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  • Aerodynamics  (84)
  • Seismology  (46)
  • 1940-1944  (88)
  • 1935-1939  (42)
  • 1
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    Tests of Several Model Nacelle-Propeller Arrangements in Front of a Wing (1939)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: An investigation was conducted in the N.A.C.A. 20-foot wind tunnel to determine the drag, the propulsive and net efficiencies, and the cooling characteristics of severa1 scale-model arrangements of air-cooled radial-engine nacelles and present-day propellers in front of an 18- percent-thick, 5- by 15-foot airfoil. This report deals with an investigation of wing-nacelle arrangements simulating the geometric proportions of airplanes in the 40,000- to 70,000- pound weight classification and having the nacelles located in the vicinity of the optimum location determined from the earlier tests.
    Keywords: Aerodynamics
    Type: NACA-SR-123
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Wind-Tunnel Investigation of an N.A.C.A. 23012 Airfoil with a Slotted Flap and Three Types of Auxiliary Flap (1938)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: An investigation was made in the N.A.C.A. 7- by 10- foot wind tunnel to determine the aerodynamic section characteristics of an N. A. C. A. 23012 airfoil with a single main slotted flap equipped successively with auxiliary flaps of the plain, split, and slotted types. A test installation mas used in which an airfoil of 7-foot span was mounted vertically between the upper and the lower sides of the closed test section so that two-dimensional flow was approximated. On the basis of maximum lift coefficient, low drag at moderate and high lift coefficients, and high drag at high lift coefficients, the optimum combination of the arrangements was found to be the double slotted flap . All the auxiliary flaps tested, however, increased the magnitudes of the pitching moments over those of the main slotted flap alone.
    Keywords: Aerodynamics
    Type: NACA-SR-97
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Interference of Tail Surfaces and Wing and Fuselage from Tests of 17 Combinations in the N.A.C.A. Variable-Density Tunnel (1939)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: An investigation of the interference associated with tail surfaces added to wing-fuselage combinations was included in the interference program in progress in the NACA variable-density tunnel. The results indicate that, in aerodynamically clean combinations, the increment to the high-speed drag can be estimated from section characteristics within useful limits of accuracy. The interference appears mainly as effects on the downwash angel and as losses in the tail. An interference burble, which markedly increases the glide-path angle and the stability in pitch before the actual stall, may be considered a means of obtaining satisfactory stalling characteristics for a complete combination.
    Keywords: Aerodynamics
    Type: NACA-SR-98
    Format: application/pdf
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  • 4
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    High-Speed Tests of Radial-Engine Cowlings (1939)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: The drag characteristics of eight radial-engine cowlings have been determined over a wide speed range in the N.A.C.A. 8-foot high-speed wind tunnel. The pressure distribution over all cowlings was measured, to and above the speed of the compressibility burble, as an aid in interpreting the force tests. One-fifth-scale models of radial-engine cowlings on a wing-nacelle combination mere used in the tests.
    Keywords: Aerodynamics
    Type: NACA-SR-109
    Format: application/pdf
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  • 5
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    Two-Dimensional Potential Flow Past an Ordinary Thick Wing Profile (1942)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: This report deals with the development of a method which gives a lucid and convenient solution of the flow conditions in the vicinity of a common, thick airfoil section wherein the thickness of the profile is taken into account. The method consists in making the airfoil the streamline in a parallel flow by disposing on its mean line certain source and vortex distributions the fields of which are superposed on the parallel flow. These distributions of singularities are secured for the generalized Karman-Trefftz profile by means of conformal transformation from the flow about a circle. Five different distribution functions are afforded for the density of superposition, which combine in a specified manner to the necessary distributions of singularity and represent a generalized Karman-Trefftz profile in parallel flow. For these profiles the speed for each of the five distributions is then computed independently of the angle of attack.
    Keywords: Aerodynamics
    Type: NACA-TM-1023
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Spinning Characteristics of Wings III : a Rectangular and Tapered Clark Y Monoplane Wing with Rounded Tips (1937)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: An investigation was made to determine the spinning characteristics of Clark Y monoplane wings with different plan forms. A rectangular wing and a wing tapered 5:2, both with rounded tips, were tested on the N.A.C.A. spinning balance in the 5-foot vertical wind tunnel. The aerodynamic characteristics of the models and a prediction of the angles of sideslip for steady spins are given. Also included is an estimate of the yawning moment that must be furnished by the parts of the airplane to balance the inertia couples and wing yawing moment for spinning equilibrium. The effects on the spin of changes in plan form and of variations of some of the important parameters are discussed and the results are compared with those for a rectangular wing with square tips. It is concluded that for a conventional monoplane using Clark Y wing the sideslip will be algebraically larger for the wing with the rounded tip than for the wing with the square tip and will be largest for the tapered wing. The effect of plan form on the spin will vary with the type of airplane; and the provision of a yawing-moment coefficient of -0.025 (i.e., opposing the spin) by the tail, fuselage, and interference effects will insure against the attainment of equilibrium on a steady spin for any of the plan forms tested and for any of the parameters used in the analysis.
    Keywords: Aerodynamics
    Type: NACA-TN-612
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation (1942)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, 20 degrees, and 40 degrees are presented. The normal force coefficients agree with lift coefficients obtained in previous test of the same model, except for the maximum lifts with flap deflection. Pressure distribution measurements were made at Reynolds Number of about 6,000,000.
    Keywords: Aerodynamics
    Type: NACA-WR-L-678
    Format: application/pdf
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  • 8
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    Aerodynamic Characteristics for Internal-Balance and Frise Type Ailerons on an NACA 6 Series Low-Drag Tip Section of the Wing for the XP-63 Airplane (1942)
    In:  CASI
    Details
    Publication Date: 2019-08-07
    Description: At the request of the Army Air Forces, Materiel Command, tests were made in the two-Dimensional low-turbulence tunnel of a mode l submitted by Bell Aircraft Corporation as the tip section of the wing of the xp-63 airplane. " The model was a NACA 66, 2x-2l6 a = 0.6 airfoil section of 50-inch chord and made of dural according to standard sheet-metal practice. The model was fitted for an internal-balance aileron with a tab and a Frise type aileron. Several alterations of the skirts and balance on the internal- balance aileron were tested to obtain the various aerodynamic characteristics of the aileron.
    Keywords: Aerodynamics
    Format: application/pdf
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  • 9
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    DVL Angular Velocity Recorder (1944)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In many studies, especially of nonstationary flight motion, it is necessary to determine the angular velocities at which the airplane rotates about its various axes. The three-component recorder is designed to serve this purpose. If the angular velocity for one flight attitude is known, other important quantities can be derived from its time rate of change, such as the angular acceleration by differentiations, or - by integration - the angles of position of the airplane - that is, the angles formed by the airplane axes with the axis direction presented at the instant of the beginning of the motion that is to be investigated.
    Keywords: Aerodynamics
    Type: NACA-TM-1065 , Luftwissen; 5; 8; 297-298
    Format: application/pdf
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  • 10
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    The Wall Interference of a Wind Tunnel of Elliptic Cross Section (1944)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The wall interference is obtained for a wind tunnel of elliptic section for the two cases of closed and open working sections. The approximate and exact methods used gave results in practically good agreement. Corresponding to the result given by Glauert for the case of the closed rectangular section, the interference is found to be a minimum for a ratio of minor to major axis of 1:square root of 6 This, however, is true only for the case where the span of the airfoil is small in comparison with the width of the tunnel. For a longer airfoil the favorable ellipse is flatter. In the case of the open working section the circular shape gives the minimum interference.
    Keywords: Aerodynamics
    Type: NACA-TM-1075 , Journal of the Society of Mechanical Engineers; 36; 190; 123-127
    Format: application/pdf
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