| Abstract | The supersonic performance of the CF-105 aircraft has been calculated for the following conditions:
(a) Combat Weight = 48,134 lb.
(b) C.G. Position at 0.28 MAC
(c) Orenda thrust estimates for PS/13 engine as installed in CF-105 (in particular T = 18,400 lb. at M = 1.5 at 50,000 ft.)
The following is a summary of calculated performance under the above conditions.
(i) Normal steady load factor at M = 1.5 at 50,000 ft. = n = 1.38
(ii) Absolute ceiling (at M = 1.5) = 56,800 ft.
(iii) Maximum level Mach number at 50,000 ft. = 1.75
It should be pointed out that these calculations apply to a combat weight of 48,134 lb., which is the combat weight as estimated by Avro. Since the NAE estimate of drag is higher than the Avro estimate, the combat weight should also be somewhat higher because of the extra fuel required to complete a combat mission of 200 nautical miles radius. However, the calculation of mission fuel has not yet been made by the NAE. |
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