AERODYNAMIC LOADS AT MACH NUMBERS FROM 0.70 TO 2.22 ON AN AIRPLANE MODEL HAVING A WING AND CANARD OF TRIANGULAR PLAN FORM AND EITHER SINGLE OR TWIN VERTICAL TAILS

Results of an investigation of the aerodynamic loads on a canard airplane model are presented without detailed analysis for the Mach number range of 0.70 to 2.22. The model consisted of a triangular wing and canard of aspect ratio 2 mounted on a Sears-Haack body of fineness ratio 12.5 and either a s...

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Bibliographische Detailangaben

Hauptverfasser:	PETERSON,VICTOR L, MENEES,GENE P
Format:	Report
Sprache:	eng
Schlagworte:	AERODYNAMIC CHARACTERISTICS AERODYNAMIC CONFIGURATIONS CANARD CONFIGURATIONS DELTA WINGS DRAG FINS LIFT LOAD DISTRIBUTION MODEL TESTS MOMENTS PRESSURE SUPERSONIC AIRCRAFT SUPERSONIC FLOW TRANSONIC CHARACTERISTICS WING BODY CONFIGURATIONS
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