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  • Aircraft Design, Testing and Performance  (128)
  • 1955-1959  (85)
  • 1940-1944  (43)
  • 1
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    The Development of a New Lateral-Control Arrangement (1941)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Development work on an arrangement using ailerons and spoilers for lateral control was carried out by the Vought-Sikorsky Aircraft Division of the United Aircraft Corporation on a small commercial airplane in flight and on an airfoil in a wind tunnel. Spoiler hinge moments were reduced by aerodynamic balance. The arrangement was then built into an experimental airplane and further improvements were adopted as the result of flight and tunnel tests. The use of ailerons for lateral control with flaps up, spoilers with flaps full down, and gradual transition as the flaps are lowered was found to provide lateral control under the flight conditions for which they were best suited. The ailerons were of short span, permitting the use of long-span flaps, and were drooped to a relatively large angle when the flaps were deflected. A high maximum lift coefficient was thus attained. With large control deflections in the intermediate flap-angle range and spoiler effectiveness near neutral improved by "ventilating" the spoiler, the lateral control was satisfactory for the experimental airplane and was a definite improvement over that of a conventional control arrangement.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Tests of the XP-46 Airplane in the N.A.C.A. Full-Scale Wind Tunnel (1940)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: An investigation has been conducted on a full-scale model of the proposed XP-46 airplane in the N. A. C. A. full-scale wind tunnel pursuant to the request of the Amy Air Corps, Materiel Division. The primary purpose of the investigation was to determine the optimum arrangement of the various component parts to obtain the maximum high speed and to provide adequate engine cooling. Additional tests included a determination of the stalling characteristics and the effectiveness of ailerons and elevators. The profile drag of the wing was ascertained by the momentum method; the location of the transition point on the wing and the critical compressibility velocities of the various airplane components were determined from surface pressure surveys.
    Keywords: Aircraft Design, Testing and Performance
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    NASA TECHNICAL REPORTS
  • 3
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    New Research on the Cowling and Cooling of Radial Engines (1943)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: An extensive series of wind-tunnel tests on a half-scale conventional, nacelle model were made by the United Aircraft Corporation to determine and correlate the effects of many variables on cooling air flow and nacelle drag. The primary investigation was concerned with the reaction of these factors to varying conditions ahead of, across, and behind the engine. In the light of this investigation, common misconceptions and factors which are frequently overlooked in the cooling and cowling of radial engines are considered in some detail. Data are presented to support certain design recommendations and conclusions which should lead toward the improvement of present engine installations. Several charts are included to facilitate the estimation of cooling drag, available cooling pressure, and cowl exit area.
    Keywords: Aircraft Design, Testing and Performance
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    NASA TECHNICAL REPORTS
  • 4
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    NACA Apparatus and Methods for Take-Off and Landing Measurements (1943)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Experience has shown that the determination of the take-off and. landing characteristics of airplanes requires specialized, equipment of a high degree of precision and reliability and demands great care in the evaluation and interpretation of data. It is believed, therefore, that a description of the apparatus and methods that have been developed by the NACA for these measurements might be of considerable interest, particularly to flight-test groups that have had little experience with landing and. take-off measurements. The basic principles and essential details of the Committee's equipment are described, the methods of utilizing the apparatus and of reducing the data are explained, and sample test results are presented.
    Keywords: Aircraft Design, Testing and Performance
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    NASA TECHNICAL REPORTS
  • 5
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    Lift and Drag of a Swept-Wing Fighter Airplane at Transonic and Supersonic Speeds (1959)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: A flight investigation was made of the lift and drag of a sweptwing fighter airplane in the basic configuration and in a slats-locked-closed configuration over a Mach number range from about 0.63 to about 1.44. At a nominal lift coefficient of 0.1 negligible drag-coefficient difference existed between the two configurations over a comparable Mach number and altitude range. For the basic configuration at zero lift the supersonic drag level was about three times as great as the subsonic drag level, which was about 0.01, whereas the drag-due-to-lift factor increased about 137 percent over the test Mach number range. At comparable Mach numbers the high-altitude data produced a larger lift-curve slope and showed a more pronounced variation of lift-curve slope in the transonic region than did the low-altitude data. For the high-altitude data the lift-curve slope at a Mach number of 1.44 was approximately 62 percent of the value at a Mach number of 0.9.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-10-1-58H , AFRC-E-DAA-TN47945
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Boundary-Layer Transition on an Open-Nose Cone at Mach 3.1 (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Comparison of transition locations for an open-nose cone, a conventional sharp cone, and a hollow cylinder showed that transition locations on the open-nose cone and the hollow cylinder were identical but differed greatly from those on the sharp cone. This is believed to be caused by the essentially two-dimensional character of leading edge of the open-nose cone. Bluntness effects on the open-nose cone observed on the hollow cylinder. Transition 2.2 times the sharp-cone transition distance by blunting the tip.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-4214
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Study of Jet-Propulsion System Comprising Blower, Burner, and Nozzle (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study was made of the performance of a jet-propulsion system composed of an engine-driven blower, a combustion chamber, and a discharge nozzle. A simplified analysis is made of this system for the purpose of showing in concise form the effect of the important design variables and operating conditions on jet thrust, thrust horsepower, and fuel consumption. Curves are presented that permit a rapid evaluation of the performance of this system for a range of operating conditions. The performance for an illustrative case of a power plant of the type under consideration id discussed in detail. It is shown that for a given airplane velocity the jet thrust horsepower depends mainly on the blower power and the amount of fuel burned in the jet; the higher the thrust horsepower is for a given blower power, the higher the fuel consumption per thrust horsepower. Within limits the amount of air pumped has only a secondary effect on the thrust horsepower and efficiency. A lower limit on air flow for a given fuel flow occurs where the combustion-chamber temperature becomes excessive on the basis of the strength of the structure. As the air-flow rate is increased, an upper limit is reached where, for a given blower power, fuel-flow rate, and combustion-chamber size, further increase in air flow causes a decrease in power and efficiency. This decrease in power is caused by excessive velocity through the combustion chamber, attended by an excessive pressure drop caused by momentum changes occurring during combustion.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-E-212 , NACA-ACR-E4E06
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Tests of Thermal-electric De-icing Equipment for Propellers (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flights were made in natural icing conditions at the NACA Ice Research Project, Minneapolis, Minn. to test several designs of thermal-electric propeller de-icing blade shoes and a hub-generator design. It was found that a minimum average unit power of 2.5 watts per square inch of blade-shoe area would protect the propeller blades at the test conditions. The most satisfactory blade shoe of the three designs tested extended to the 20-percent-chord point and to 90 percent of the blade radius. A concentration of heat in the leading-edge region of this shoe was found to reduce the power input necessary for satisfactory de-icing. A satisfactory thermal design of blade shoe and a hub generator of sufficient capacity were developed.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-A-47 , NACA-ARR-4A20
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Effect of Changes in Aileron Rigging on the Stick Forces of a High-Speed Fighter Airplane (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of changes in aileron rigging between 2 deg up and 2 deg down on the stick forces were determined from wind-tunnel data for a finite-span wing model. These effects were investigated for ailerons deflecting equally in both directions and linearly with stick deflection. Data were analyzed for a Frise, a sealed internally balanced, and a beveled-trailing-edge aileron. The results of the analysis showed that only ailerons having linear hinge-moment characteristics are unaffected by changes in rigging and indicated that ailerons having decidedly nonlinear hinge-moment-coefficient curves, particularly for deflections near 0 deg, are very sensitive to changes in rigging.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-289 , NACA-RB-L4E11
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Wind-Tunnel Investigation of Perforated Split Flaps for Use as Dive Brakes on a Tapered NACA 23012 Airfoil (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic characteristics of a tapered NACA 23012 airfoil with single and double perforated split flaps have been determined in the NACA 7- by 10-foot wind tunnel. Dynamic pressure surveys were made behind the airfoil at the approximate location of the tail in order to determine the extent and location of the wake for several of the flap arrangements. In addition, computations have been made of an application of perforated double split flaps for use as fighter brakes. The results indicated that single or double perforated split flaps may be used to obtain satisfactory dive control without undue buffeting effects and that single or double perforated split flaps may also be used as fighter brakes. The perforated split flaps had approximately the same effects on the aerodynamic and wake characteristics of the tapered airfoil as on a comparable rectangular airfoil.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-373
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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