This volume contains six appendixes which augment the blast and thermal analysis presented in Volume II. In the first, there is a detailed description of the general F-106A mission profile, including scramble, takeoff, attack, return to base, etc. The second contains a description of the effects that partial degradation or complete loss of individual secondary structural elements would have upon overall performance capabilities of the F-106A aircraft. Appendix III includes presentations of the integral equation and F-106A fuselage cross-sectional data which were used to evaluate secondary structure preloading effects at supersonic speeds prior to thermal and overpressure analyses. Appendix IV contains the separated form of the kernel function that was used in the subsonic aerodynamic loading analysis. Appendix V contains the F-106A dynamic response models, i.e., mass matrices, stiffness matrices, natural frequencies; and mode shapes, which were used in the gust analysis. The last contains influence coefficient data used to calculate aerodynamic pressure distributions for the subsonic wing, subsonic fin, supersonic wing, and supersonic fin.


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    F-106A Environmental Vibration

    G. L. Getline | NTIS | 1960




    Structural Test Program F-106A Airplane

    S. Lustig / D. W. Jackson / F. E. Hussong | NTIS | 1960