National Advisory Committee for Aeronautics (NACA) - 5,157 Matching Results

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Characteristics of a Sealed Internally Balanced Aileron from Tests of a 1/4-Scale Partial-Span Model of the Republic XF-12 Airplane in the Langley 19-Foot Pressure Tunnel

Description: This paper presents the results of the aileron investigation and includes rolling-moment, yawing-moment, and aileron hinge-moment coefficients and pressure coefficients across the aileron-balance seal through a range of angle of attack, tab deflection, and aileron deflection with flaps neutral and deflected 20 degrees and 55 degrees. Some of the effects of wing roughness and balance seal leakage on the aileron and tab characteristics are also presented.
Date: November 1, 1946
Creator: Graham, Robert R.; Martina, Albert P. & Salmi, Reino J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Estimation of the Flying Qualities of the Kaiser Fleetwing All-Wing Airplane from Tests of a 1/7-Scale Model, TED No. NACA 2340

Description: "An investigation of a 1/7-scale powered model of the Kaiser Fleetwing all-wing airplane was made in the Langley full-scale tunnel to provide data for an estimation of the flying qualities of the airplane. The analysis of the stability and control characteristics of the airplane has been made as closely as possible in accordance with the requirements of the Bureau of Aeronautics, Navy Department's specifications, and a summary of the more significant conclusions is presented as follows. With th… more
Date: November 1, 1946
Creator: Brewer, Gerald W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms. 4 - July 19, 1946 to July 20, 1946 at Orlando, Florida

Description: "Summaries of the gust and draft velocities evaluated from acceleration and airspeed-altitude records taken by NACA instruments installed n P-61c airplanes participating in thunderstorm flights 12 and 13 of July 19, 1946, and July 20, 1946, respectively, are presented in tables I and II herein. These data are of the type presented in reference 1 for previous flights. Inspection of the motion picture records of the pilots' instrument panels for the present flights indicated that the milliameter … more
Date: November 1946
Creator: Tolefson, H. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of an Auxiliary Belly Fuel Tank on the Low-Speed Static Stability Characteristics of a 1/5-Scale Model of the Grumman XF8F-1 Airplane, TED No. NACA 2384

Description: "In order to determine the aerodynamic effects of an auxiliary belly fuel tank on the Grumman F8F-1 airplane, a wind-tunnel investigation was made on a 1/5 - scale model of the Grumman XF8F-1 airplane. Pitch and yaw tests were made with the model in the cruising and landing configurations for windmilling and take-off power conditions. Tuft studies and static-pressure measurements were also made to determine the flow characteristics in the region of the fuel tank" (p. 1).
Date: November 5, 1946
Creator: Cook, Charles B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Evaluation of Gust and Draft Velocities from Flights of P-61c Airplanes within Thunderstorms. 3 - July 12, 1946 to July 18, 1946 at Orlando, Florida

Description: The gust and draft velocities evaluated from acceleration and airspeed-altitude records taken by NACA instruments installed in P-61c airplanes participating in thunderstorm flights 9, 10, and 11 of July 12, 1946, July 17, 1946, and July 18, 1946, respectively, are presented in references 1 and 2 for previous flights. In accordance with a recent discussion with a member of the U.S. Weather Bureau staff, motion-picture records of the pilots' instrument panels for the present flights were inspecte… more
Date: November 5, 1946
Creator: Tolefson, H. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tank Tests of an Alternate Hull Form for the Consolidated Vultee PB2Y-3 Airplane

Description: From Summary: "Tests have been made in Langley tank no. I of a dynamic model of the Consolidated Vultee PB2Y-3 airplane. These tests were made using an alternate hull form, the purpose of which was to reduce the bow spray and eliminate the landing instability which are objectionable features of the production design. The major differences from the PB2Y-3 hull included a deeper step to improve the landing stability , and a lengthened forebody and increased beam to reduce the sway in the propelle… more
Date: November 6, 1946
Creator: Land, Norman S. & Posner, Jack
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Fuel Composition, Engine Operating Variables, and Spark-Plug Type and Condition on Preignition-Limited Performance of an R-2800 Cylinder

Description: The preignition characteristics of the R-2800 cylinder, as effected by fuel consumption, engine operating variables, and spark plug type and condition, were evaluated. The effects on preignition-limited performance of various percentages of aromatics (benzene, toluene, cumene, xylene) in a base fuel of triptane were investigated. Two paraffins (triptane and S + 6.0 ml TEL/gal) and two refinery blends (28-R and 33-R) were preignition rated. The effect of changes in the following engine operating… more
Date: November 15, 1946
Creator: Pfender, John F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Wing Flaps and Wing Duct Inlet on the Lift and Stalling Characteristics of a 1/4-Scale Partial-Span Model of the Republic XF-12 Airplane in the Langley 19-Foot Pressure Tunnel

Description: From Summary: "An investigation was conducted in the Langley 19-foot pressure tunnel to determine the lift, drag, pitching-moment and stalling characteristics of a 1/4 -scale partial-span model of the left wing of the Republic XF-12 airplane. The effects of a duct inlet, located between the nacelles at the leading edge of the wing, on those characteristics were also investigated. The Reynolds numbers for the investigation covered a range from 4,500,000 to 8,600,000. The results of the investiga… more
Date: November 18, 1946
Creator: Graham, Robert R.; Martina, Albert P. & Salmi, Reino J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Speed Longitudinal-Stability and Control Characteristics of the Consolidated Vultee Lark Missile as Predicted from Wind-Tunnel Tests (TED No. NACA 2391)

Description: "A high-speed wind-tunnel investigation of the aerodynamic characteristics of a full-scale model of the Consolidated Vultee Lark indicates that the missile possesses satisfactory longitudinal-stability and-control characteristics throughout the Mach number range from 0.2 to 0.85, but that the maximum lift coefficients developed are not high enough to insure interception of the target at high altitudes. A reduction in wing loading appears advisable. Although the static longitudinal stability at … more
Date: November 19, 1946
Creator: Axelson, John A. & Martin, Andrew
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loading 2 - Curtiss 838-1C2-18R1 Four-Blade Propeller

Description: "An investigation was conducted in the Cleveland altitude wind tunnel to determine the performance of a Curtiss propeller with four 838-1C2-1SR1 blades on a YP-47M airplane at high blade loadings and engine powers. The study was made for a range of power coefficients between 0.30 and 1.00 at free-stream Mach numbers of 0.40 and 0.50. The results of the force measurements indicate primarily the trend of propeller efficiency for changes in power coefficient or advance-diameter ratio, inasmuch as … more
Date: November 26, 1946
Creator: Wallner, Lewis E. & Sorin, Solomon M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loadings 4 - Curtiss 732-1C2-0 Four-Blade Propeller

Description: "An altitude-wind-tunnel investigation has been made to determine the performance of a Curtiss 732-1C2-0 four-blade propeller on a YP-47M airplane at high blade loadings and engine power. Propeller characteristics were obtained for a range of power coefficients from 0.30 to 1.00 at free-stream Mach numbers of 0.40 and .50" (p. 1).
Date: November 26, 1946
Creator: Saari, Martin J. & Sorin, Solomon M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation of a New Type of Supersonic Inlet

Description: "A supersonic inlet with supersonic deceleration of the flow entirely outside of the inlet is considered. A particular arrangement with fixed geometry having a central body with a circular annular intake is analyzed, and it is shown theoretically that this arrangement gives high pressure recovery for a large range of Mach number and mass flow and therefore is practical for use on supersonic airplanes and missiles. For some Mach numbers the drag coefficient for this type of inlet is larger than … more
Date: November 27, 1946
Creator: Ferri, Antonio & Nucci, Louis M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loadings 5 - Curtiss 836-14C2-18R1 Four-Blade Propeller

Description: An investigation of the performance of several propellers on the YP-47M airplane at high blade loadings has been conducted in the Cleveland altitude wind tunnel at the request of the Air Materiel Command, Army Air Forces. As part of the program, a study was made of a Curtiss 836-14C2-18R1 four-blade propeller. The investigation was made for a range of power coefficients from 0.10 to 1.00 at free-stream Mach numbers of 0.30, 0.40, and 0.50 for density altitudes from 10,000 to 45,000 feet, engine… more
Date: December 2, 1946
Creator: Saari, Martin J. & Wallner, Lewis E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of the Pressure-Loss Characteristics of the Westinghouse X24-C-2 Inlet Screen, TED No. NACA 0447

Description: At the request of the Bureau of Aeronautics, Navy Department, investigations of the static-pressure losses and total-head distributions of the Westinghouse X24-C-2 inlet screen were made in the induction aerodynamics laboratory at Langley. The screen was investigated in two configurations, both before and after rounding the leading edges of the vanes. Investigations were conducted through air flows up to about pounds per second.
Date: December 2, 1946
Creator: Lankford, John L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Ditching Tests of a 1/9-Size Model of the Army P-38 Airplane in Langley Tank No. 2 and at the Outdoor Catapult

Description: "A dynamically similar model of the Army P-38 airplane was tested to determine the best way to land this airplane on the water and to determine its probable ditching performance. The tests consisted of ditching the model at various landing attitudes, flap settings, speeds, weights, and conditions of simulated damage. The model was ditched in calm water from the tank towing carriage and a few ditching were made in both calm and rough water at the outdoor catapult" (p. 1).
Date: December 3, 1946
Creator: Jarvis, George A. & Cederborg, Gibson A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Measurements of the Directional Stability and Control of a P-51D Airplane with a Horn-Balanced Rudder as Compared with Previously Tested Vertical-Tail Configurations

Description: "At the request of the Air Materiel Command, Army Air Forces, flight tests were conducted on a P-5lD-20-NA (AAF No. 44-63826) airplane equipped with a horn-balanced rudder. This rudder was fitted with an unbalancing tab as was the original product fan rudder. Tests were made both with the unbalancing tab in operation and with the unbalancing tab locked. The modification to the original vertical tail consisted of removing the cap from the top of the fin and adding 1.91 square feet of area to the… more
Date: December 3, 1946
Creator: Mungall, Robert G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tank Tests of a 1/7-Size Powered Dynamic Model of the Grumman XJR2F-1 Amphibian: Spray Characteristics, Take-Off and Landing Stability in Smooth Water - Langley Tank Model 212, TED No. NACA 2378

Description: From Summary: "Tests of a model of the XJR2F-Y amphibian were made in Langley tank no. to determine the spray characteristics and the take-off and landing stability. At a gross load of 22,000 pounds full size, spray entered the propeller disk only at a very narrow range of speeds. The spray striking the flaps was not excessive and no appreciable wetting of the tail surfaces was noted. The trim limits of stability appeared to be satisfactory and the upper-limit porpoising was not violent."
Date: December 4, 1946
Creator: Land, Norman S. & Zeck, Howard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Spinning-Tunnel Tests of a 1/26th Scale Model of the Douglas XTB2D-1 Airplane

Description: "A spin-tunnel investigation of a 1/26 scale model of the Douglas XTB2D-1 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements upon the erect- and inverted-spin and recovery characteristics of the model were determined for various loading conditions. Tests were also performed to determine the effects of various tail modifications. The investigation included emergency spin-recovery parachute tests as well as crew-escape and rudder… more
Date: December 5, 1946
Creator: Stone, Ralph W., Jr. & Berman, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Three Modifications on Performance of Auxiliary-Stage Supercharger for V-1710-93 Engine

Description: "Three modifications of the auxiliary-stage supercharger for the V-1710-93 engine were designed and tested as part of an investigation to improve the power output and the altitude performance of the engine. A 12-vane diffuser was substituted for the standard 11-vane diffuser, and a vaneless discharge passage and a modified scroll were designed to increase the flow capacity of the supercharger and thereby to increase the performance at the high volume flows required by the engine. With the 12-va… more
Date: December 6, 1946
Creator: Downing, Richard M. & Finger, Harold B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical and Experimental Data for a Number of NACA 6A-Series Airfoil Sections

Description: The NACA 6A-series airfoil sections were designed to eliminate the trailing-edge cusp which is characteristic of the NACA 6-series sections. Theoretical data are presented for NACA 6A-series basic thickness forms having the position of minimum pressure at 30-, 40-, and 50-percent chord and with thickness ratios varying from 6 percent to 15 percent. Also presented are data for a mean line designed to maintain straight sides on the cambered sections. The experimental results of a two dimensional … more
Date: December 6, 1946
Creator: Loftin, Laurence K., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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… more
Date: December 8, 1946
Creator: Scher, Stanley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Evaluation of Gust and Draft Velocities from Flights of P-61c Airplanes within Thunderstorms August 7, 1946 to August 13, 1946 at Orlando, Florida

Description: This report presents the results obtained from gust and draft velocity measurements within thunderstorms for the period August 7, 1946 to August, 13, 1946 at Orlando Florida. In several of the surveys, indications of ambient air temperature were obtained from photo-observer records. These data are summarized in the report.
Date: December 9, 1946
Creator: Tolefson, Harold B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Knock-Limited Performance of Triptane and Xylidines Blended with 28-R Aviation Fuel at High Compression Ratios and Maximum-Economy Spark Setting

Description: From Summary :"An investigation was conducted to evaluate the possibilities of utilizing the high-performance characteristics of triptane and xylidines blended with 28-R fuel in order to increase fuel economy by the use of high compression ratios and maximum-economy spark setting. Full-scale single-cylinder knock tests were run with 20 deg B.T.C. and maximum-economy spark settings at compression ratios of 6.9, 8.0, and 10.0, and with two inlet-air temperatures. The fuels tested consisted of tri… more
Date: December 12, 1946
Creator: Held, Louis F. & Pritchard, Ernest I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loadings 6 - Hamilton Standard 6507A-2 Four- and Three-Blade Propellers

Description: "An altitude-wind-tunnel investigation has been made to determine the performance of Hamilton Standard 6507A-2 four-blade and three-blade propellers on a YP-47M airplane at high blade loadings and high engine powers. Characteristics of the four-blase propeller were obtained for a range of power coefficients from 0.10 to 1.00 at free-stream Mach numbers of 0.20, 0.30, 0.40. Characteristics of the three-blade propeller were obtained for a range of power coefficients from 0.30 to 1.00 at a free-st… more
Date: December 19, 1946
Creator: Saari, Martin J. & Sorin, Solomon M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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