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  • 1
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    Low-speed wind-tunnel tests of single- and counter-rotation propellers (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A low-speed (Mach 0 to 0.3) wind-tunnel investigation was conducted to determine the basic performance, force and moment characteristics, and flow-field velocities of single- and counter-rotation propellers. Compared with the eight-blade single-rotation propeller, a four- by four- (4 x 4) blade counter-rotation propeller with the same blade design produced substantially higher thrust coefficients for the same blade angles and advance ratios. The results further indicated that ingestion of the wake from a supporting pylon for a pusher configuration produced no significant change in the propeller thrust performance for either the single- or counter-rotation propellers. A two-component laser velocimeter (LV) system was used to make detailed measurements of the propeller flow fields. Results show increasing slipstream velocities with increasing blade angle and decreasing advance ratio. Flow-field measurements for the counter-rotation propeller show that the rear propeller turned the flow in the opposite direction from the front propeller and, therefore, could eliminate the swirl component of velocity, as would be expected.
    Keywords: AERODYNAMICS
    Type: NASA-TM-87656 , L-16077 , NAS 1.15:87656
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Aerodynamic characteristics of a propeller powered high lift semispan wing (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted on the engine/airframe integration aerodynamics for potential high-lift aircraft configurations. The model consisted of a semispan wing with a double-isolated flap system and a Krueger leading edge device. The advanced propeller and the powered nacelle were tested and aerodynamic characteristics of the combined system are presented. It was found that the lift coefficient of the powered wing could be increased by the propeller slipstream when the rotational speed was increased and high-lift devices were deployed. Moving the nacelle/propeller closer to the wing in the vertical direction indicated higher lift augmentation than a shift in the longitudinal direction. A pitch-down nacelle inclination enhanced the lift performance of the system much better than vertical and horizontal variation of the nacelle locations and showed that the powered wing can sustain higher angles of attack near maximum lift performance.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0388
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Low-speed wind-tunnel tests of an advanced eight-bladed propeller (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As part of a research program on advanced turboprop aircraft aerodynamics, a low-speed wind-tunnel investigation was conducted to document the basic performance and force and moment characteristics of an advanced eight-bladed propeller. The results show that in addition to the normal force and pitching moment produced by the propeller/nacelle combination at angle of attack, a significant side force and yawing moment are also produced. Furthermore, it is shown that for test conditions wherein compressibility effects can be ignored, accurate simulation of propeller performance and flow fields can be achieved by matching the nondimensional power loading of the model propeller to that of the full-scale propeller.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86364 , L-15898 , NAS 1.15:86364
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Wind tunnel test results of heavy rain effects on airfoil performance (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The effects of simulated heavy rain on the aerodynamic characteristics of a NACA 64-210 airfoil section equipped with high-lift devices were investigated in the NASA Langley 14- by 22-Foot Subsonic Tunnel. The experiment was part of an on-going NASA program to determine the effect of heavy rain on airplane performance, and was directed at providing insight into scaling laws for subscale model testing of rain effects. The model used in the investigation had a chord of 2.5 feet, a span of 8.0 feet, and was mounted on the tunnel centerline between two large endplates. A water spray distribution system was located 10 chord lengths upstream of the model. The sensitivity of test results to partial-span coverage of the model in the simulated rain environment as compared to full-span coverage was also investigated. The lift and drag data obtained for the high-lift configuration show excellent repeatability of results compared to the previous data. Results obtained for various spray concentrations and tunnel speeds showed significant losses in maximum lift capability, a decrease in the angle of attack for maximum lift, and an increase in drag as the stimulated rain rate was increased. The test results also indicated that the data were not strongly affected by surface tension effects for the high-lift configuration.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-0260
    Format: text
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  • 5
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    Study of several factors affecting crew escape trajectories from the Space Shuttle Orbiter at low-subsonic speeds (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Factors affecting the bailout characteristics from the space shuttle orbiter at low-subsonic speeds were investigated. In the 12-foot low-speed tunnel and the 4 by 7-meter tunnel with 0.03-scale models. The effect of crew-model exit velocity, body position, and body weight were studied with egress from the main side hatch with the orbiter upright and from the upper cabin hatch with the orbiter inverted. Crew model drag and flow field measurements around the orbiter were estimated. The high-angle-of-attack trim characteristics of the orbiter was determined by force tests in an attempt to improve bailout conditions. A computer simulation was made to evaluate the maneuver necessary to attain the high-angle-of-attack trim.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-86303 , L-15839 , NAS 1.15:86303
    Format: application/pdf
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  • 6
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    Low-speed aerodynamic characteristics of a highly swept arrow wing configuration with several deflected leading edge concepts (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effectiveness of leading edge concepts for minimizing or controlling leading edge flow separation was studied. Emphasis was placed on low speed performance, stability, and control characteristics of configurations with highly swept wings. Simple deflection of the leading edge, a variable camber leading edge system, and a leading edge vortex flow system were among the concepts studied. The data are presented without analysis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-80180
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Analysis of a turbulent boundary layer over a moving ground plane (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Four methods of predicting the integral and friction parameters for a turbulent boundary layer over a moving ground plane were evaluated by using test information obtained in 76.2- by 50.8-centimeter tunnel. The tunnel was operated in the open sidewall configuration. These methods are (1) relative integral parameter method, (2) modified power law method, (3) relative power law method, and (4) modified law of the wall method. The modified law of the wall method predicts a more rapid decrease in skin friction with an increase in the ratio of belt velocity to free steam velocity than do methods (1) and (3).
    Keywords: FLUID MECHANICS
    Type: NASA-TN-D-6788 , L-7872
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Turbulent boundary layers over nonstationary plane boundaries (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Methods of predicting integral parameters and skin friction coefficients of turbulent boundary layers developing over moving ground planes were evaluated. The three methods evaluated were: relative integral parameter method; relative power law method; and modified law of the wall method.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-74091 , L-11465
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Wind-tunnel investigation of an externally blown flap STOL transport model including and investigation of wall effects (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wind-tunnel investigation was conducted in the Langley V/STOL tunnel and in a scaled version of the Ames 40- by 80-foot tunnel test section installed as a liner in the Langley V/STOL tunnel to determine the effect of test-section size on aerodynamic characteristics of the model. The model investigated was a swept-wing, jet-powered, externally blown flap (EBF) STOL transport configuration with a leading-edge slat and triple-slotted flaps. The model was an 0.1645-scale model of a 11.58-meter (38.0-ft) span model designed for tests in a 40- by 80-foot tunnel. The data compare the aerodynamic characteristics of the model with and without the tunnel liner installed. Data are presented as a function of thrust coefficient over an angle-of-attack range of 0 deg to 25 deg. A thrust-coefficient range up to approximately 4.0 was simulated, most ot the tests being conducted at a free-stream dynamic pressure of 814 Newtons/sq m (17 lb sq ft). The data are presented with a minimum of analysis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3009
    Format: application/pdf
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  • 10
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    Longitudinal aerodynamics of a low-wing lift-fan transport including hover characteristics in and out of ground effect (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wind-tunnel investigation was conducted in the Langley V/STOL tunnel to determine the longitudinal aerodynamic characteristics of a six-fan, tip-driven (remote) lift-fan VTOL transport throughout transition. The large midspan lift-fan pods and cruise fans were removed to determine their influence on the stability and control of the configuration. Data were obtained in the hovering mode for ranges of model height above ground. The data are presented without analysis or discussion.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-72670
    Format: application/pdf
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