Analysis of the performance of a highly loaded 12-inch VTOL Z-ax1s, fan-in-wing model at zero forward speed

From National Research Council Canada

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DOI	Resolve DOI: https://doi.org/10.4224/40003693
Author	Search for: Schaub, U. W.¹; Search for: Bassett, R. W.¹
Affiliation	National Research Council Canada. Division of Mechanical Engineering
Format	Text, Technical Report
Physical description	50 p.
Abstract	The performance of a highly loaded VTOL fan-in-wing model was examined under static ambient conditions. The experiments revealed that the fan was capable of delivering a maximum disk loading of 465 p.s.f. at an over-all efficiency of only 65 percent. At somewhat lower loadings, more efficient operation was possible, typically: 72 percent at 445 p.s.f. At tip speeds in excess of 785 f.p.s. (15,000 r.p.m.) the rotor was subjected to transonic flow conditions and, being designed for subsonic operation, suffered large losses. The thrust decreased gradually without evidence of an abrupt stall. It was observed that the inlet surface pressure force was nearly equal to half the thrust in the tip speed range 471 f.p.s. to 680 f.p.s. (i.e. 9,000 to 13,000 r.p.m.), while at higher speeds it was greater.
Publication date	1965-09
Publisher	National Research Council Canada
Series	Aeronautical Report (National Research Council Canada. Division of Mechanical Engineering. Engine Laboratory), no. LR-439 (September 1965).
Language	English
Peer reviewed	No
NRC number	NRCC-0008829 NRC-8829
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Record identifier	0b5cb908-8c73-43b0-8339-0c161c42e5d9
Record created	2025-09-05
Record modified	2025-11-03

Date modified:: 2026-01-15