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  • General Chemistry  (554)
  • Aircraft Design, Testing and Performance  (19)
  • 1955-1959
  • 1940-1944  (573)
  • 1944  (96)
  • 1940  (477)
Collection
Keywords
Publisher
Years
  • 1955-1959
  • 1940-1944  (573)
Year
  • 1
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    The Effects of Aerodynamic Heating on Ice Formations on Airplane Propellers (1940)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: An investigation has been made of the effect of aerodynamic heating on propeller-blade temperatures. The blade temperature rise resulting from aerodynamic heating was measured and the relation between the resulting blade temperatures and the outer limit of the iced-over region was examined. It was found that the outermost station at which ice formed on a propeller blade was determined by the blade temperature rise resulting from the aerodynamic heating at that point.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-153
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    High-Speed Tests of a Model Twin-Engine Low-Wing Transport Airplane (1940)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: Force tests were made of a 1/8-scale model of a twin-engine low-wing transport airplane in the NACA 8-foot high-speed wind tunnel to investigate compressibility and interference effects at speeds up to 450 miles per hour. In addition to tests of the standard arrangement of the model tests were made with several modifications designed to reduce the drag and to increase the critical speed. The results show serious increases in drag at critical speeds below 450 miles per hour due to the occurrence of compressibility burbles on the standard radial-engine cowlings, on sections of the wing as a result of wing-nacelle interference, and on the semi-retracted main landing wheels. The critical speed at which the shock occurred on the standard cowlings was 20 miles per hour lower in the presence of the fuselage than in the presence of the wing only. The drag of the complete model was reduced 25% at 300 miles per hour by completely retracting the landing gear, fairing the windshield irregularities, and substituting streamline nacelles (with allowance made for the proper amount of cooling-air flow) for the standard nacelle arrangement. The values of the critical Mach number were extended from 0.47 to 0.60 as a result of the aforementioned improvements. The principal purpose of the reported tests was to investigate the effect of compressibility on the drag of the component parts of a representative large airplane and on the overall drag of such an airplane. The influence of interference on compressibility effects was also studied. In addition, it was proposed to test several modifications of the standard component parts that gave promise of an improvement in aerodynamic characteristics.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-143
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    A Theoretical Investigation of the Rolling Oscillations of an Airplane with Ailerons Free (1944)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An analysis is made of the stability of an airplane with ailerons free, with particular attention to the motions when the ailerons have a tendency to float against the wind. The present analysis supersedes the aileron investigation contained in NACA Report No. 709. The equations of motion are first written to include yawing and sideslipping, and it is demonstrated that the principal effects of freeing the ailerons can be determined without regard to these motions. If the ailerons tend to float against the wind and have a high degree of aerodynamic balance, rolling oscillations, in addition to the normal lateral oscillations, are likely to occur. On the basis of the equations including only the rolling motion and the aileron deflection, formulas are derived for the stability and damping of the rolling oscillations in terms of the hinge moment derivatives and other characteristics of the ailerons and airplane. Charts are also presented showing the oscillatory regions and stability boundaries for a fictitious airplane of conventional proportions. The effects of friction in the control system are investigated and discussed. If the ailerons tend to trail with the wind, the condition for stable variation of stick force with aileron deflection is found to determine the amount of aerodynamic balance that may be used. If the ailerons tend to float against the wind, the period and damping of the rolling oscillations are found to be satisfactory (in a mass-balanced system) so long as the restoring moment is not completely balanced out. Unbalanced mass behind the hinge, however, has an unfavorable effect on the damping of the oscillations and so shifts the boundary that close aerodynamic balance may not be attainable.
    Keywords: Aircraft Design, Testing and Performance
    Type: AD-A301275 , NACA-TR-787 , NASA-TM-111361 , NAS 1.15:111361
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Analysis of Experimental Investigations of the Planing Process of the Surface of Water (1944)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Pressure distribution and spray measurements were carried out on rectangular flat and V-bottom planing surfaces. Lift, resistance, and center of pressure data are analyzed and it is shown how these values may be computed for the pure planing procees of a flat or V-bottom suface of arbitrary beam, load and speed, the method being illustrated with the aid of an example.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1061 , Jahrbuch 1937 der Deutschen Luftfahrtforschung; 320-339
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Experiments on Drag of Revolving Disks, Cylinders, and Streamline Rods at High Speeds (1944)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: An experimental investigation concerned primarily with the extension of test data on the drag of revolving disks, cylinders, and streamline rods to high Mach numbers and Reynolds numbers is presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TR-793
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    The Effect of Several Armament Installations on the Drag of 1/8-Scale Model of the B-32 Airplane (1944)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The effect of several armament installations on the drag of a 1/8 scale model of the B-32 airplane was determined. Turrets in the following positions were tested: nose, tail, upper forward, upper aft, and lower. The nose and tail turrets were each equipped with two.50-caliber guns. Upper turrets were of three types: two.50-caliber guns, four.50-caliber guns, and 20-millimeter cannon. Lower turrets were of two types: two.50-caliber guns and four.50-caliber guns. The effect of streamlining the upper two- and four-gun turrets and of extending the lower two-gun turret was determined. The tests were conducted in the Langley 19-foot. pressure tunnel at a Reynolds number of approximately 2,960,000 and a Mach number of 0.13. Large increases in drag coefficient were caused by the complete armament installations. At a lift coefficient of 0. 4 the installations with nonstreamlined upper turrets and the lower turret retracted increased the drag coefficient by 0.0022 and 0.0027 for the two-gun and four-gun turret installations, respectively. Streamlining the upper turrets reduced the drag of these installations by approximately 40 percent with the upper turrets streamlined, the drag increase was about the same for either the two- or four-gun turret installation. The streamlined two-cannon upper turrets increased the drag about the same amount as the two-gun upper turrets that were not streamlined. Extension of the lower turret. increased the drag slightly more than the whole streamlined gun-turret installation.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-MR-L4L30a
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Comparison of Three Exit-Area Control Devices on an N.A.C.A. Cowling, Special Report (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Adjustable cowling flaps, an adjustable-length cowling skirt, and a bottom opening with adjustable flap were tested as means of controlling the rate of cooling-air flow through an air-cooled radial-engine cowling. The devices were tested in the NACA 20-foot tunnel on a model wing-nacelle-propeller combination, through an airspeed range of 20 to 80 miles per hour, and with the propeller blade angle set 23 degrees at 0.75 of the tip radius. The resistance of the engine to air flow through the cowling was simulated by a perforated plate. The results indicated that the adjustable cowling flap and the bottom opening with adjustable flap were about equally effective on the basis of pressure drop obtainable and that both were more effective means of increasing the pressure drop through the cowling than the adjustable-length skirt. At conditions of equal cooling-air flow, the net efficiency obtained with the adjustable cowling flaps and the adjustable-length cowling skirt was about 1% greater than the net efficiency obtained with the bottom opening with adjustable flap.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-144
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Wind-Tunnel Investigation of Rectangular Air-Duct Entrances in the Leading Edge of an NACA 23018 Wing, Special Report (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A preliminary investigation of a number of duct entrances of rectangular shape installed in the leading edge of a wing was conducted in the NACA 20-foot tunnel to determine the external drag, the available pressure, the critical Mach numbers, and the effect on the maximum lift. The results showed that the most satisfactory entrances, which had practically no effect on the wing characteristics, had their lips approximately in the vertical plane of the leading edge of the wing. This requirement necessitated extending the lips outside the wing contour for all except the small entrances. Full dynamic pressure was found to be available over a fairly wide range of angle of attack. The critical Mach number for a small entrance was calculated to be as high as that for the plain wing but was slightly lower for the larger entrances tested.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-154
    Format: application/pdf
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  • 9
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    Full-Scale Tests of 4- and 6-Blade, Single- and Dual-Rotating Propellers, Special Report (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Test of 10-foot diameter, 4- and 6-blade single- and dual-rotating propellers were conducted in the 20-foot propeller-research tunnel. The propellers were mounted at the front end of a streamline body incorporating spinners to house the hub portions. The effect of a symmetrical wing mounted in the slipstream was investigated. The blade angles investigated ranged from 20 degrees to 65 degrees; the latter setting corresponds to airplane speeds of over 500 miles per hour. The results indicate that dual-rotating propellers were from 0 to 6% more efficient than single-rotating ones; but when operating in the presence of a wing the gain was reduced about one-half. Other advantages of dual-rotating propellers were found to include greater power absorption and greater efficiency at the low V/nD operating range of high pitch propellers.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-157
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Detail Calculations of the Estimated Shift in Stick-Fixed Neutral Point Due to the Windmilling Propeller and to the Fuselage of the Republic XF-12 Airplane (1944)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Detail calculations are presented of the shifts in stick-fixed neutral point of the Republic XF-12 airplane due to the windmilling propellers and to the fuselage. The results of these calculations differ somewhat from those previously made for this airplane by Republic Aviation Corporation personnel under the direction of Langley flight division personnel. Due to these differences the neutral point for the airplane is predicted to be 37.8 percent mean aerodynamic chord, instead of 40.8 percent mean aerodynamic chord as previously reported.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-CMR-L4J16
    Format: application/pdf
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