A Correlation Study of The Wing-Body Interference Factor for High Angles

Krishnamurthy, M and Venugopal, S (1991) A Correlation Study of The Wing-Body Interference Factor for High Angles. Technical Report. NAL, Bangalore.

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    Abstract

    In This Study A Method Is Presented For Estimating The Wingbvdy Interference Factor, K For Slender Configurations Through Subsonic,Transonic And Supersonic W Speed Ranges . This Method Can Predict The Interference Factor Upto Angles Of Attack Of About 30° . The Method Makes Use Of A Limited Experimental Data Base For Kw Available In 2the 2literature . The Data Has Been Correlated Against A Single Parameter 1-M Sincc Which Accounts For Free Stream Mach Number As Well As Angle Of Attack . Least Square Polynomial Curve Fits Have Been Used For The Correlated Data For Various Wing Aspect Ratios And Tapers . Three Way Linear Interpolation Has Been Adopted To Estimate The K From The Curve Fitted Data Against Aspect Ratio, Taper Ratio And The Ratio Of Body Radius To Fin Semispan (Inclusive Of Body) . For M = .8, The Data Does Not Correlate With This Parameter And Hence Direct Interpolation Of K For This Mach Number Has Been Adopted . The Factor K Obtained By This Method Accounts For The Effects Due To Loss Of Upwash As Well As Decrease In Dynamic Pressure At Higher Angles Of Attack And Mach Numbers,And Is Predicted Within ±10 Percent Accuracy . The Method Is However Limited To Wings Of Low Aspect Ratio ( E-4-0 , Typical Of Fins Used In Conventional Missiles) With Zero Or Small Trailing Edge Sweep Angles .

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Wing-Body Interference Factor; High Angle of Attack; Interference Lift.
    Subjects: AERONAUTICS > Aeronautics (General)
    Division/Department: Centre for Civil Aircraft Design and Development, Centre for Civil Aircraft Design and Development
    Depositing User: M/S ICAST NAL
    Date Deposited: 24 Sep 2012 10:13
    Last Modified: 24 Sep 2012 10:13
    URI: http://nal-ir.nal.res.in/id/eprint/10934

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