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  • Other Sources  (25)
  • Meteorology and Climatology  (13)
  • Aeronautics (General)  (12)
  • 1945-1949  (25)
  • 1
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    Index of NACA Technical Publications: 1915-1949 (1949)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: The Index of NACA Technical Publications covers reports issued from the date of origin of the Committee in 1915 until approximately September 1949. Because omissions were noted after publication of the Index issued in 1947, and since many new reports have been released since that time, it was decided to issue a new volume to supersede completely the 1947 Index, with supplements to be issued regularly in the future. Commencing with all publications issued after September 1, 1949, subject classifications were revised, the most important change involving the transfer of aircraft loads reports from the Aerodynamics classification to Structures. For those maintaining a file of NACA index cards, it is recommended that cards issued for reports dated prior to September 1, 1949 be removed from the file. This volume includes the same index information. Supplements covering periods following September 1, 1949, will be arranged according to the revised subject classifications. On the pages immediately following, the subject classifications are indexed in order of breakdown. There is included in the back of this volume an alphabetical arrangement of the subject classifications.
    Keywords: Aeronautics (General)
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  • 2
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    Cooling of Gas Turbines II : Effectiveness of Rim Cooling of Blades (1947)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aeronautics (General)
    Type: NACA-RM-E7B11b , NACA-MR-E5I20
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  • 3
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    Recommended Values of Meteorological Factors to Be Considered in the Design of Aircraft Ice-Prevention Equipment (1949)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Meteorological conditions conducive to aircraft icing are arranged in four classifications: three are associated with cloud structure and the fourth with freezing rain. The range of possible meteorological factors for each classification is discussed and specific values recommended for consideration in the design of ice-prevention equipment for aircraft are selected and tabulated. The values selected are based upon a study of the available observational data and theoretical considerations where observations are lacking. Recommendations for future research in the field are presented.
    Keywords: Meteorology and Climatology
    Type: NACA-TN-1855
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  • 4
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    Investigation of Meteorological Conditions Associated with Aircraft Icing in Layer-Type Clouds for 1947-48 Winter (1949)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Rotating-cylinder measurements of the icing conditions encountered in flight during the winter of 1947-48 are presented. Liquid water content, drop size, and temperature data are shown to be consistent with previously measured conditions and with proposed maximum icing conditions in supercooled layer-type clouds. Cumulative frequency graphs of meteorological parameters indicate the frequency with which various icing conditions have been encountered in the Great Lakes area and surrounding states.
    Keywords: Meteorology and Climatology
    Type: NACA-TN-1793
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  • 5
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    Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes Within Thunderstorms August 14, 1946 to August 15, 1946 at Orlando, Florida (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Tables I and II of the present paper summarize the gust and draft velocity data for thunderstorm-flights 21 and 22 of August 14, 1946 and August 15, 1946, respectively. These data were evaluated from records of NACA airspeed-altitude and acceleration recorders installed in P-61C airplanes and are of the type presented for previous flights. Table III summarizes the readings of a milliammeter which was used in conjunction with other equipment to indicate ambient-air temperature during thunderstorm surveys. These data were read from photo-observer records and include all cases in which variations of the instrument indications were noted for the present flights.
    Keywords: Meteorology and Climatology
    Type: NACA-RM-L7C31
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  • 6
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    Investigation of the Pressure-Loss Characteristics of the Westinghouse X24-C-2 Inlet Screen, TED No. NACA 0447 (1946)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    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. The results of the investigations indicate that maximum lift coefficients of 1.36, 1.71 and 2.11 were measured on the model with flaps neutral and deflected 20 deg. and 55 deg, respectively, at a reynolds number of 8,600,000. When the duct inlet was replaced by a basic airfoil nose the flap neutral maximum lift coefficient was increased from 1.36 to 1.41. The results also showed that at maximum lift with flaps neutral or deflected 55 deg most of the area between the nacelles was stalled while only small areas on other portions of the model were stalled; when the duct inlet was replaced by the basic airfoil nose the stall was delayed to a slightly higher angle of attack but the nature of the stall was relatively unaffected.
    Keywords: Aeronautics (General)
    Type: NACA-RM-L6J29
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  • 7
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    Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms: August 23, 1946 to September 4, 1946 at Orlando, Florida (1946)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This report presents the results obtained from gust and draft velocity measurements within thunderstorms for the period August 23, 1946 to September 4, 1946 at Orlando, Florida. These data are summarized in tables I end II and are of the type presented in reference 1 for previous flights. In several of the surveys, indications of ambient air temperature were obtained from photo-observer records. These data are summarized in table III.
    Keywords: Meteorology and Climatology
    Type: NACA-RM-L7A14
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  • 8
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    Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms June 2, 1947 to June 7, 1947 at Clinton County Army Air Field, Ohio (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from June 2, 1947 to June 7, 1947, are presented.
    Keywords: Meteorology and Climatology
    Type: NACA-RM-L7J31
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  • 9
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    Six-component measurements on a straight and a 35 degree swept-back trapezoidal wing with and without split flaps (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: In accord with me test program (published in reference 7) the wing in question is briefly designated as No. 5. It differs from the rectangular wing discussed in reference 7 by its taper and from the 35O swept-back trapezoidal wing treated in reference 8 by the absence of sweepbaok .
    Keywords: Aeronautics (General)
    Type: NACA-TM-1107
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  • 10
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    Scale effect and optimum relations for sea surface planning (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: From the general dimensional and mechanical similarity theory it follows that a condition of steady motion of a given shape\bottom with constant speed on the surface of water is determined by four nondimensional parameters. By considering the various systems of independent parameters which are applied in theory and practice and special tests, there is determined their mutual relations and their suitability as planning characteristics. In studying the scale effect on the basis of the Prnndtl formula for the friction coefficient for a turbulent condition the order of magnitude is given of the error in applying the model data to full scale in the case of a single-step bottom For a bottom of complicated shape it is shown how from the test data of the hydrodynamic characteristics for one speed with various loads, or one load with various speeds, there may be obtained by simple computation with good approximation the hydrodynamic characteristics for a different speed or for a different load. (These considerations may be of use in solving certain problems on the stability of planning.) This permits extrapolating the curve of resistance against speed for large speeds inaccessible in the tank tests or for other loads which were not tested. The data obtained by computation are in good agreement with the test results. Problems regarding the optimum trim angle or the optimum width in the case of planning of a flat plate are considered from the point of view of the minimum resistance for a given load on the water and planning speeds. Formulas and graphs are given for the optimum value of the planning coefficient and the corresponding values of the trim angle and width of the flat plate.
    Keywords: Aeronautics (General)
    Type: NACA-TM-1097 , Central Aero-Hydrodynamical Institute; Report-439
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  • 11
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    Investigation of the NACA 4-(5)(08)-03 Two-blade Propeller at Forward Mach Numbers to 0.925 (1949)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: No abstract available
    Keywords: Aeronautics (General)
    Type: NACA-RM-L9G06a
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  • 12
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    Investigations of Pressure Distribution on Fast Flying Bodies (1946)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: The question to be treated is: how high is the pressure in the bow wave caused by a body flying at supersonic speed, and how far reaching are the destructive effects of that wave? The pressure distribution on an s.S. and an S. projectile of normal speed has been ascertained already by the methods of measurement used at the Ballistic Institute of the Technical Academy of the German Air Forces. Now similar investigations of the conditions on especially fast-flying bodies were carried out.
    Keywords: Aeronautics (General)
    Type: NACA-TM-1101 , Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluftzeugmeisters (ZWB); No. 8103
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  • 13
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    Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Nozzles and Three Rotor-Blade Designs (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A single-stage modification of the turbine from a Mark 25 torpedo power plant was investigated to determine the performance with two nozzles and three rotor-blade designs. The performance was evaluated in terms of brake, rotor, and blade efficiencies at pressure ratios of 8, 15 (design), and 20. The blade efficiencies with the two nozzles are compared with those obtained with four other nozzles previously investigated with the same three rotor-blade designs. Blade efficiency with the cast nozzle of rectangular cross section (J) was higher than that with the circular reamed nozzle (K) at all speeds and pressure ratios with a rotor having a 0.45-inch 17 degree-inlet-angle blades. The efficiencies for both these nozzles were generally low compared with those of the four other nozzles previously investigated in combination with this rotor. At pressure ratios of 15 and 20, the blade efficiencies with nozzle K and the two rotors with 0.40-inch blades having different inlet angles were higher than with the four other nozzles, but the efficiency with nozzle J was generally low. Increasing the blade inlet angle from 17 degrees to 20 degrees had little effect on turbine performance, whereas changing the blade length from 0.40 to 0.45 inch had a marked effect. Although a slight correlation of efficiency with nozzle size was noted for the rotor with 0.45-inch 17 degree-inlet-angle blades, no such effect was discernible ,for the two rotors with 0.40-inch blades.Losses in the supersonic air stream resulting from the complex flow path in the small air passages are probably a large percentage of the total losses, and apparently the effects of changing nozzle size and shape within the limits investigated are of secondary importance.
    Keywords: Aeronautics (General)
    Type: NACA-RM-SE9J25
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  • 14
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    Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A Mark 25 torpedo power plant modified to operate as a single-stage turbine was investigated to determine the performance with two nozzle designs and a standard first-stage rotor having 0.40-inch blades with a 17O met-air angle. Both nozzles had smaller port cross-sectional areas than those nozzles of similar design, which were previously investigated. The performance of the two nozzles was compared on the basis of blade, rotor, and brake efficiencies as a function of blade-jet speed ratio for pressure ratios of 8, 15 (design), and 20. At pressure ratios of 15 and 20, the blade efficiency obtained with the nozzle having circular passages (K) was higher than that obtained with the nozzle having rectangular passages (J). At a pressure ratio of 8, the efficiencies obtained with the two nozzles were comparable for blade-jet speed ratios of less than 0.260. For blade-jet speed ratios exceeding this value, nozzle K yielded slightly higher efficiencies. The maximum blade efficiency of 0.569 was obtained with nozzle K at a pressure ratio of 8 and a blade-jet speed ratio of 0.295. At design speed and pressure ratio, nozzle K yielded a maximum blade efficiency of 0.534, an increase of 0.031 over that obtained with nozzle J. When the blade efficiencies of the two nozzles were compared with those of four other nozzles previously investigated, the maximum difference for the six nozzles with this rotor was 0.050. From, this comparison, no specific effect of nozzles size or shape on over-all performance was discernible.
    Keywords: Aeronautics (General)
    Type: NACA-RM-SE9H30
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  • 15
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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 (1946)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was conducted in the Langley 19-foot pressure tunnel to determine the lift, drag, pitching-moment and stalling characteristics fo 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 investigation indicated that maximum lift coefficients of 1.36, 1.71, and 2.11 were measured on the model with flaps neutral and deflected 20 deg and 55 deg, respectively at a Reynolds number of 8,600,000. When the duct inlet was replaced by a basic airfoil nose the flap-neutral maximum-lift coefficient was increased from 1.36 to 1.41. The results also showed that at maximum lift with flaps neutral or deflected 55 deg. most of the area between the nacelles were stalled while only small areas on other portions of the model were stalled; when the duct inlet was replaced by the basic airfoil nose the stall was delayed to a slightly higher angle of attack but the nature of the stall was relatively unaffected.
    Keywords: Aeronautics (General)
    Type: NACA-RM-L6J22
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  • 16
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    Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms August 13, 1947 to August 15, 1947 at Clinton County Army Air Field, Ohio (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from August 13, 1947 to August 15, 1947 are presented.
    Keywords: Meteorology and Climatology
    Type: NACA-RM-L8A27
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  • 17
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    Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms August 16, 1947 to August 20, 1947 at Clinton County Army Air Field, Ohio (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from August 16, 1947 to August 20, 1947 are presented.
    Keywords: Meteorology and Climatology
    Type: NACA-RM-L8B04
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  • 18
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    Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms: September 5, 1946 to September 10, 1946 at Orlando, Florida (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Tables I and II of this report summarize the gust and draft velocity data for thunderstorm flights 31, 32, and 33 of September 5, 1946, September 6, 1946, and September 10, 1946, respectively. These data were evaluated from records of NACA instruments installed in P-61C airplanes and are of the type presented for previous flights. Table III summarizes the readings of a milliammeter which was used in conjunction with other equipment to indicate ambient air temperature during thunderstorm surveys. These data were read from motion-picture records of the instrument and include all cases in which variations in the instrument indications were noted for the present flights.
    Keywords: Meteorology and Climatology
    Type: NACA-RM-L7C07
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  • 19
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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 (1946)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    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.
    Keywords: Meteorology and Climatology
    Type: NACA-RM-L6K16
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  • 20
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    Evaluation of Gust and Draft Velocities from Flights of F-61C Airplanes within Thunderstorms August 7, 1947 to August 13, 1947 at Clinton County Army Air Field, Ohio (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air FIeld, Ohio, from August 7, 1947 to August 13, 1947 are presented.
    Keywords: Meteorology and Climatology
    Type: NACA-RM-L8A30
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  • 21
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    Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms May 13, 1947 to May 29, 1947 at Clinton County Army Air Field, Ohio (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The gust and draft velocities evaluated from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from May 13 to May 29, 1947 are presented.
    Keywords: Meteorology and Climatology
    Type: NACA-RM-L7J29
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  • 22
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    Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms June 11, 1947 to July 11, 1947 at Clinton County Army Air Field, Ohio (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from June 11, 1947 to July 11, 1947 are presented.
    Keywords: Meteorology and Climatology
    Type: NACA-RM-L7K25
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  • 23
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    Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms September 4, 1947 to September 5, 1947 at Clinton County Army Air Field, Ohio (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from September 4, 1947 to September 5, 1947 are presented.
    Keywords: Meteorology and Climatology
    Type: NACA-RM-L8C19
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  • 24
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    Investigation of an Experimental Supersonic Axial-Flow Compressor (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: An investigation is in progress at the Langley Laboratory of the NACA to explore the possibilities of axial-flow compressors operating with supersonic velocities relative to the blade rows. The first phase of this investigation, a study of supersonic diffusers, has been reported. The second phase, an analysis of supersonic compressors, has also been reported. Preliminary calculations have shown that very high pressure ratios across a stage, together with somewhat increased mass flows, are possible with compressors which decelerate air through the speed of sound in their rotor blading. These performance characteristics are desirable in compressors for aircraft jet propulsion units, gas turbines, or superchargers. The third phase, presented here, is a preliminary experimental investigation of a supersonic compressor designed to produce a high pressure ratio in a single stage.
    Keywords: Aeronautics (General)
    Type: NACA-RM-L6J01b
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  • 25
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    Comparison of Water-Load Distributions Obtained during Seaplane Landings with Bureau of Aeronautics Specifications. TED No. NACA 2413 (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Bureau of Aeronautics Design Specifications SS-IC-2 for water loads in sheltered water are compared with experimental water loads obtained during a full--scale landing investigation. This investigation was conducted with a JRS-1 flying boat which has a 20 degrees dead-rise V-bottom with a partial chine flare. The range of landing conditions included airspeeds between 88 and 126 feet per second, sinking speeds between 1.6 and 9.1 feet per second, flight angles less than 6 degrees, and trims between 2 degrees and 12 degrees. Landings were moderate and were made in calm water. Measurements were obtained of maximum over-all loads, maximum pitching moments, and pressure distributions. Maximum experimental loads include over-all load factors of 2g, moments of 128,000 pound-feet, and maximum local pressures greater than 40 pounds per square inch. Experimental over-all loads are approximately one-half the design values, while local pressures are of the same order as or larger than pressures calculated from specifications for plating, stringer, floor, and frame design. The value of this comparison is limited, to some extent, by the moderate conditions of the test and by the necessary simplifying assumptions used in comparing the specifications with the experimental loads.
    Keywords: Aeronautics (General)
    Type: NACA-RM-SL9G01
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