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  • 1
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    Experimental Results for a Flapped Natural-laminar-flow Airfoil with High Lift/drag Ratio (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experimental results have been obtained for a flapped natural-laminar-flow airfoil, NLF(1)-0414F, in the Langley Low-Turbulence Pressure Tunnel. The tests were conducted over a Mach number range from 0.05 to 0.40 and a chord Reynolds number range from about 3.0 x 10(6) to 22.0 x 10(6). The airfoil was designed for 0.70 chord laminar flow on both surfaces at a lift coefficient of 0.40, a Reynolds number of 10.0 x 10(6), and a Mach number of 0.40. A 0.125 chord simple flap was incorporated in the design to increase the low-drag, lift-coefficient range. Results were also obtained for a 0.20 chord split-flap deflected 60 deg.
    Keywords: AERODYNAMICS
    Type: NASA-TM-85788 , NAS 1.15:85788
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Recent modifications and calibration of the Langley low-turbulence pressure tunnel (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Modifications to the Langley Low-Turbulence Pressure Tunnel are presented and a calibration of the mean flow parameters in the test section is provided. Also included are the operational capability of the tunnel and typical test results for both single-element and multi-element airfoils. Modifications to the facility consisted of the following: replacement of the original cooling coils and antiturbulence screens and addition of a tunnel-shell heating system, a two dimensional model-support and force-balance system, a sidewall boundary layer control system, a remote-controlled survey apparatus, and a new data acquisition system. A calibration of the mean flow parameters in the test section was conducted over the complete operational range of the tunnel. The calibration included dynamic-pressure measurements, Mach number distributions, flow-angularity measurements, boundary-layer characteristics, and total-pressure profiles. In addition, test-section turbulence measurements made after the tunnel modifications have been included with these calibration data to show a comparison of existing turbulence levels with data obtained for the facility in 1941 with the original screen installation.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2328 , L-15728 , NAS 1.60:2328
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Low-speed aerodynamic characteristics of a 13 percent thick medium speed airfoil designed for general aviation applications (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel tests were conducted to determine the low speed, two dimensional aerodynamic characteristics of a 13percent thick medium speed airfoil designed for general aviation applications. The results were compared with data for the 13 percent thick low speed airfoil. The tests were conducted over a Mach number range from 0.10 to 0.32, a chord Reynolds number range from 2.0 x 10 to the 6th power to 12.0 x 10 to the 6th power, and an angle of attack frange from about -8 deg to 10 deg. The objective of retaining good high-lift low speed characteristics for an airfoil designed to have good medium speed cruise performance was achieved.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1498 , L-12976
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    An Exploratory Investigation of the Effects of a Thin Plastic Film Cover on the Profile Drag of an Aircraft Wing Panel (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Exploratory wind tunnel tests were conducted on a large chord aircraft wing panel to evaluate the potential for drag reduction resulting from the application of a thin plastic film cover. The tests were conducted at a Mach number of 0.15 over a Reynolds number range from about 7 x 10 to the 6th power to 63 x 10 to the 6th power.
    Keywords: AERODYNAMICS
    Type: NASA-TM-74073
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Low speed aerodynamic characteristics of a 17 percent thick airfoil section designed for general aviation applications (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind-tunnel tests have been conducted to determine the low-speed two-dimensional aerodynamic characteristics of a 17-percent-thick airfoil designed for general aviation applications (GA(W)-1). The results were compared with predictions based on a theoretical method for calculating the viscous flow about the airfoil. The tests were conducted over a Mach number range from 0.10 to 0.28. Reynolds numbers based on airfoil chord varied from 2.0 million to 20.0 million. Maximum section lift coefficients greater than 2.0 were obtained and section lift-drag ratio at a lift coefficient of 1.0 (climb condition) varied from about 65 to 85 as the Reynolds number increased from about 2.0 million to 6.0 million.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7428 , L-9132
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Effects of thickness on the aerodynamic characteristics of an initial low-speed family of airfoils for general aviation applications (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind tunnel tests were conducted to determine the effects of airfoil thickness-ratio on the low speed aerodynamic characteristics of an initial family of airfoils. The results were compared with theoretical predictions obtained from a subsonic viscous method. The tests were conducted over a Mach number range from 0.10 to 0.28. Chord Reynolds numbers varied from about 2.0 x 1 million to 9.0 x 1 million.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-72843
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Low-speed aerodynamic characteristics of airfoil sections with rounded trailing edges in forward and reverse flow (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Low-speed wind-tunnel tests were conducted to determine the two-dimensional aerodynamic characteristics of 6-, 12-, and 18-percent-thick airfoil sections with rounded trailing edges in both forward and reverse flow. The shapes incorporated camber with both the leading and trailing edges rounded to provide reasonable aerodynamic performance with either edge directed toward the free-stream flow. The tests were conducted with the airfoils in both normal and reverse orientations relative to the free stream. The Mach number was varied from 0.16 to 0.36 and the angle of attack was varied from minus 10 to 24 million. Reynolds number, based on the airfoil chord, was varied from about 1.0 to 12.0 million.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3060 , L-9327
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Low-speed aerodynamic characteristics of a 13-percent-thick airfoil section designed for general aviation applications (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind-tunnel tests were conducted to determine the low-speed section characteristics of a 13 percent-thick airfoil designed for general aviation applications. The results were compared with NACA 12 percent-thick sections and with the 17 percent-thick NASA airfoil. The tests were conducted ovar a Mach number range from 0.10 to 0.35. Chord Reynolds numbers varied from about 2,000,000 to 9,000,000.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-72697
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind-tunnel tests were conducted in the Langley low-turbulence pressure tunnel to evaluate the effects on performance of modifying a 17-percent-thick low-speed airfoil. The airfoil contour was altered to reduce the pitching-moment coefficient by increasing the forward loading and to increase the climb lift-drag ratio by decreasing the aft upper surface pressure gradient. The tests were conducted over a Mach number range from 0.07 to 0.32, a chord Reynolds number range 1.0 x 10 to the 6th power to 12.0 x 10 to the 6th power, and an angle-of-attack range from about -10 deg to 20 deg.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1919 , L-14666
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Low-speed wind tunnel results for a modified 13-percent-thick airfoil (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind-tunnel tests were conducted to evaluate the effects on performance of modifying a 13-percent-thick low-speed airfoil. The airfoil contour was altered to reduce the aft upper surface pressure gradient and hence delay boundary layer separation at typical lift coefficients for light general aviation airplanes. The tests were conducted at a Mach number of 0.15 or less over a Reynolds number range from about 1,000,000 to 9,000,000.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-74018
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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