Rich,
The tests were made on a test stand with a propeller load. HP was calculated from load cell torque measurements and RPM. The elevation here in Laramie, WY is 7200 ft which limits the NA MAP to 23". The MAX RPM for the NA Renesis of 5300 at WOT
was not shown on the chart . 5600 RPM and MAP of 30" for the TC Renesis was the limit due to inability to keep the mixture from going lean. This was a result of a combination of a partially blocked fuel filter and the limited capacity of the
stock 1986 RX7 fuel pump, both of which have now been rectified.
RV6A, 1986 13B NA, RD1A, EC2
From: Rotary motors in aircraft [flyrotary@lancaironline.net] on behalf of ARGOLDMAN@aol.com [ARGOLDMAN@aol.com]
Sent: Thursday, January 03, 2013 1:27 PM
To: Rotary motors in aircraft
Subject: [FlyRotary] Re: turbo manifold
Still studying the chart
What was the reason for stopping the testing on there renesis both NA and turbo AT 5600rpm?
It's my understanding that the renesis is a higher revving engine than the standard 13B with it's lighter rotors etc.
What was the limiting factor? Were these Dyno tests?
Rich