HIGH LIFT SURFACE DESIGN PROCEDURES. EXPERIMENTAL VERIFICATION. VOLUME I. SUMMARY AND EVALUATION.
NORAIR DIV NORTHROP CORP HAWTHORNE CALIF
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The main purpose of this work was to determine the performance gains of wings designed for optimized high lift by a new design procedure based on lifting surface theory for wings in steady subsonic flow. The theoretically predicted performance of the wings is compared with the wind tunnel test results and comparisons are made between these results and the performance of wings designed by other methods. The results indicated that the optimized high lift wing had greater lift to drag ratios in the high lift range of operation than cruise wings using high lift devices. The optimized high lift wing exhibited results comparable to the cruise wing when it was flapped to approximate the mean surface slope distribution of the cruise wing. The results also verified the computer programs and demonstrated that the new design procedure can be used for a wide range of lift coefficients. It is concluded that this new design procedure is superior to the old cut and dry methods. Also, if high lift is of prime importance in a mission, the penalties are less if the wing is designed for optimized high lift and flapped for low lift. Author