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  • Aircraft Design, Testing and Performance  (8)
  • 1950-1954  (5)
  • 1940-1944  (3)
  • 1
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    Experimental Investigation of Spreading Characteristics of Choked Jets Expanding into Quiescent Air (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Investigations have been conducted to determine by means of total-pressure surveys the boundaries of single and twin jets discharging through convergent nozzles into quiescent air. The jet boundaries for the region from the nozzle outlets to a station 6 nozzle diameters downstream are presented for nozzle pressure ratios ranging from 2.5 t o 16.0 and for twin-Jet nozzle center-line spacings ranging from 1.42 to 2.50 nozzle diameters. The effects of these parameters on the interaction of twin Jets are discussed. In order to ascertain the utility of the results for other than the test conditions, the effects of jet temperature, Reynolds number, and humidity on the pressure boundaries have been briefly investigated. The result indicate that for a jet of 2.6 the pressure boundaries are slightly smaller than those of corresponding unheated jets and that the effects of Reynolds number and humidity are negligible.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E50E03a
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The Effect of Blunt-Trailing-Edge Modifications on the High-Speed Stability and Control Characteristics of a Swept-Wing Fighter Airplane (1954)
    In:  CASI
    Details
    Publication Date: 2019-05-25
    Description: An investigation was conducted on a 35 deg swept-wing fighter airplane to determine the effects of several blunt-trailing-edge modifications to the wing and tail on the high-speed stability and control characteristics and tracking performance. The results indicated significant improvement in the pitch-up characteristics for the blunt-aileron configuration at Mach numbers around 0.90. As a result of increased effectiveness of the blunt-trailing-edge aileron, the roll-off, customarily experienced with the unmodified airplane in wings-level flight between Mach numbers of about 0.9 and 1.0 was eliminated, The results also indicated that the increased effectiveness of the blunt aileron more than offset the large associated aileron hinge moment, resulting in significant improvement in the rolling performance at Mach numbers between 0.85 and 1.0. It appeared from these results that the tracking performance with the blunt-aileron configuration in the pitch-up and buffeting flight region at high Mach numbers was considerably improved over that of the unmodified airplane; however, the tracking errors of 8 to 15 mils were definitely unsatisfactory. A drag increment of about O.OOl5 due to the blunt ailerons was noted at Mach numbers to about 0.85. The drag increment was 0 at Mach numbers above 0.90.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-A54C31
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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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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  • 4
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    Wind-Tunnel Investigations of Diving Brakes (1942)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Unduly high diving speeds can be effectively controlled by diving brakes but their employment involves at the same time a number of disagreeable features: namely, rotation of zero lift direction, variation of diviving moment, and, the creation of a potent dead air region.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1033
    Format: application/pdf
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  • 5
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    A Wind-Tunnel Investigation to Determine the Effect of Various Head Designs on the Aerodynamic Characteristics in Pitch of the Army Ordnance Corps T205 3.5-Inch Heat Rocket (1952)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The aerodynamic characteristics in pitch of the Army Ordnance Corps T205 3.5-inch HEAT rocket with various head designs and one fin modification have been determined at velocities of 500, 700 and 900 feet per second in the Langley high-speed 7- by 10-foot tunnel. The results presented are those of the full-scale model. Comparison of results obtained at 500 feet per second shows, in general, that for changes on the forward portion of the head the missile configurations having the greatest stability - most rearward center-of-loads location - were those having the highest drag. However, very limited comparisons indicate that the shape of the rear position of the head may be an important factor in reducing the drag and increasing the restoring moments. Generally, large increases in drag were noted for the various head designs with an increase in Mach number from 0.62 to 0.82. Pitching-moment-curve slopes increased with Mach number on all models except those having reasonably well-faired forward sections. These models showed a decrease in stability with increases in Mach number.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL52G15
    Format: application/pdf
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  • 6
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    Wind-Tunnel Investigation at Low Speed of the Static Longitudinal and Lateral Stability Characteristics of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane (1953)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An experimental investigation has been made in the Langley stability tunnel at low speed to determine the static longitudinal and lateral stability characteristics of a l/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller-blade angle were investigated briefly for the complete model. Most of the tests were made through an angle-of-attack range from about -4 deg. to 29 deg, and the thrust-coefficient range was from 0 t o 0.7. In order to expedite distribution of these data to interested persons, no analysis of the data has been prepared for this report,
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53B20
    Format: application/pdf
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  • 7
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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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  • 8
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    Vibration of a Wing of Finite Span in a Supersonic Flow (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An investigate ion was made of the disturbed motion of a gas for the harmonic vibrations of a thin slightly cambered wing of finite span moving forward with supersonic velocity. This problem was considered by E. A. Krasilshchikova who applied the method of Fourier series and obtained a solution of the space problem for the condition that the Mach cones drawn through the leading edge of the wing intersect the wing or are tangent to it. In this paper, a different method of solution is given, which is free from the previously mentioned condition. In particular, the vibrations of a triangular wing lying within the Mach cone are considered.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1257 , Prikladnaya Matematika i Mekhanika; 11; 371-376
    Format: application/pdf
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