The design of inlets and nozzles and their interactions with the airframe may account for a large percentage of the total drag of modern high performance aircraft. This paper contains an overview of an inlet/airframe interactions program, the flight tests of which were conduced at the NASA Dryden Flight Research Center.Inlet drag and interaction data from a 7.5-percent-cale wind tunnel model are compared with data from an F-15 airplane, modified to match the model. Data are presented for Mach numbers of 0.6, 0.9, and 1.2 with varying angles of attack and engine mass flows. Limited comparisons of flight and wind tunnel data for upper and lower cowl pressure coefficients are presented and show good agreement in most areas. The inlet drag and lift from model and aircraf data were derived by pressure integration. For a few selected conditions at all three Mach numbers and an angle of attack of 0deg, Hie flight and wind tunnel pressure-integrated drag were in close agreement. Flight-measured inlet lift was somwhat lower than that measured in the wind tunnel. Differences between pressure-integrated and force balance inlet drag at a Mach number of 0.6 are discussed. (Se.)
Preliminary flight and wind tunnel comparisons of the inlet/airframe interaction of the F-15 airplane
Erste Ergebnisse von Flug- und Windkanalmessungen der Wechselwirkungen zwischen Triebwerkseinlass und Baukoerper des Flugzeugs F-15
AIAA-Papers ; 1-17
1979
17 Seiten, 22 Bilder, 1 Tabelle, 8 Quellen
Aufsatz (Konferenz)
Englisch
AIAA | 1970
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