NASA Pathfinder II Research Fighter Model

Similar to the Pathfinder I configurations for subsonic transports, a Pathfinder II series of relevant, yet generic fighter configurations were defined collaboratively with industry during the 1980s. The configurations associated with General Dynamics and McDonnell Douglas were tested. The General Dynamics configuration included a conventional forebody, an advanced moderately swept wing, and the capability for parametric variation of leading- and trailing-edge devices; test conditions included Mach numbers from 0.4 to 0.95, angles of attack up to 33 deg, and a maximum Reynolds number of 66 million.

The McDonnell Douglas configuration included a conventional forebody, an advanced wing, and a variety of empennage components enabling investigation of singe- and twin-tail configurations.
Test conditions included Mach numbers of 0.6, 0.8, and 0.9 at angles of attack up to 18 deg with chord Reynolds numbers up to 61 million.

Additionally, the McDonnell Douglas Pathfinder II configuration was tested at sideslip angles up to 10 deg. Aside from the HSR Reference H configuration, this configuration has the most extensive lateral/directional database at high Reynolds numbers.

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MDC Pathfinder II
This configuration was developed jointly with McDonnell Douglas Corporation (St. Louis, MO.), now Boeing. The model had a conventional (smooth-sided) forebody, an advanced cambered transonic wing, and a variety of empennage components. This model was also designed for cryogenic testing.
Tests were performed in the NTF in the fall of 1995. The purpose of the test was to provide a full-scale Reynolds number data base and Reynolds number increments applicable to thinwing, fighter-type configurations. Data were obtained from M=0.60 to 0.90 and Rnc from 5 to 61 million (flight) at angles of attack from -2° to 18°.

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