Tests made to determine range of advance ratio and blade angle in which tunnel wall corrections as developed for wings might be used for rotors; lift and drag coefficient data were corrected by standard wing-type wall corrections using full span of rotor as vortex span and area of rotor disk as wing area; data compared to determine at which blade angles and advance ratios corrections gave satisfactory agreement.
Experimental investigation of effect of wind tunnel walls on aerodynamic performance of helicopter rotor
NASA -- Tech Note
1960
35 pages
Article (Journal)
English
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Investigation of experimental aerodynamic loading on model helicopter rotor blade
Engineering Index Backfile | 1953
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