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GRUMMAN F6F-5 HELLCAT II PERFORMANCE


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#1 CORSNING

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Posted 08 February 2014 - 02:50 PM

F6F MILITARY POWER PERFORMANCE

 

http://www.wwiiaircr...rg/f6f/f6f.html

 

A/C No. 58310 Report date: 9/7/44

 

Altitude/Speed/Climb

Meters/mph/fpm/minutes to altitude

S.L.......318/2660

.1,000..322/2415

.2,000..333/2390

.3,000..345/2340

.4,000..358/2170

.5,000..373/2000

.6,000..376/1765

.7,000..390/1350

.8,000..383/  900

.9,000..374/  555

10,000.NG./  215

Feet---------------------------

.5,000..326/2405/ 1.95

10,000.346/2360/ 4.0

15,000.366/2325/ 6.25

20,000.377/2000/ 8.6

25,000.389/1520/11.4

30,000.370/  835/15.6

35,000.NG./  335/26.0

 

Maximimums: 391 [email protected] 23,100 ft. and 2,660 [email protected] S.L.

 

Ceilings

Combat: 28,790 ft.

Operational: 33,330 ft.

Service: 37,100 ft.

 

Wing Area (all F6F-5s): 334 sq.ft.

 

Wing Loading: 37.19-lbs./sq.ft.

 

Power Loading: 6.369+lbs./[email protected] 18,800 ft.

 

Engine: P&W R-2800-10W : 1865 [email protected] 1,500 ft. (military power). Combat power was applied between 18,800-22,800 ft. with maximum output of 1,950 [email protected] 18,800 ft. with 60"Hg boost.

 

Combat Weight: 12,420 lbs.

 

hellcattaxi.jpg

CAF SoCAL


Edited by CORSNING, 13 November 2017 - 05:23 PM.


#2 CORSNING

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Posted 08 February 2014 - 03:06 PM

F6F-5 MILITARY PERFORMANCE

 

A/C No. 72731 Report date 7/14/45

 

Altitude/Speed/Climb

Meters/mph/fpm/minutes to altitude

S.L.......311/2910

 1,000..320/2695/ 1.2

 2,000..323/2560/ 2.45

 3,000..335/2540/ 3.7

 4,000..347/2515/ 5.05

 5,000..361/2380/ 6.35

 6,000..370/2190/ 7.75

 7,000..371/1865/ 9.45

 8,000..372/1470/11.4

 9.000..NG./1080/14.4

10,000.NG./  675/17.8

Feet----------------------

 5,000..320/2570/ 1.85

10,000.335/2540/ 3.9

15,000.355/2500/ 5.8

20,000.369/2185/ 7.95

25,000.375/1620/10.5

30,000.NG./1015/14.55

35,000.NG./  415/22.0

 

Maximums: 376.5 [email protected] 23,900 ft. and 2,910 [email protected] S.L.

 

Ceilings

Combat: 30,170 ft.

Operational: 34,250 ft.

Service: 37,600 ft.

 

Wing Loading: 37.84+lbs./sq.ft.

 

Power Loading: 6.549+lbs./hp.

 

Engine Power: 1,930 hp./2,500 ft./52.5"Hg.

 

Combat Weight: 12,640 lbs.



#3 CORSNING

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Posted 08 February 2014 - 03:58 PM

F6F-5 STANDARD PERFORMANCE

 

BUREAU OF AERONAUTICS, NAVY DEPT. NAVAER 1335A

 

( Go to Google and type in STANDARD AIRCRAFT CHARACTERISTICS F6F-5. You should have a few choices that will bring up this document ).

 

Altitude/Speed/Climb

Meters/mph/fpm/minutes to altitude

S.L.......318/2980

 1,000..330/2920

 2,000..342/2860

 3,000..355/2805

 4,000..367/2460

 5,000..370/2320

 6,000..276/2000

 7,000..380/1675

 8,000..373/1315

 9,000..362/  955

10,000.NG./  600

Feet--------------------------

 5,000..337/2890

10,000.356/2800

15,000.366/2430

20,000.376/1940/ 7.7

25,000.377/1450

30,000.360/  905

35,000.NG./  360

 

Maximums: 380 [email protected] 23,400 ft. and 2,980 [email protected] S.L.

 

Ceilings

Combat: 29,130 ft.

Operational: 33,700 ft.

Service: 37,350 ft.

 

Range Maximum: 950 mls./178 mph./15,000 ft.

 

Engine: P&W R-2800-10W :

2,030 hp./2,700 rpm./S.L.

2,110 hp./2,700 rpm./13,100 ft.

1,930 hp./2,700 rpm./15,700 ft.

1,940 hp./2,700 rpm./18,000 ft.

 

Combat Weight: 12,740 lbs.

 

Wing Loading: 38.14+lbs./sq.ft.

 

Power Loading: 6.038 -lbs./hp.

 

Armament: 6 x 0.5in,/200 or 400 rpg. OR 2 x 20mm/225 rpg. + 4 x 0.5in./400 rpg.

 

 

There is no date on this STANDARD AIRCRAFT CHARACTERISTICS report so I do not know if it is an early specifications report or a later final report.

 

I have found that several aircraft listings like this can be located by typing in STANDARD AIRCRAFT CHARACTERISTICS followed by the model of aircraft desired.



#4 CORSNING

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Posted 08 February 2014 - 04:48 PM

F6F-5 COMBAT POWER PERFORMANCE

 

I have not located a complete report on the combat performance of the F6F-5 at this time. However a couple of years ago I did a work up of calculations using the Hellcat II data sheet and other reports. The following is what I came up with:

 

Calculated performance:

 

Altitude/Speed/Climb

Meters/mph/fpm

S.L.......335/3500

 1,000..339/3440

 2,000..348/3380

 3,000..360/3180

 4,000..373/2955

 5,000..379/2605

 6,000..392/2225

 7,000..391/1835

 8,000..383/1435

 9,000..374/1070

10,000.NG./  685

Feet-------------------------

 5,000..341/3410

10,000.361/3095

15,000.380/2725

20,000.392/2195

25,000.389/1610

30,000.370/1020

 

Maximum: 392 [email protected] 19,200 ft. (with rocket racks and bomb/aux.tank pylons and shackles) and 3,500 [email protected] S.L.

 

Ceilings

Combat: 30,125 ft.

Operational: 34,350 ft.

Service: 37,800 ft.

 

Wing Loading: 35.49+lbs./sq.ft.

 

Power Loading: 5.269-lbs./[email protected] S.L. AND 5.553-lbs./[email protected] 12,400 ft. (at take-off weight)

NOTE: weight of an A/C decreases immediately after the engine is started and fuel begins to be consumed.

 

Engine: P&W 2800-10W

2,250 hp./58" Hg/S.L.

2,135 hp./60" Hg/12,400 ft.

1,970 hp./60" Hg/16,900 ft.

 

Combat Weight: 11,855 lbs. (air superiority/light fighter mode)

 

http://www.wwiiaircr...at-II-ads-a.jpg


Edited by CORSNING, 08 November 2017 - 09:15 PM.


#5 CORSNING

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Posted 08 February 2014 - 07:21 PM

PROJECT TED NO. PTR - 1115

FINAL REPORT ON COMPARATIVE COMBAT EVALUATION TRIALS OF JAPANESE TONY I TYPE 3 FIGHTER

The Ki 61-I was tested against the F6F-5, FM-2, F4U-1D, F4U-4, F7F-3 and F8F-1. The following information comes from that test report dated 26 January 1943. 

 

CLIMB: The F6F has a superior rate of climb at all altitudes.

 

SPEED: The F6F is faster at all altitudes.

 

TURNS: The Tony is greatly superior to the F6F in turns at speeds below 180 knots. (The FM-2 has an equal or slightly smaller radius of turn than the Tony I type 3).

 

ROLLS: The Tony I and F6F are approximately equal at low speeds. The F6F is greatly superior at high speeds.

 

ACCELERATION: The F6F has the initial advantage.

 

ZOOM: The F6F is superior.

 

 

 

The following information comes from a report comparing the A6M5 model 52 against the F6F-5, F4U-1D and FM-2. Note: The turns of the FM-2 and Zeke 52 were very similar, with a slight advantage in favor of the Zeke 52. (Sorry, I couldn't help myself). 

 

ZEKE 52 vs F6F-5

 

CLIMB: The Zeke climbed about 600 fpm. better up to 9,000 ft., advantage fell off gradually until 14,000 ft. where they were about equal. Above 14,000 ft. the F6F held the advantage. The best climbing speeds were: 105 knots. for the Zeke and 130 knots for F6F. 

 

ROLL: Equal at speeds under 200 knots, F6F superior above.

 

TURN: Zeke greatly superior in slow speed turns at low and medium altitudes, decreasing to about equal at 30,000 ft.

 

DIVE: Initial dive about equal, after which the F6F was far superior.

 

VISION: The Zeke was considered to permit better vizion in all respects.

 

MANEUVERABILITY: The Zeke was far superior at speeds below about 175 knots, diminishing with speed until 200 knots. The F6F had the advantage above 200 knots ( 230 mph ).

 

SPEED ( I SAVED THIS SPECIFICALLY FOR LAST ): The F6F-5 was much faster than the Zeke 52 at all altitudes. Top speeds attained were 335 mph at 18,000 ft. for the Zeke and 409 mph. at 21,600 ft. for the F6F-5.

 

Source: http://www.wwiiaircraftperformance.org

 

 

 

On http://forum.axishis...ic.php?t=99933 it was posted that in American Warplanes the WEP maximum speed of the F6F-5 was 404 mph. ('American Warplanes of World War II' by David Donald?)


Edited by CORSNING, 08 November 2017 - 09:26 PM.


#6 CORSNING

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Posted 12 December 2015 - 10:34 PM

GRUMMAN F5F-5 MAXIMUM SPEED

 

   

     America's Hundred thousand states that a modified F6F-3 with F6F-5 features was flown at a speed of 410 mph./21,000 ft.in January 1945. No other particulars listed.

 

     In TAIC REPORT NO. 17 issued November 1944 in which the A6M5 was pitted against the F4U-1D, F6F-5 & FM-2 it states that the F6F-5 managed to reach 409 mph./21,600 ft. No boost level given.

 

     I have read that David Donald lists the F6F-5 as being able to reach 404 mph. in his book "American Warplanes of World War II". I do not know at this time if a boost level was given.

 

    The following performance information comes from Graph 71 illustrated in America's Hundred Thousand  by Francis H. Dean. This is manufacturers data. No engine boost level is given.

 

F6F-5 HELLCAT (Grumman tests)

 

Full throttle height low s/c: 359 mph./762 m. (2,500 ft.)

Switch low/high s/c: 357 mph./1,264.9 m. (4,150 ft.)

FTH medium altitude: 394 mph./4,800.6 m. (13,750 ft.)

Switch medium/high altitude: 391.5 mph./5,425.4 m. (17,800 ft.)

FTH high s/c: 400 mph./6,171.2 m. (20,250 ft.). Dean states in text 20,000 ft.,

Switch Combat/Military power: 391 mph./7,071.4 m. (23,200 ft.)

FTH Military high s/c: 395 mph./7,559 m. (24,800 ft.)

 

350 mph./S.L.

359 mph./762 m. full throttle height neutral blower.

358 mph./1,000 m.

357 mph./1,264.9 m. switch neutral/low blower.

365 mph./2,000 m.

375 mph./3,000 m.

385.5 mph./4,000 m.

394 mph./4,800.6 m. full throttle height low blower.

395 mph./5,000 m.

391.5 mph./5,425.4 m. switch low/high blower.

398 mph./6,000 m.

400 mph./6,172.2 m. full throttle height high blower.

392 mph./7,000 m.

391 mph./7,071.4 m. switch combat/military power.

395 mph./7,559 m. full throttle height military power high s/c.

389 mph./8,000 m.

 

Combat Weight: 12,483 lbs.

 

Note: The graph that these performance figures were drawn from looks like a typical performance line of a Hellcat using 'military' power, not combat power. The full throttle height in combat power is usually at a  much higher altitude than the graph displays.


Edited by CORSNING, 12 November 2017 - 02:08 PM.


#7 CORSNING

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Posted 08 November 2017 - 10:13 PM

The following information is from History Stories (/News). It comes from the report

" The Akutan Zero: How a Captured Japanese Fighter Plane Helped Win World

War II " by Elizabeth Hanes.

 

     " On September 20, Lieutenant Commander Eddie Sanders became the first

pilot to fly a Zero in American colors. The plane performed beautifully, and Sanders

went on to fly 24 test flights in 25 days. In the process, he discovered the Zero

possessed not one but two Achilles' heels. First, it was nearly impossible to perform

rolls at moderately high speeds. This meant that forcing the enemy into such a

maneuver would confer a tactical advantage to Allied pilots. Second, a poorly

designed carburetor caused the engine to sputter badly when the plane was placed

into a dive at a high rate of speed. Thus, forcing the Zeroes to dive during a dogfight

might make them easy targets for Allied gunners."

     " Marine Captain Kenneth Walsh described how he used information from the  

Zero test flight to finish the war with 17 aerial victories over Zeros: "With a Zero on

my tail I did a split S, and with its nose down and full throttle my Corsair picked up

speed fast. I wanted at least 240 knots, preferably 260. Then, as prescribed, I rolled

hard right, As I did this and continued my dive, tracers from the Zero zinged past my

plane's belly. From information that came from Koga's Zero, I new the Zero rolled

more slowly to the right than to the left. If I hadn't knon which way to turn or roll, I'd

have probably rolled to my left. If I had done that, the Zero would likely have turned

with me, locked on, and had me. I used that maneuver a number of times to get

away from Zeros."

     " Masatake Okumiya, a Japanese officer who led many Zero squadrons and

authored the book "Zero", described the significance of the Allies' capture of Koga's

plane as 'no less serious than the Japanese defeat at Midway' and said it 'did much

to hasten our final defeat'."

 

http://www.history.c...in-world-war-ii


Edited by CORSNING, 08 November 2017 - 10:15 PM.

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#8 CORSNING

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Posted 13 November 2017 - 06:03 PM

Hellcat II JV.224

Aircraft and Armament Experimental Establishment,

Boscombe Down

Period of tests- September - October 1944

The following information comes from a report provided by Mr. Neil Stirling

on http://www.wwiiaircraftperformance.org

 

     This Report deals with the effect of the introduction of water injection on

climb performance in Auxiliary Low gear and on level speed performance

in Auxiliary High gear.

     Climb: The rate of climb is increased by 650 ft/min at all heights up to

11,200 ft., the full throttle height using water injection.

     Level speed: The true level speed is increased by 20 mph (17 knots)

up to 18,600 ft., the full throttle height using water injection. At this height

the true level speed is 377 mph (328 knots) compared with 367 mph

(319 knots) at 21,800 ft., the full throttle height for the maximum manifold

pressure permissible without water injection.

 

The aircraft was flown at a mean weight of 11,500 lb. (no external stores).

Speeds recorded using water injection and 60"Hg boost:

354 mph./12,000 ft.

361 mph./14,000 ft.

368 mph./16,000 ft.

375 mph./18,000 ft.

377 mph./18,600 ft.

374 mph./20,000 ft.

367 mph./21,800 ft.

366 mph./22,000 ft.

353 mph./24,000 ft.

Climb

2,000 ft./3,160 fpm./0.63 min.

4,000 ft./3,160 fpm./1.26 min.

6,000 ft./3,160 fpm./1.89 min.

8,000 ft./3,160 fpm./2.25 min.

10,000 ft./3,160 fpm./3.15 min.

12,000 ft./3,000 fpm./3.80 min.

14,000 ft./2,680 fpm./4.51 min.

15,000 ft./2,490 fpm./4.91 min.

 

Converting altitudes to meters within the scope of these tests looks like this:

Altitude / Speed / Climb

Meters / mph / minutes to altitude

S. L.                3160 

1,000              3160     1.04

2,000              3160     2.08

3,000              3160     3.12

3,415              3160     (critical height for climb)

4,000   358     2820

5,000   369

5,700   377    (full throttle height for speed, still at 60"Hg)

6,000   373    (56.9"Hg)

7,000   361    (49.9"Hg)

 

This aircraft and these tests are mentioned in Peter Caygill's book

Flying to the Limit. The following are quotes from this book, page 187.

     "Although the service ceiling was quoted as being 37,800 ft., the

Hellcat struggled much above 30,000 ft."

     "The stalling speed with gear and flaps down was a very low 67 mph. IAS."


Edited by CORSNING, 13 November 2017 - 06:08 PM.





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