MEMORANDUM REPORT ON
Consolidated B-24C, A.C. No. 40-2378
| Subject: | Acceptance Performance Tests |
| Section: | Flying Branch |
| Serial No.: | PHQ-M-19-1326-A |
| A. | Purpose | |
| 1. | Report on tests of B-24C conducted at the manufacturer's plant. Airplane equipped with four (4) Pratt and Whitney R-1830-41 engines and turbo superchargers and three-bladed constant speed propellers, blade design No. 6153A-12. Gross weight as tested 41,000 lbs. except where otherwise stated. Engine cowl flaps closed on high speed and fuel consumption tests. B.H.P. figures obtained from torque meters. | |
| B. | Test Results | |
| 1. | High speed at 25,000 ft. is 313 mph at 1200 bhp per engine at 2700 rpm. | |
MEMORANDUM REPORT ON
Consolidated B-24D, airplane, A.C. No. 40-696
| Subject: | Acceptance Performance Tests |
| Section: | Flight Section |
| Serial No.: | PHQ-M-19-1401-A |
| A. | Purpose | |
| 1. | To report on acceptance performance tests conducted at the manufacturer's plant on the B-24D airplane, A.C. No. 40-696. Airplane equipped with four (4) Pratt & Whitney R-1830-43 engines with torque meters; exhaust driven turbo superchargers; three bladed constant speed hydromatic propellers, blade design No. 6153-19. Landing gear retracted, wing flaps neutral, intercooler shutters wide open, cowl flaps in specified position. Airplane loaded to design gross weight of 41,000 pounds, c.g. location 25.8 percent and overload gross weights of 48,000 pounds, c.g. location 28.3 percent, and 56,000 pounds, c.g. location 29.8 percent. Deicer boots installed and all radio antenna in place. Exposed guns installed and in the aft position. Twp .50 caliber guns in tail turret; two .50 caliber guns in top fuselage turret; twp .50 caliber buns in belly turret. Nose guns not in place. Astrodome in place | |
MEMORANDUM REPORT ON
Consolidated B-24E, Airplane, AAF No. 40-7073
| Subject: | Comparative Propeller Performance Tests |
| Section: | Flight |
| Serial No.: | Eng-47-1672-A |
| A. | Purpose | ||
| 1. | To report comparative performance results of tests run on the B-24E airplane, AAF No. 42-7073 at Wright Field using the following propellers: | ||
| a. | Hamilton Standard Hydromatic, three-bladed constant speed full feathering propellers, blade design No. 6353A-18, normal blade angle range 18 to 88 degrees at 42 inch radius. | ||
| b. | Hamilton Standard Hydromatic, three-bladed constant speed full feathering propellers, blade design No. 6477A-0, normal blade angle range 18 to 88 degrees at 42 inch radius. | ||
| Speed vs Power, 49,000 pounds |
| Speed vs Power, 60,000 pounds |
FLIGHT TEST OF NORTH AMERICAN
B-24G, AAF NO. 42-78095
| II Summary
In general the flight characteristics of the airplane tested are the same as other similarly equipped B-24 airplanes. High speed was 291 MPH at military power, 2700 RPM, 49" Hg. manifold pressure, 1255 BHP per engine at 23,000 ft. altitude and 59,100 lbs. gross weight (62,000 lb. take-off weight). Climbs made at a gross take-off weight of 64,000 pounds with cowl flaps and intercoolers wide open, at rated power, 2550 RPM, 46" Hg. manifold pressure indicated a service ceiling of 24,300 feet using 1170 BHP per engine. Rate of climb at 20,000 ft. at rated power is approximately 300 ft/min. With balanced power the airplane tested required approximately two and one-half degrees of right rudder trim for straight flight and approximately five to six degrees right trim for take-off and initial climb. |
| Level Flight Results |
| Climb Results |
Liberator III. L.V.337
(4 - Twin Wasp R.1830-43)
Brief performance and tail buffet tests
Summary
| (a) The maximum measured speed of the aeroplane is 269 m.p.h. at 20,000 ft., but this is not the full throttle height (See end of para.1).
(b) The time to 20,000 ft. is 63 minutes, and the time to 10,000 ft. is 25 minutes. (c) The maximum rate of climb is 430 ft/min. at ground level. The service ceiling is not known. (d) The aeroplane takes off in 895 yards and reaches 50 feet iin 1295 yards, from rest (in zero wind and standard atmosphere). (e) From the scanty information obtained it is probable that the engine cooling is satisfactory for tropical use. (f) In level flight at rated power, opening the cooling gills fully reduces the true air speed of the aeroplane by approximately 30 m.p.h. (g) Tail buffeting is introduced when the inboard cooling gills are open within the range 1/3rd - 2/3rds but the degree of buffet is not dangerous at best climbing speed. |
