National Advisory Committee for Aeronautics (NACA) - 39 Matching Results

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Yaw characteristics of a 52 degree sweptback wing of NACA 64(sub 1)-112 section with a fuselage and with leading-edge and split flaps at Reynolds numbers from 1.93 x 10(exp 6) to 6.00 x 10(exp 6)

Description: Report presenting low-speed testing in the pressure tunnel to determine the aerodynamic characteristics in yaw of a 52 degree sweptback wing with aspect ratio 2.88 and taper ratio 0.625 with NACA 64(sub 1)-112 airfoil sections. Testing included an investigation of the effects on the lateral stability of a fuselage and leading-edge and split flaps. Results regarding the lateral stability parameters of a plain wing, effect of flaps on the lateral stability parameters, effect of scale, and airflow characteristics in the region of a vertical tail are provided.
Date: November 8, 1948
Creator: Salmi, Reino J.
Partner: UNT Libraries Government Documents Department

Longitudinal stability and control characteristics of a semispan model of a supersonic airplane configuration at transonic speeds from tests by the NACA wing-flow method

Description: Report presenting an investigation using the NACA wing-flow method to determine the longitudinal stability and control characteristics at transonic speeds of a semispan airplane model with a long slender fuselage, straight wing, and tail of low aspect ratio with faired symmetrical double-wedge airfoil sections. Measurements of the normal force and pitching moments at various angles of attack with five different stabilizer angles of incidence were recorded. The tests were carried out a range of Mach numbers.
Date: November 8, 1948
Creator: Silsby, Norman S. & McKay, James M.
Partner: UNT Libraries Government Documents Department

An investigation of the characteristics of an unswept wing of aspect ratio 4.01 in the Langley 8-foot high-speed tunnel

Description: Report presenting an investigation of the characteristics of a low-aspect-ratio wing at high subsonic Mach numbers in the high-speed tunnel. The wing model had an NACA 65-108 airfoil section, an aspect ratio of 4.01, a taper ratio of 0.498, and no twist or dihedral. Results regarding normal-force characteristics, pitching-moment characteristics, and drag characteristics are provided.
Date: November 8, 1949
Creator: Bielat, Ralph P. & Cahn, Maurice S.
Partner: UNT Libraries Government Documents Department

Flight and test-stand investigation of high-performance fuels in Pratt & Whitney R-1830-94 engines IV : comparison of cooling characteristics of flight and test-stand engines

Description: The cooling characteristics of three R-1830-94 engines, two of which were mounted in a test stand and the other in a B-24D airplane, were investigated and the results were compared. The flight tests were made at a pressure altitude of 7000 feet; the test-stand runs were made at ground-level atmospheric conditions. Three cooling runs were made for each engine: variable cooling-air pressure drop, variable carburetor-air flow, and variable fuel-air ratio. Actual cylinder temperatures of the three engines at nearly the same operating conditions of charge-air flow, fuel-air ratio, and cooling-air pressure drop paralleled predicted temperatures for the same conditions. This result was found to be true for a limited period of engine running time, this period coinciding with the time during which the cooling-correlation data were taken.
Date: October 8, 1946
Creator: Werner, Milton & Dandois, Marcel
Partner: UNT Libraries Government Documents Department

Comparative drag measurements at transonic speeds of 6-percent-thick airfoils of symmetrical double-wedge and circular-arc sections from tests by the NACA wing-flow method

Description: Report presenting comparative drag measurements at zero lift at transonic speeds for two sharp-leading-edge airfoils using the NACA wing-flow method. One airfoil had a symmetrical circular-arc section and one had a symmetrical double-wedge section. The primary difference in the drag characteristics of the two airfoils at zero lift is the earlier drag rise of the double-wedge section.
Date: April 8, 1947
Creator: Silsby, Norman S.
Partner: UNT Libraries Government Documents Department

Drag measurements of a swept-back wing having inverse taper as determined by flight tests at supersonic speeds

Description: Report discussing the results of flight tests to determine the drag at zero lift of a swept-back wing of inverse taper using an NACA 65-009 airfoil. The data was compared to untapered wings with a similar degree of sweepback. The tapered wing was found to have a lower drag coefficient than the 34-degree swept-back untapered wing but a higher drag coefficient than the 45-degree swept-back untapered wing.
Date: April 8, 1947
Creator: Alexander, Sidney R.
Partner: UNT Libraries Government Documents Department

Damping-in-roll characteristics of a 42.7 degree sweptback wing as determined from a wind-tunnel investigation of a twisted semispan wing

Description: Report presenting an investigation to determine the damping-in-roll characteristics of a 42.7 degree sweptback wing using a linearly twisted wing to represent a rolling wing. Results regarding the effect of the airfoil contour, damping-in-roll coefficient, wing-tip helix angle, and theoretical results are provided.
Date: August 8, 1949
Creator: Lockwood, Vernard E.
Partner: UNT Libraries Government Documents Department

Investigation of effects of several fuel-injection locations on operational performance of a 20-inch ram jet

Description: Report presenting the results of an investigation to determine the effects of several methods of fuel injection on the operational performance of a 20-inch ram jet. Four fuel-injection arrangements using the same flame holder were presented. Results regarding the variation of combustion efficiency, ram-pressure ratio, location of the point of fuel injection, and range of fuel-air ratios over which combustion can be maintained are provided.
Date: June 8, 1948
Creator: Sterbentz, W. H.; Perchonok, E. & Wilcox, F. A.
Partner: UNT Libraries Government Documents Department

Comparison of the transonic drag characteristics of two wing-body combinations differing only in the location of the 45 degree sweptback wing

Description: Report presenting the drag of a series of wing-body combinations by the free-fall method in order to provide information on the drag characteristics of promising transonic and supersonic airplane arrangements. Time histories, Mach number variations, and drag coefficients for several areas of the body are provided.
Date: December 8, 1947
Creator: Mathews, Charles W. & Thompson, Jim Rogers
Partner: UNT Libraries Government Documents Department

Investigation at large scale of the pressure distribution and flow phenomena over a wing with the leading edge swept back 47.5 degrees having circular-arc airfoil sections and equipped with drooped-nose and plain flaps

Description: Report presenting an investigation of the pressure distribution over a wing with the leading-edge swept back 47.5 degrees and with symmetrical circular-arc airfoil sections in the full-scale tunnel at a designated Mach and Reynolds number. The investigation included measurements of the surface static pressures along the chord for six spanwise stations, for a large angle-of-attack range, and for several angles of yaw.
Date: September 8, 1949
Creator: Lange, Roy H.; Whittle, Edward F., Jr. & Fink, Marvin P.
Partner: UNT Libraries Government Documents Department

Smooth-Water Landing Stability and Rough-Water Landing and Take-Off Behavior of a 1/13-Scale Model of the Consolidated Vultee Skate 7 Seaplane, TED No. NACA DE 338

Description: A model of the Consolidated Vultee Aircraft Corporation Skate 7 seaplane was tested in Langley tank no. 2. Presented without discussion in this paper are landing stability in smooth water, maximum normal accelerations occurring during rough-water landings, and take-off behavior in waves.
Date: September 8, 1949
Creator: McKann, Robert F.; Coffee, Claude W. & Arabian, Donald D.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8, and 19XB-1 Jet-Propulsion Engines. II - Analysis of Turbine Performance of the 19B-8 Engine

Description: Performance characteristics of the turbine in the 19B-8 jet propulsion engine were determined from an investigation of the complete engine in the Cleveland altitude wind tunnel. The investigation covered a range of simulated altitudes from 5000 to 30,000 feet and flight Mach numbers from 0.05 to 0.46 for various tail-cone positions over the entire operable range of engine speeds. The characteristics of the turbine are presented as functions of the total-pressure ratio across the turbine and the turbine speed and the gas flow corrected to NACA standard atmospheric conditions at sea level. The effect of changes in altitude, flight Mach number, and tail-cone position on turbine performance is discussed. The turbine efficiency with the tail cone in varied from a maximum of 80.5 percent to minimum of 75 percent over a range of engine speeds from 7500 to 17,500 rpm at a flight Mach number of 0.055. Turbine efficiency was unaffected by changes in altitude up to 15,000 feet but was a function of tail-cone position and flight Mach number. Decreasing the tail-pipe-nozzle outlet area 21 percent reduced the turbine efficiency between 2 and 4.5 percent. The turbine efficiency increased between 1.5 and 3 percent as the flight Mach number changed from 0.055 to 0.297.
Date: January 8, 1947
Creator: Krebs, Richard P. & Suozzi, Frank L.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of the Stability of the Jettisonable Nose Section of the X-3 Airplane

Description: Because previous work has indicated that jettisonable nose sections of airplanes may be inherently unstable, and thus may cause dangerous centripetal accelerations on a pilot after jettisoning during high-speed flight, an investigation has been conducted in the Langley 20-foot free-spinning tunnel to determine the behavior in descent of a model of the jettisonable nose section of the Douglas X-3 airplane. The effects of varying the center-of-gravity position, of attaching fins of various sizes, and of installing a stabilizing parachute were investigated. In the investigation the model descended with its front and trimmed 36 deg above the horizontal and rotated about a vertical wind axis while rolling about its longitudinal body axis. The nose section was made to descend in a stable front-down attitude when stabilizing fins were installed in conjunction with movement of the center of gravity forward or when a stable parachute was attached to the model.
Date: December 8, 1946
Creator: Scher, Stanley H.
Partner: UNT Libraries Government Documents Department

Air-Stream Surveys in the Vicinity of the Tail of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

Description: The XF-12 airplane was designed by Republic Aviation Corporation to provide the Army Air Forces with a high performance, photo reconnaissance aircraft. A series of air-stream surveys were made n the vicinity of the empennage of a 1/8.33-scale powered model of the XF-12 airplane in the Langley 19-foot pressure tunnel. Surveys of the vortical-tail region were made through a range of yaw angles of plus or minus 20 degrees at a high and low angle of attack. The horizontal-tail surveys were made over a fairly wide range of angles of attack at zero degrees yaw. Several power and flap conditions were investigated. The results are presented in the form a dynamic pressure ratios, sidewash angles, and downwash angles plotted against vertical distance from the fuselage center line. The results of the investigation indicate that a vertical tail located in a conventional position would be in a field of flow where the dynamic pressure ratios at the horizontal tail to be increased; for equal lift coefficients, the effect of power or flap deflection on the direction of flow at any particular point in the region of the horizontal tail is small.
Date: April 8, 1947
Creator: Foster, Gerald V.
Partner: UNT Libraries Government Documents Department