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  • Aerodynamics  (25)
  • Aircraft Design, Testing and Performance  (23)
  • 2020-2024
  • 1945-1949  (48)
  • 1948  (48)
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  • 2020-2024
  • 1945-1949  (48)
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  • 11
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    Investigation of the Aerodynamic and Icing Characteristics of a Recessed Fuel Cell Vent Assembly. I: Rear Wall Vent Tube Mounting (1948)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-14
    Beschreibung: No abstract available
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-E8A27b
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 12
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    Maintaining Laminar Flow in the Boundary Layer using a Swept-Back Wing (1948)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The positions of boundary-layer transition were ascertained experimentally for a swept-back wing and a wing without sweepback which were alike in all other respects and were compared for the same angle of attack (R(sub e) = 5.6 x 10(exp 5)). The swept-back wing in a definite range of angle of attack resulted in a backward shift of the transition point on the suction side of the wing. The favorable effect of sweepback on the position of the transition point is confirmed, consequently. In addition to decreasing the drag at high Mach numbers, the swept-back wing is acknowledged to have additional advantages. These are: (1) Decrease of the pressure drag. The reduction factor is approximately equal to the cosine of the angle of sweepback. (2) Backward shift of the transition point. There are no known experiments which establish experimentally the advantage anticipated. It appeared justifiable, therefore, to carry out some fundamental experiments which might furnish some idea of the magnitude of the advantage expected. Such an experiment is reported in what follows; the advantage of the sweepback appears clearly.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1180 , Untersuchungen und Mitteilungen; 3151
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 13
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    Test Report on Three- and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio (1948)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The investigations of the reports to 4 on wings of small aspect ratio are continued. The present report deals with the results of the three- and six-component measurements and the flow pictures of the triangular wing series with the aspect ratio Lambda = 3 to Lambda = 1.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Materialart: NACA-TM-1176 , Untersuchungen und Mitteilungen; 1023/5
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 14
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    Preliminary Results of Nene II Engine Altitude-chamber Performance Investigation (1948)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: An investigation is being conducted to determine the altitude performance characteristics of the Nene II engine and its components. The present paper presents the preliminary results obtained using jet nozzle 18.00 inches in diameter, with an area equal to 92.2 percent of the area of the standard jet nozzle for this engine. The experimental results presented are for conditions simulating altitudes from 20,000 to 60,000 feet and ram-pressure ratios from 1.1 to 3.5. These ram-pressure ratios correspond to flight Mach numbers between 0.374 and 1.466. Data obtained with the 18.00 inch-diameter jet nozzle and corrected to standard sea-level conditions showed substantially the same trends with altitude as the data previously obtained with an 18.75-inch-diameter nozzle and with an 18.41-inch-diameter nozzle. Jet thrust, air consumption, and fuel consumption, corrected to standard sea-level conditions, increased rapidly with increasing ram-pressure ratio. In general, corrected net thrust specific fuel consumption increased with increase in ram-pressure ratio. Corrected net thrust decreased with an increase in ram-pressure ratio at an engine speed of 8000 rpm. At corrected engine speeds between 8000 and 10,800 rpm, net thrust first decreased with an increase in ram-pressure ratio and then increased with further increase in ram pressure ratio; at corrected engine speeds above 10,800 rpm, net thrust increased continuously with increase in ram-pressure ratio. Tail-pipe temperature decreased with an increase in ram-pressure ratio.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Materialart: NACA-RM-E8H06
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 15
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    Preliminary Results of British Nene II Engine Altitude-Chamber Performance Investigation. I - Altitude Performance Using Standard 18.75-Inch-Diameter Jet Nozzle (1948)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: An investigation is being conducted to determine the altitude performance characteristics of the British Nene II engine and its components. The present paper presents the preliminary results obtained using a standard jet nozzle. The test results presented are for conditions simulating altitudes from sea level to 60,000 feet and ram pressure ratios from 1.0 to 2.3. These ram pressure ratios correspond to flight Mach numbers between zero and 1.16 assuming a 100 percent ram recovery.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Materialart: NACA-RM-E8E12
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 16
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    Investigation of the Flying Mock-Up of the Consolidated Vultee XP-92 Airplane in the Ames 40- by 80-Foot Wind Tunnel. Force and Moment Characteristics (1948)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: This report contains the results of the investigation of the aerodynamic characteristics of the flying mock-up of the Consolidated Vultee XP-92 airplane as conducted in the Ames 40- by 80-foot wind tunnel, Data are presented for test conditions which would give information as to the limits of stability and controllability, and also, the effect of Reynolds number. No analysis of the data has been made.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SA8B04
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 17
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    An Investigation of the Wing and the Wing-Fuselage Combination of a Full-Scale Model of the Republic XP-91 Airplane in the Ames 40-by 80-Foot Wing Tunnel (1948)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Wind-tunnel tests of a full-scale model of the Republic XP-91 airplane were conducted to determine the longitudinal and lateral characteristics of the wing alone and the wing-fuselage combination, the characteristics of the aileron, and the damping in roll af the wing alone. Various high-lift devices were investigated including trailing-edge split flaps and partial- and full-span leading-edge slats and Krueger-type nose flaps. Results of this investigation showed that a very significant gain in maximum lift could be achieved through use of the proper leading-edge device, The maximum lift coefficient of the model with split flaps and the original partial-span straight slats was only 1.2; whereas a value of approximately 1.8 was obtained by drooping the slat and extending it full span, Improvement in maximum lift of approximately the same amount resulted when a full-span nose flap was substituted for the original partial-span slat.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SA8F09
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 18
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    Flight Measurements of Flying Qualities of a P-47D-30 Airplane (AAF No. 43-3441) to Determine Longitudinal Stability and Control and Stalling Characteristics (1948)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Flight tests have been made to determine the longitudinal stability and control and stalling characteristics of the P-47.E-30 airplane. The teat results show the airplane to be unstable stick free in any power-on condition even at the most forward center-of-gravity position tested. At the rearward center-of-gravity position tested the airplane also had neutral to negative stick-fixed stability with power on. The characteristics in accelerated flight were acceptable at the forward center-of-gravity position at low and high altitudes except at high speed where the control-force variations with acceleration were high. At the rearward center-of-gravity position, elevator-force reversals were experienced in turns at low speeds, and the force per g was low at all the other speeds. Ample stall warning was afforded in all the conditions tested and the stalling characteristics were very satisfactory except in the approach and wave-off conditions.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L8A06
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 19
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    Performance of Compressor of XJ-41-V Turbojet Engine V-Performance Analysis of Compressor with Revised Vaned Collector over Range of Compressor Speeds from 3600 to 11,500 RPM (1948)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: An investigation of the XJ-41-V turbojet-engine compressor with a revised vaned collector was conducted to determine the performance of the compressor and to obtain fundamental information on the aerodynamic problems associated with large centrifugal compressors of this type. The original vaned collector was revised by increasing the flow area at the vaned collector entrance. A maximum adiabatic efficiency of 0.81 was obtained et a corrected weight flow of 36.5 pounds per second and a pressure ratio of 1.90. The peak pressure ratio was 3.93 and occurred at an impeller speed of 11,500 rpm at a corrected weight flow of 65.5 pounds per second. Revision of the vaned collector resulted in an increased airflow capacity over the speed range. The design air-flow capacity of 78 pounds per second was very nearly reached at the engine design speed of 11,500 rpm. The compressor air-flow choking point occurred in the vaned collector passage; however, at speeds above 8300 rpm, the air-flow capacity of the impeller was being approached as indicated by large pressure losses in the impeller at maximum air-flow conditions. An increase in compressor air-flow capacity at the higher speeds can possibly be obtained 5y removal of the flow restriction in the impeller, which would result in an increased air density at the vaned collector entrance.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Materialart: NACA-RM-SE8A22
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 20
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    An Investigation of the McDonnell XP-85 Airplane in the Ames 40- by 80-foot Wind Tunnel. Force and Moment Tests (1948)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Wind-tunnel tests of the McDonnell XP-85 airplane were conducted to determine its longitudinal, lateral, and directional stability and the characteristics of the aileron, the ruddervator, the leading-edge droop nose flap, and the stall control vanes. The directional stability of the airplane with numerous skyhook modifications and with a ventral fin was also investigated. The results of the tests showed that the effectiveness of the droop nose flaps and the stall control vanes was negligible with regard to either the maximum lift or longitudinal stability of the airplane. Contrary to any previous small-scale results, extension of the skyhook caused a 75-percent reduction in the directional stability of the airplane for both low and high values of lift coefficient. The simplest solution to the problem short of a major redesign of the skyhook appears to be the adoption of a ventral fin.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Materialart: NACA-RM-SA8I23
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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