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  • 1
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    Experimental investigation of wing installation effects on a two-dimensional mixer/ejector nozzle for supersonic transport aircraft (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experimental results from a wind tunnel test conducted to investigate propulsion/airframe integration (PAI) effects are presented. The objectives of the test were to examine rough order-of-magnitude changes in the acoustic characteristics of a mixer/ejector nozzle due to the presence of a wing and to obtain limited wing and nozzle flow-field measurements. A simple representative supersonic transport wing planform, with deflecting flaps, was installed above a two-dimensional mixer/ejector nozzle that was supplied with high-pressure heated air. Various configurations and wing positions with respect to the nozzle were studied. Because of hardware problems, no acoustics and only a limited set of flow-field data were obtained. For most hardware configurations tested, no significant propulsion/airframe integration effects were identified. Significant effects were seen for extreme flap deflections. The combination of the exploratory nature of the test and the limited flow-field instrumentation made it impossible to identify definitive propulsion/airframe integration effects.
    Keywords: AERODYNAMICS
    Type: NASA-TM-105713 , E-7107 , NAS 1.15:105713
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Application of the ONERA model of dynamic stall (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A semiempirical model to predict the unsteady loads on an airfoil that is experiencing dynamic stall, is investigated. The mathematical model is described from an engineering point of view, demonstrates the procedure for obtaining various empirical parameters, and compares the loads predicted by the model with those obtained in the experiment. It is found that the procedure is straightforward, and the final calculations are in qualitative agreement with the experimental results. Comparisons between calculations and measurements also indicate that a decrease in accuracy results when the values of both the reduced frequency and the amplitude of oscillation are large. Potential quantitative improvements in the accuracy of the calculations are discussed for accounting of both the hysteresis in the static data and the effects of stall delay in the governing equations.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2399 , A-9824 , AVSCOM-TR-84-A-3 , NAS 1.60:2399 , AD-A159502
    Format: application/pdf
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  • 3
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    An Experimental Study of Dynamic Stall on Advanced Airfoil Sections (1982)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Detailed unsteady boundary layer measurements are presented for eight airfoils oscillated in pitch through the dynamic stall regime. The present report (the third of three volumes) describes the techniques developed for analysis and evaluation of the hot film and hot wire signals, offers some interpretation of the results, and tabulates all the cases in which flow reversal has been recorded.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84245-Vol-3 , A-8938 , NAS 1.15:84245-VOL-3 , USAAVRADCOM-TR-82-A-8-Vol-3
    Format: application/pdf
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  • 4
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    Angle of attack estimation using an inertial reference platform (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper presents the mathematical development and flight test results of an angle of attack estimation system based on inertial navigation system inputs. The estimator uses these inputs to determine the coefficient of lift required at any instant inflight. Angle of attack is then modeled through a regression analysis based on coefficient of lift, altitude and Mach. Overall correlation of the estimator as tested was generally within 0.5 degrees through 17 degrees angle of attack on an F-15A aircraft. A robustness analysis indicates that the system can be used adequately in maneuvering flight.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-4351 , AIAA Atmospheric Flight Mechanics Conference; Aug 15, 1988 - Aug 17, 1988; Minneapolis, MN; United States
    Format: text
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