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  • Aerodynamics  (25)
  • 2015-2019
  • 2005-2009
  • 2000-2004
  • 1975-1979
  • 1950-1954
  • 1945-1949  (25)
  • 1948  (25)
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Keywords
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  • 2015-2019
  • 2005-2009
  • 2000-2004
  • 1975-1979
  • 1950-1954
    • +
Year
  • 1
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    An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analysis is presented of the influence of wing aspect ratio and tail location on the effects of compressibility upon static longitudinal stability. The investigation showed that the use of reduced wing aspect ratios or short tail lengths leads to serious reductions in high-speed stability and the possibility of high-speed instability.
    Keywords: Aerodynamics
    Type: NACA-RM-A7J13
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Investigation of the Penetration on an Air Jet Directed Perpendicularly to an Air Stream (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted to determine the penetration of a circular air Jet directed perpendicularly to an air stream as a function of Jet density, Jet velocity, air-stream density, air-stream velocity, Jet diameter, and distance downstream from the Jet. The penetration was determined for nearly constant values of air-stream density at two tunnel velocities, four Jet diameters, four positions downstream of the Jet, and for a large range of Jet velocities and densities. An equation for the penetration was obtained in terms of the Jet diameter, the distance downstream from the jet, and the ratios of Jet and air-stream velocities and densities.
    Keywords: Aerodynamics
    Type: NACA-TN-1615
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the Grumman XF9F-2 Airplane with Wing-Tip Tanks Installed (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of the spin and recovery characteristics of a 1/24-scale model of the Grumman XF9F-2 airplane with wing-tip tanks installed has been conducted-in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect spin and recovery characteristics of the model for a range of possible loadings of the tip tanks were determined. Spin and recovery characteristics without tanks were determined in a previous investigation. The model results indicated that the airplane spins will generally be oscillatory and that recoveries will be satisfactory for all loadings by normal recovery technique (full rudder reversal followed approximately one-half turn later by moving the elevator down). The rudder force necessary for recovery should be within the physical capability of the pilot but the elevator force may be excessive so that some type of balance or booster might be necessary, or it might be necessary to jettison the wing-tip tanks.
    Keywords: Aerodynamics
    Type: NACA-RM-SL9F01
    Format: application/pdf
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  • 4
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    Supplementary Investigation to Determine the Effects of Center-of-Gravity Position on the Spin, Longitudinal-Trim, and Tumbling Characteristics of a 1/20-Scale Model of the Consolidated Vultee 7002 Airplane (Flying Mock-up of XF-92) (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A supplementary wind-tunnel investigation has been conducted to determine the effect of rearward positions of the center of gravity on the spin, longitudinal-trim, and tumbling characteristics of the 1/20-scale model of the Consolidated Vultee 7002 airplane equipped with the single vertical tail. A few tests were also made with dual vertical tails added to the model. The model was ballasted to represent, the airplane in its approximate design gross weight for two center-of-gravity positions, 3O and 35 percent of the mean aerodynamic chord. The original tests previously reported were for a center-of-gravity position of 24 percent of the mean aerodynamic chord.
    Keywords: Aerodynamics
    Type: NACA-RM-SL9B24
    Format: application/pdf
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  • 5
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    A Theoretical Investigation of the Dynamic Lateral Stability Characteristics of the MX-838 (XB-51) Airplane (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: At the request of the Air Material Command, U. S. Air Force, a theoretical study has been made of the dynamic lateral stability characteristics of the MX-838 (XB-51) airplane. The calculations included the determination of the neutral-oscillatory-stability boundary (R = 0), the period and time to damp to one-half amplitude of the lateral oscillation, end the time to damp to one-half amplitude for the spiral mode. Factors varied in the investigation were lift coefficient, wing incidence, wing loading, and altitude. The results of the investigation showed that the lateral oscillation of the airplane is unstable below a lift coefficient of 1.2 with flaps . deflected 40deg but is stable over the entire speed range with flaps deflected 20deg or 0deg. The results showed that satisfactory oscillatory stability can probably be obtained for all lift coefficients with the proper variation of flap deflection and wing incidence with airspeed. Reducing the positive wing incidence improved the oscillatory stability characteristics. The airplane is spirally unstable for most conditions but the instability is mild and the Air Force requirements are easily met.
    Keywords: Aerodynamics
    Type: NACA-RM-SL8K10
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-type 4000.pound-thrust turboJet engine for a range of pressure altitudes from 5000 to 40,000 feet and ram pressure ratios from 1.02 to 1.86 are presented and the experimental and analytical methods employed are discussed. By means of suitable generalizing factors applied to the measured performance data, curves were obtained from which the engine performance at any altitude for a given ram pressure ratio can be estimated. The data presented include the windmilling drag characteristics of the turbojet engine for the ranges of altitudes and ram pressure ratios covered by the performance data.
    Keywords: Aerodynamics
    Type: NACA-RM-E8F09-Pt-1
    Format: application/pdf
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  • 7
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    High-Speed Wind-Tunnel Investigation of the Longitudinal Stability and Control Characteristics of a 0.10-Scale Model of the Grumman XF9F-2 Airplane, TED No. NACA DE301 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was made in the Langley high-speed 7-by 10-foot tunnel to determine the high-speed longitudinal stability end con&o1 characteristics of a 0.01-scale model of the Grumman XF9F-2 airplane in the Mach number range from 0.40 to 0.85. The results indicated that the lift and drag force breaks occurred at a Mach number of about 0.76. The aerodynamic-center position moved rearward after the force break and control position stability was present for all Mach numbers up to a Mach number of 0.80.
    Keywords: Aerodynamics
    Type: NACA-RM-SL8K16
    Format: application/pdf
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  • 8
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    Hydrodynamic Characteristics of an Aerodynamically Refined Planing-Tail Hull (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The hydrodynamic characteristics of an aerodynamically refined planing-tail hull were determined from dynamic model tests in Langley tank no. 2. Stable take-off could be made for a wide range of locations of the center of gravity. The lower porpoising limit peak was high, but no upper limit was encountered. Resistance was high, being about the same as that of float seaplanes. A reasonable range of trims for stable landings was available only in the aft range of center-of-gravity locations.
    Keywords: Aerodynamics
    Type: NACA-RM-L8G16
    Format: application/pdf
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  • 9
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    Investigation of the Flying Mock-Up of Consolidated Vultee XP-92 Airplane in the Ames 40- by 80-Foot Wind Tunnel: Pressure Distributions (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This report contains the results of the wind tunnel investigation of the pressure distribution on the flying mock-up of the Consolidated Vultee XP-92 airplane. Data are presented for the pressure distribution over the wing, vertical tail and the fuselage, and for the pressure loss and rate of flow through the ducted fuselage. Data are also presented for the calibration of two airspeed indicators, and for the calibration of angle-of-attack and sideslip-angle indicator vanes.
    Keywords: Aerodynamics
    Type: NACA-RM-SA8D08
    Format: application/pdf
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  • 10
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    An Investigation of the McDonnell XP-85 Airplane in the Ames 40- by 80-Foot Wind Tunnel: Pressure-Distribution Tests (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Pressure measurements were made during wind-tunnel tests of the McDonnell XP-85 parasite fighter. Static-pressure orifices were located over the fuselage nose, over the canopy, along the wing root, and along the upper and lower stabilizer roots. A total-pressure and static-pressure rake was located in the turbojet engine air-intake duct. It was installed at the station where the compressor face would be located. Pressure data were obtained for two airplane conditions, clean and with skyhook extended, through a range of angle of attack and a range of yaw.
    Keywords: Aerodynamics
    Type: NACA-RM-SA8J22
    Format: application/pdf
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