Keywords: Performance, Rotor load, Lynx helicopter

Abstract: This report presents the results of a series of flight tests on the Lynx XZ170 helicopter with rectangular blades. The test objectives were to explore the flight envelope and to measure the performance and structural loads of the Lynx main-rotor system. The tests were conducted as part of the British Experimental Rotor Programme (BERP) under a contract with the Ministry of Defense in England. Data were acquired for steady-level flights at five weight coefficients. Some flight conditions were tested at beyond the retreating-blade stall boundary, which was defined by a predetermined limit on the pitch-link vibratory load. In addition to documenting the flight conditions and data, this report describes the aircraft, particularly the rotor system, in detail.

The following errata were found in NASA TM 104000.

1. Page 13, Table 8. Elastic-center offset should be changed to Tension-center offset.

2. Page 14, Table 8b. Blade stiffness. The radial stiffness distribution should be replaced with the following:

Radial Station	Radial Stiffness
r/R	EA, lb
0.0000	1.0000E+08
0.2141	1.0000E+08
0.2828	4.5000E+07
0.3968	3.1306E+07
0.4500	3.0554E+07
0.5000	2.9801E+07
0.5500	2.9047E+07
0.5992	2.8296E+07
0.5992	2.7422E+07
0.6500	2.6784E+07
0.6786	2.6400E+07
0.6786	2.5750E+07
0.7000	2.5534E+07
0.7500	2.5008E+07
0.7579	2.4926E+07
0.7579	2.4624E+07
0.8000	2.4235E+07
0.8500	2.3775E+07
0.9000	2.3314E+07
0.9500	2.4470E+07
0.9921	2.4096E+07

3. Page 48. Appendix B. The true air speed for Flight 503 condition C should be 87.2 knots.

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Last Modified: Friday, 21-Dec-2007 14:11:52 PST