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    Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. volume 12. Vertical Tail Net Chordwise Pressure Distributions and Isobars

    M. E. Manro / J. P. Moulijn / J. D. Knittel | NTIS | 1972
    Schlagwörter: Supersonic aircraft , Wind tunnel models , Supersonic flow , Supersonic transports

    Pressure Distributions on a Delta Wing Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. Volume 11. Vertical tail section and Total Surface Aerodynamic Coefficients, Chordwise Pressure Distributions

    M. E. Manro / J. P. Moulijn / J. D. Knittel | NTIS | 1972
    Schlagwörter: Supersonic aircraft , Supersonic flow , Wind tunnel models , Supersonic transports

    Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. Volume 9. Horizontal Stabilzer Section and Total Surface Aerodynamic Coefficients, Chordwise Pressure Distributions

    M. E. Manro / J. P. Moulijn / J. D. Knittel | NTIS | 1972
    Schlagwörter: Supersonic aircraft , Supersonic flow , Wind tunnel models , Supersonic transports

    Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. Volume 6. Wing Chordwise Pressure Distribution - Nacelles Off

    M. E. Manro / J. P. Moulijn / J. D. Knittel | NTIS | 1972
    Schlagwörter: Supersonic aircraft , Supersonic flow , Wind tunnel models , Supersonic transports

    Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. Volume 3. Wing Section and Total Surface Aerodynamic Coefficients

    M. E. Manro / J. P. Moulijn / J. D. Knittel | NTIS | 1972
    Schlagwörter: Supersonic aircraft , Wind tunnel models , Supersonic flow , Supersonic transports

    Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. Volume 4. Wing Chordwise Pressure Distributions - Nacelles on

    M. E. Manro / J. P. Moulijn / J. D. Knittel | NTIS | 1972
    Schlagwörter: Supersonic aircraft , Wind tunnel models , Supersonic flow , Supersonic transports

    Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9 Volume 8. Wing Chordwise Pressure Distributions, Effects of: Nacelles, Flaps, Spoilers, Sideslip, and Reynolds Number. Part 1

    M. E. Manro / J. P. Moulijn / J. D. Knittel | NTIS | 1972
    Schlagwörter: Supersonic aircraft , Supersonic flow , Wind tunnel models , Supersonic transports

    Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. Volume 1. Summary Report

    M. E. Manro / J. P. Moulijn / J. D. Knittel | NTIS | 1972
    Schlagwörter: Supersonic aircraft , Wind tunnel models , Supersonic flow , Supersonic transports

    Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination At Mach Numbers from 0.3 to 2.9. Volume 7. Wing Net Chordwise Pressure Distributions and Isobars - Nacelles Off

    M. E. Manro / J. P. Moulijn / J. D. Knittel | NTIS | 1972
    Schlagwörter: Supersonic aircraft , Wind tunnel models , Supersonic transports

    Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. Volume 2. Comparisons of Theory and Experiment

    M. E. Manro / J. P. Moulijn / J. D. Knittel | NTIS | 1972
    Schlagwörter: Supersonic aircraft , Wind tunnel models , Supersonic flow , Supersonic transports

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