Publication Date:
2019-08-15
Description:
An elementary calculation inspired by the classic treatment for the steady state permits the determination of the induced velocity and the overall lift of the rotor as a function of the collective pitch for all values of the advance per turn. The nature of the lift response is shown to be essentially a function of the rate of pitch change.
Keywords:
Aircraft Design, Testing and Performance
Type:
NASA-TT-F-18
,
L-455
,
Comptes Rendus; 247; 9; 738-741
Format:
text
Permalink