-17 Turbojet Engine in an Altitude Chamber

Date: January 3, 1951
Creator: Vincent, K. R. & Gale, B. M.
Description: An investigation of the altitude performance characteristics of an Allison J35-A-17 turbojet engines have been conducted in an altitude chamber at the NACA Lewis laboratory. Engine performance was obtained over a range of altitudes from 20,000 to 60,000 feet at a flight Mach number of 0.62 and a range of flight Mach numbers from 0.42 to 1.22 at an altitude of 30,000 feet. The performance of the engine over the range investigated could be generalized up to an altitude of 30,000 feet. Performance of the engine at any flight Mach number in the range investigated can be predicted for those operating condition a t which critical flow exits in the exhaust nozzle with the exception of the variables corrected net thrust, and net-thrust specific fuel consumption.
Contributing Partner: UNT Libraries Government Documents Department
Altitude-test-chamber investigation of performance of a 28-inch ram-jet engine III : combustion and operational performance of three flame holders with a center pilot burner

Altitude-test-chamber investigation of performance of a 28-inch ram-jet engine III : combustion and operational performance of three flame holders with a center pilot burner

Date: February 6, 1951
Creator: Shillito, Thomas B; Younger, George G & Henzel, James G , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude-test-chamber investigation of performance of a 28-inch ram-jet engine IV : effect of inlet-air temperature, combustion-chamber-inlet Mach number, and fuel volatility on combustion performance

Altitude-test-chamber investigation of performance of a 28-inch ram-jet engine IV : effect of inlet-air temperature, combustion-chamber-inlet Mach number, and fuel volatility on combustion performance

Date: July 27, 1951
Creator: Kahn, Robert W; Nakanishi, Shigeo & Harp, James L , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude-wind-tunnel investigation of performance characteristics of a J47d prototype (RX1-1) turbojet engine with fixed-area exhaust nozzle

Altitude-wind-tunnel investigation of performance characteristics of a J47d prototype (RX1-1) turbojet engine with fixed-area exhaust nozzle

Date: September 4, 1951
Creator: Saari, M J & Wintler, J T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
FIRST PREV 1 2 3 4 5 NEXT LAST