Graphical analysis and data sheet detailing crankshaft deflection and failure tests for a Condor model engine.
| Identifier | ExFiles\Box 63\4\ scan0145 | |
| Date | 25th August 1913 guessed | |
| CONDOR(Aero Engine) MODEL CRANKSHAFTS D.E.S. 36 STO TYPE WEBS A B DEFLECTION IN INCHES + .080 + .060 + .040 + .020 .000 - .020 - .040 - .060 - .080 NOTE PERMANENT SET ON BOTH CRANKS NIL. LOAD APPLIED = 750LBS LENGTH OF LEVER 8.125" DATUM POINTS AS PER SKETCH FLYWHEEL 8 DATUM PEGS SWEATED TO CRANKS FOR CONVENIENCE OF CLOCKING LEVER LOAD APPLIED ON THIS ¢ PARTICULARS OF RUNNING. CRANK | R.P.M | TOTAL REVS | TOTAL TIME RUN A | 600 | 400 | 2/3 MINS B | 300 | 364.850 | 20 HRS, 16 MINS BREAKING POINT OF CRANK 'A' IS SHOWN ON SKETCH WITH A FULL LINE. (OF CRANK B) A DOTTED LINE. A SECOND CRANK WAS RUN UNDER THE SAME CONDITIONS AS A AND BROKE AT 400 REVS IN THE SAME PLACE. | ||
From the Rolls-Royce experimental archive: a quarter of a million communications from Rolls-Royce, 1906 to 1960's. Documents from the Sir Henry Royce Memorial Foundation (SHRMF).