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  • 11
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    Use of Two-dimensional Data in Estimating Loads on a 45 Degree Sweptback Wing with Slats and Partial-span Flaps (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-3040
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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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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    NASA TECHNICAL REPORTS
  • 13
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    Wind-Tunnel Investigation of the Low-Speed Static Longitudinal Characteristics of the Republic RF-84F Airplane (1952)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Tests in the Ames 40- by 80-foot wind tunnel of the static longitudinal characteristics of the Republic RF-84F were made to determine both the origin and a suitable remedy for a pitch up tendency of the airplane encountered at moderate lift coefficients. The results indicated that the pitch-up at moderate lift coefficients was caused by an abrupt change in downwash at the tail which in turn was traceable presumably to flow conditions associated with the inlet-to-wing leading-edge discontinuity.. Attempts to eliminate this pitch-up characteristic with various fairings and stall-control devices. were not wholly successful. The investigation revealed, however, that significant gains in the performance of the airplane could be achieved in the upper lift range.. Three different configurations consisting of a partial-span modified leading edge combined with one or with two-fenees or a leading-edge extension each delayed the onset of separation to higher lift coefficients and provided large improvements in the stability of the airplane in the upper lift range.
    Keywords: Aerodynamics
    Type: NACA-RM-SA52H04
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 14
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    An Investigation of a Full-Scale Model of the Republic XF-91 Airplane in the Ames 40- By 80-Foot Wind Tunnel: Pressure Data (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Wind-tunnel tests of a full-scale model of the Republic XF-91 airplane were conducted to determine the distribution of pressure over the external wing fuel tank installation and over the vee tail and ventral fin. The data were obtained for a range of angles of attack and sideslip and elerudder deflection angles; the presentation is in tabular form.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SA9C25
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 15
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    An Investigation of the Wing and the Wing-Fuselage Combination of a Full-Scale Model of the Republic XP-91 Airplane in the Ames 40-by 80-Foot Wing Tunnel (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Wind-tunnel tests of a full-scale model of the Republic XP-91 airplane were conducted to determine the longitudinal and lateral characteristics of the wing alone and the wing-fuselage combination, the characteristics of the aileron, and the damping in roll af the wing alone. Various high-lift devices were investigated including trailing-edge split flaps and partial- and full-span leading-edge slats and Krueger-type nose flaps. Results of this investigation showed that a very significant gain in maximum lift could be achieved through use of the proper leading-edge device, The maximum lift coefficient of the model with split flaps and the original partial-span straight slats was only 1.2; whereas a value of approximately 1.8 was obtained by drooping the slat and extending it full span, Improvement in maximum lift of approximately the same amount resulted when a full-span nose flap was substituted for the original partial-span slat.
    Keywords: Aerodynamics
    Type: NACA-RM-SA8F09
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 16
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    Force Tests of the Boeing XB-47 Full-Scale Empennage in the Ames 40- by 80-Foot Wind Tunnel (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A wind-tunnel investigation of the Boeing XB-47 full-scale empennage was conducted to provide, prior to flight tests, data required on the effectiveness of the elevator and rudder. The XB-47 airplane is a jet-propelled medium bomber having wing and tail surfaces swept back 35 degrees. The investigation included tests of the effectiveness of the elevator with normal straight sides, with a buldged trailing edge, and with a modified hinge-line gap and tests of the effectiveness of the rudder with a normal straight-sided tab and with a bulged tab.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-A7H12
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 17
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    An Investigation of the McDonnell XP-85 Airplane in the Ames 40- by 80-foot Wind Tunnel. Force and Moment Tests (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Wind-tunnel tests of the McDonnell XP-85 airplane were conducted to determine its longitudinal, lateral, and directional stability and the characteristics of the aileron, the ruddervator, the leading-edge droop nose flap, and the stall control vanes. The directional stability of the airplane with numerous skyhook modifications and with a ventral fin was also investigated. The results of the tests showed that the effectiveness of the droop nose flaps and the stall control vanes was negligible with regard to either the maximum lift or longitudinal stability of the airplane. Contrary to any previous small-scale results, extension of the skyhook caused a 75-percent reduction in the directional stability of the airplane for both low and high values of lift coefficient. The simplest solution to the problem short of a major redesign of the skyhook appears to be the adoption of a ventral fin.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SA8I23
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 18
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    Investigation of the Effect of Tip Tanks on the Wing Loading of a Republic F-84 Airplane in the Ames 40- by 80-foot Wind Tunnel (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Wind-tunnel tests at low Mach number of a Republic F-84C airplane were conducted to determine by pressure-distribution measurements the air loads on wing-tip tanks and the change in wing load distribution due to the presence of tip tanks. Measurements of the aeroelastic twist of the wing were also obtained. Results are presented in the form of loading coefficient, center-of- pressure location, pitching-moment coefficient, aerodynamic-center location, and aeroelastic twist. The investigation revealed that the redistributions in loading brought about by either the tip tanks or elastic deformation of the wing were relatively small when compared with the chnnges in loading normally associated with the deflection of an aileron.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SA9B02
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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