C123k Limited Performance and Stability and Control Tests

C123k Limited Performance and Stability and Control Tests

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The purpose of this C-123K test program was to obtain quantitative performance data and to qualitatively evaluate stability and control characteristics. The test aircraft was a C-123B modified to the C-123K configuration by the installation of a pylon-mounted J85-GE-17 engine under each wing, an improved modulated antiskid brake system, and a Monitair angle of attack/stall warning system. Test results indicated a substantial improvement in takeoff, climb and landing performance over the C-123B aircraft. Addition of the jet engines resulted in a drag increase corresponding to a loss of approximately 7 KIAS for the same power setting at an aircraft gross weight of 50, 000 pounds and sea level standard day conditions. In general, stability and control characteristics were similar to those of the C-123B aircraft. The air minimum directional control speeds were below stalling speed with one jet engine inoperative and the remaining jet engine at maximum power. With one reciprocating engine inoperative, the minimum control speed was 8 knots faster than that shown in the Flight Manual. The airspeed calibration obtained during this evaluation was significantly different from that presented in the Flight Manual.The airspeed calibration obtained during this evaluation was significantly different from that presented in the Flight Manual.


Title:C123k Limited Performance and Stability and Control Tests
Author: Charles Van Norman, Jerry D. Bowline, AIR FORCE FLIGHT TEST CENTER EDWARDS AFB CA.
Publisher: - 1967
ISBN-13:

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