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  • 1
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    Results of a brief flight investigation of a coin-type STOL aircraft (1966)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Performance characteristics and handling qualities of current generation counter-insurgency aircraft in low speed STOL flight regime
    Keywords: AIRCRAFT
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Interdependence of parameters important to the design of subsonic canard-configured aircraft (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An analysis is made of the interrelationship of the longitudinal parameters important to the aerodynamic design of an efficient canard or tandem wing configuration. It is shown that theoretical configuration span efficiencies substantially greater than one are feasible with the proper choice of parameters. This improvement can translate into significantly increased lift/drag ratios assuming fixed spans. The Prandtl-Munk relationship for induced drag is used as a convenient qualitative guide, with stability and trim criteria superimposed. An 'aspect-ratio ratio' parameter is introduced to aid in optimizing a configuration longitudinally. It is shown that a canard/wing 'aspect-ratio ratio' of approximately 3/2 to 2 is necessary to achieve peak span efficiency for a given span ratio and gap, assuming representative parameters.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 850865
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Flight tests of a one-man helicopter and com- parison of its handling qualities with those of larger vtol aircraft (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-24
    Description: Flight tests of one-man helicopter and comparison of handling qualities
    Keywords: AIRCRAFT
    Type: NASA-TN-D-3060
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Large-scale wind-tunnel tests of inverting flaps on a STOL utility aircraft model (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A unique inverting flap system was investigated on a large scale deflected slipstream model in the Ames 40 by 80 foot wind tunnel. The subject tests utilized 33% chord double-slotted flaps on a low aspect ratio wing that was fully immersed in the propeller slipstream. Evaluation of the flap effectiveness is aided by comparisons with the results of tests of other flap systems on the same twin propeller, twin tail boom STOL utility aircraft mode. No extreme or abrupt force or moment increments were encountered when the flaps were deflected through a wide range, corresponding to the complete retraction/extension spectrum. The lift and descent capability of the inverting flaps compared very favorably with that of the other flap systems that have been tested on this model, including some with much greater mechanical complexity. As expected, the flaps caused large nose down, pitching moment increments at the high lift settings; however, the trimmed characteristics are still competitive with those obtained from the more complicated flap systems. It is believed that these flaps may have promising potential application to the design of relatively simple STOL utility aircraft with improved performance capabilities. In addition, they may merit consideration as retrofits to existing aircraft with less effective flap systems.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1696 , AVRADCOM-TM-80-A-1 , A-7061
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Large-scale wind-tunnel tests of three vehicles incorporating a deployable rigid wing (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind-tunnel tests were performed to determine the aerodynamic characteristics of three full-scale vehicles incorporating a unique folding metal wing, and to investigate its deployment characteristics. The static aerodynamic data are presented without analysis.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA-TM-X-62405 , A-5854
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Results of a brief flight investigation of a coin-type STOL aircraft (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flight tests of coin-type STOL aircraft
    Keywords: AIRCRAFT
    Type: NASA-TN-D-4141
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Reduction of Stall-Spin Entry Tendencies Through Wing Aerodynamic Design (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Results of recent wind tunnel tests and analyses are described which are aimed at helping to prevent spin entry after a stall by modifications to the aircraft wing. Simple add-on devices were utilized which modify the shape of the lift curve after stall, making it essentially flat to 30- 40 degree angle of attack. It is hypothesized that his will greatly reduce the danger of spin entry. Further research will be aimed at laying a firmer theoretical and analytical basis for the approach and at incorporating the complete full scale airplane and its dynamics into the problem.
    Keywords: Aircraft Design, Testing and Performance
    Type: Rept-760481 , NASA-TM-208064 , Business Aircraft Meeting; Apr 06, 1976 - Apr 09, 1976; Wichita, KS; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    A method for localizing wing flow separation at stall to alleviate spin entry tendencies (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A wing leading-edge modification has been developed, applicable at present to single-engine light aircraft, which produces stabilizing vortices at stall and beyond. These vortices have the effect of fixing the stall pattern of the wing such that the various portions of the wing upper surface stall nearly symmetrically. The lift coefficient produced is essentially constant to very high angles of attack above the stall angle of the unmodified wing. It is hypothesized that these characteristics will help prevent inadvertent spin entry after a stall. Results are presented from recent large-scale wind-tunnel tests of a complete light aircraft, both with and without the modification.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-1476 , Aircraft Systems and Technology Conference; Aug 21, 1978 - Aug 23, 1978; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    An investigation of a direct side-force maneuvering system on a deflected jet VTOL aircraft (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Direct side-force maneuvering system on deflected X-14A jet VTOL aircraft without changing bank angle
    Keywords: AIRCRAFT
    Type: NASA-TN-D-5175
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Alleviation of Spin-Entry Tendencies through Localization of Wing-Flow Separation (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Studies have been made on several wing leading-edge modifications applicable at present to single-engine light aircraft, which produce stabilizing vortices at stall and beyond. These vortices have the effect of fixing the stall pattern of the wing such that the various portions of the wing upper surface stall nearly symmetrically. The lift coefficient produced is maintained at a high level to angles of attack significantly above the stall angle of the unmodified wing, and the divergence in roll usually is reduced to a controllable level. It is hypothesized that these characteristics will help prevent inadvertent spin entry after a stall. Results are presented from recent large-scale wind-tunnel tests of a typical light aircraft, both with and without the modifications. The data indicate (hot the static stall and poststall characteristics of this aircraft, in a typical landing-approach condition, are noticeably improved when it suitable leading-edge modification is employed; and also that no appreciable aerodynamic penalties are evident in the normal flight envelope.
    Keywords: Aerodynamics
    Type: NASA/TM-81-207529 , NAS 1.15:207529 , AIAA Paper 78-1476R , Journal of Aircraft; 18; 2; 69-75|Aircraft Systems and Technology Conference; Aug 21, 1978 - Aug 23, 1978; Los Angeles, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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