OFFICIAL PERFORMANCE TEST OF FOKKER C0-4 EQUIPPED WITH LIBERTY 12-CYLINDER ENGINE

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1 Auburn University libraries lllllll llllllllllllllllllllllllllllll llllllllllllllllllllll\ ) File D 52.1 /Fokker/86 AR SERVCE N MA TON CRCULAR (AVATON ) t ee l PUBLSHED BY THE CHEF OF AR SERVCE, WASHNGTON, D. C. Vol. V June 1, 1925 No. 507 OFFCAL PERFORMANCE TEST OF FOKKER C04 EQUPPED WTH LBERTY 12CYLNDER ENGNE f (FL YNG SECTON REPORT) Engineering Division, Air Service McCook Field, Dayton, Ohio November 10, 1924 Ralph Brown Draughon LBRARY MAY 17 Z013 Non Depoitory Auburn University ". WASHNGTON GOVERNMENT PRNTNG OFFCE 1925

2 ., \.. i CERTFCATE: By direction of the Secretary of War the matter contained herein is published as administrative information and is required for the proper transaction of the public business. (n)

3 "(\,,._ OFFCAL PERFORMANCE TE TFt KER COA EQUPPED WTH LBERTY 12CYLNDER ENGNE SUMMARY OF RESULTS NOVEMBER 10, Airplane: Fokker C0 4. Type: X. A. S: No.: P325. Pila.ts: Lieutenant Barksdale and Lieutenant Batten. Engine: Liberty. Type: 12 cylinder, 400 horsepower. A. S. No.: Rated horsepower: 423 at 1,700 revolutions per minute. Propeller manufacturer: Engineering Division. Drawing or inspection No.: X Diameter: 10 feet. Pitch: 19.3 at 48 inches. Designed NVD v Zero torque ND., WEGHTS Pounds Empty with water, including 70 pounds variable load 3, 140 Armament 218 Equipment _ 362 Crew 360 Gasoline (92 gallons) 546 Oil (9 gallons) 68 Total weight, loaded 4, 694 Wing area (including ailerons): 407 square feet. Wing loading: pounds per square foot. Rated power loading: pounds per horsepower. Ground revolutions per minute: 1,520. Was armament in place during all tests? No rear guqs and Scarff. Disposable load: 1,554 pounds. Densi Temp. ty C. Converted to standard Standard altitude in feet (a) Speed (b) Climb Level M. p. R. p. T\r::e te R. p. M. p. h. m. min. min. m. h Yz. 824 lyz ) llyz Yz Q 72 1, , , , , , , , , , , , ,000 25,000 14,750 service , , ceiling. 16,800absolute 95. O 1, 510 O, O ceiling. Landing speed: 58 miles per hour. Endurance, full throttle at 10,000 r,jimb): 3 hours 42 minutes. feet t (1) F uel consumption: pound per horsepower per hour. At best blade setting, determined from tests. DSTRBUTON OF WEGHTS Weight empty (with water) Armament and equipment Crew Gasoline _ OiL Weight loaded Weight on front wheels (tail skid on ground) Weight on tail skid (tail skid on ground) Weight on front wheels (flying position) _ Weight on tail skid (flying position), (blocks) Pounds 3, " 4,694 3, , Distance center line of axle to point of support of tail skid, 18 feet, 11 inches. Provisions for special equipment not carried during test. DESCRPTON OF ARPLANE DMENSONS Overall span: 39 feet 6 inches + 2 feet 4 inches for aileron balance. Overall length: 29 feet 8 inches. Overall height: 10 feet 10 inches. n flying position: 5 feet 6:Y:; inches. ARP,A!>ES Wing curve: Fokker. Sweepback: None. Dihedral, degrees: 0. Stagger: 37.5 inches. Total area, including ailerons: square feet. Gap: 76 inches. UPPER PLANE (ncluding center section) Span: 39 feet 6 inches. Chord: 79 inches. Area, with ailerons: square feet. ncidence, degrees: nner, 2. Outer, 1 +. LOWER PLANE Span: 32 feet 10 inches. Chord: 59 inches. Area: 143 square feet. (including J nci?ence, degrees: nner,.so+. Outer, 2 +. Effective, 1.38.

4 2 ALERONS OR FLAPS Number: Two. Arrangement.: Trailing edge upper wing tip. Upper length: 9 feet 4% inches. Balance, 14 inches. Upper chord: 672 to 11 inches. Upper area: 17.6 square feet. Distance from center of ailerons to longitudinal axis of airplane: 15 feet H inch. CENTER SECTON Area: None. Upper wing integral. Contents: Gravity gas tank. Area: square feet. Chord : 56 inches. STABL7 E R ELEVATOR Area: 23 square feet. Balanced area, square feet. Distance from leading edge of elevator to center of gravity of airplane: 19 feet 5 inches. Chord: 24 inches maximum. Span: 11 feet 6 inches. Span of balance: 17 inches. RUDDER Area: 8.85 square feet. Balanced area: square feet. Distance from leading edge of rudder to center of gravit.v of airplane, 19 feet 7 in ches. FUSELAGE Maximum cross section shape!ta " f Maximum cross section area.. ;::}a Maximum cross section dimension =i_ l1.."j LAND NG GE AR Number of wheels: Two 36 inches by 8 in ches. Tread: 6 feet 7 :Y:;; inches. Shockabsorbing system: E lastic chord. Braking device : Tail skid. h ee l s a head of center of gravity: 25 inches. Area: 4 square feet. FN DESCRPTON OF POWER PLANT ENGNE Make: Liberty. Factory No A. S. No YG. Type V 45 water cooled. Number in plane: One. Location : Nose of fuselage. Rated horsepower: 400. Rated revolutions per minute: 1, 700. Bore : 5 inches. Stroke: 7 inches. Compression ratio: 5.42 :1. Weight, dry: 84,369. Gas consumption: 216 pounds per hour. Oil consumption: 16 pounds per hour. Weight of water in engine: 45 pounds. Remarks : Model GNTON Battery or magneto : Battery. Make : Delco. Number: Two, 8volt. Distributor: D elco. Plugs, make: Mosler. T ype: M 1. Gap:.015 inch. Remarks: Time"s E. S CARBURETOHS Make: Zenith. T ype: United States 52. Number: 2. Choke: 36. Compensator: 170. Gas drains: Tube direct from carburetor. Air intake: Vertical overhead scoop. Mixture control: Backsuction type. Effective to altitude: Yes. RADATOHS Make : Fokker. Type : A. S. standard. Number: Twoone on each side. Position: Rear of fire wall. D epth : 7 inches. Length : 2672 inches. Width: 11 % inches. R adiator surface : 268 Rquare feet, total. Temperature adjustment: Retracting. Flow, gallons per minute: 39.6 gallons per minute at 2.5 pounds gauge. Thermometers, make: Boyce. Weight, pounds: 54 pounds (each). T ype: "C." Water capacity of whole system : 120 pounds (approximate). EXHAUST PPES Description: Standard manifold. LUBRCATON Capacity oil tank: 72 pounds. Oil used (bra nd): Liberty. Oil pressure: 42 pounds. Oil temperature : nlet, 122 F.; outlet, 139 F. T ype pump: Gear. Wet or dry sump: Dry sump. Description lubrication system: Force feed to main bearings, connecting rods, and cam shafts, spray to cylinder walls a nd wrist pins. FUEL SYSTEM Number of tanks: One main, 1 gravity. Location: Gravity, upper wing; main, betwoen engine and pilot. Capacity: Main, 80 gallons (480 pounds). Reserve, 60 pounds. Description of fuel supply system: Gravity from gravity tank to ma in. Pressure from main tank to carhuretor b y vertical shaft gear pump C 5.

5 <. 3 ENGNE CONTROi, Description: Rod and lever. PROPELLER Make: Dural. Number blades: Two. Diameter: 10 feet. Pitch: 19.3 at 48 inches radius. Manufacturers N o.: X A. S. No. ; inspection, Remarks: Adjustable on ground. PLOTS OBSERVATONS ON FOKKER co..:.4pa2s 1. As a result of fl ying the Fokker C04 in routine test work by the undersigned, the following is sub 1)itted: TAX NG Taxies well and is quite maneuverable on the ground. TAKEOFF s generally good, although the tail seems to come up to flying position rather slowly. Has no tendency to swing on takeoff. LANDNG Lands easily and slowly, but has quite a decided tendency to ground loop in either direction, and it is not a lways possible to stop it even with power. BALANCE Seems to be slightly unstable longitudinally. MANEUVERABLTY Maneuvers well and is exceptionally light on controls. This ship has not been stunted by the undersigned. ACCESSBLTY Cockpit very roomy and comfortable. nstruments and controls located convenient ly, although a little difficulty is encountered in getting in and out of cockpit, especially when wearing heavy clothing. VSBLTY Excellent in all directions excepting straight down ; however, this is not considered bad as plane can be. turned or banked in order to observe in this direct ion. 2. Considering this plane in comparison with the Atlantic A01, it is not quite as good a ship, although having the same general characteristics. EUGENE C. BATTEN, First Lieutenant, Air Service, T est Pilot.

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