HIGH LIFT SURFACE; DESIGN PROCEDURES; EXPERIMENTAL VERIFICATION. VOLUME III. WIND TUNNEL TESTS.
NORAIR DIV NORTHROP CORP HAWTHORNE CALIF
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The volume presents the results of a low speed wind tunnel test of four half-span wing models. The primary objective of the test was to obtain experimental data on wings developed by a high lift surface computer program. Two wings designed by this method, one high and one low lift, were tested. A secondary objective of the test was to determine the feasibility of simulating the high lift wing by flaps on the low lift wing and, conversely, simulating the low lift wing by flaps on the high lift wing. This involved an additional two models for a total of four. Author