Investigation was conducted in Langley 4- by 4-ft supersonic pressure tunnel; 5 models were tested with fineness ratios varying from 19.1 to 14.8; tests covered angle-of-attack range up to about 28° for complete configuration and various combinations of component parts.
Aerodynamic characteristics in pitch of series of cruciform-wing missiles with canard controls at mach number of 2.01
NASA -- Tech Note
1961
40 pages
Report
Englisch
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