F-35C Heavy Weight Ground Tow Test 4 x 2,000 lb GBU-31s

F-35 Armament, fuel tanks, internal and external hardpoints, loadouts, and other stores.
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spazsinbad

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Unread post11 Jun 2013, 09:25

http://2.bp.blogspot.com/-nA8I7RBRKsg/U ... 4_1137.jpg H/T SNAFU

"F-35C CF-3 was used for a heavyweight ground tow test at the Naval Air Warfare Center Aircraft Division test facility at NAS Patuxent River, Maryland, on 6 June 2013. The aircraft was fitted with four 2,000-pound GBU-31 guided bombs on the aircraft’s external pylons. US Navy Lt. Cmdr. Tony Wilson was in the cockpit during the test."
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Prinz_Eugn

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Unread post11 Jun 2013, 19:49

I have to say, the C is the best looking F-35. On the ground, at least.
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Unread post13 Jun 2013, 05:18

I agree, the big wing looks good on it.
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aceshigh

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Unread post13 Jun 2013, 18:12

The wing looks right. I wish the A-model had it as well. (and with an even bigger engine, so it wouldn't loose performance).
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Unread post13 Jun 2013, 19:41

Bigger engine means less range
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Unread post13 Jun 2013, 19:45

SpudmanWP wrote:Bigger engine means less range


Reminds me of the old response of a P-51 pilot to a Spitfire pilot who challenged him to a mock dogfight along the lines of sure, I will see you over Berlin at noon.
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Unread post13 Jun 2013, 20:10

Depends on what the need is.

A bigger engine and bigger wing = more drag, less internal fuel, higher fuel consumption rate, and less transonic acceleration.

The purpose of the larger wing with the existing F135 was to get a slower approach rate and to increase range.

The idea of a F-35A with the C wing and a larger engine to offset the drag of the C wing only ends up with a larger wing for the sake of ascetics at the expense of range.

Your example of the P-51 vs Spitfire comparison fails because they are completely different airframes.
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Unread post13 Jun 2013, 21:08

SpudmanWP wrote:Depends on what the need is.

A bigger engine and bigger wing = more drag, less internal fuel, higher fuel consumption rate, and less transonic acceleration.

The purpose of the larger wing with the existing F135 was to get a slower approach rate and to increase range.

The idea of a F-35A with the C wing and a larger engine to offset the drag of the C wing only ends up with a larger wing for the sake of ascetics at the expense of range.

Your example of the P-51 vs Spitfire comparison fails because they are completely different airframes.


Was not intended as a comparison for this just a reminder that range is often one of the most important operational characteristics of a fighter. It is not all about turning and burning.
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Unread post14 Jun 2013, 08:04

Wish there were more pics...can't find any yet.
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Unread post14 Jun 2013, 08:32

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Unread post14 Jun 2013, 10:16

On a completely different note, Has the redesigned tailhook for the F-35C been tested yet?
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Unread post14 Jun 2013, 11:13

'jacarlsen' the best place for your interest would be here: http://www.f-16.net/index.php?name=PNph ... &start=345

Work backwards or start at an earlier page or at the beginning of the thread: F-35C Lands at Lakehurst For Testing

TOP POST ON THIS PAGE 23 is the most up to date info:

http://www.f-16.net/index.php?name=PNph ... &start=330
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Unread post14 Jun 2013, 17:38

spazsinbad wrote:http://2.bp.blogspot.com/-nA8I7RBRKsg/UbZ0htabX2I/AAAAAAAAy-Q/zhmabMv3ix0/s1600/2013_News_Web_F35C_13P00240_004_1269967624_1137.jpg H/T SNAFU

"F-35C CF-3 was used for a heavyweight ground tow test at the Naval Air Warfare Center Aircraft Division test facility at NAS Patuxent River, Maryland, on 6 June 2013. The aircraft was fitted with four 2,000-pound GBU-31 guided bombs on the aircraft’s external pylons. US Navy Lt. Cmdr. Tony Wilson was in the cockpit during the test."


Can a F-35C catapult launch with that load-out (anything else in the internal bays) and nearly as important--can it bring back that load-out? :lol:
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Unread post14 Jun 2013, 17:48

Not sure on the Cat but I am pretty sure it can't bring-back that much... but neither can the Superhornet.

---edit--

The F-35C's shipboard Bringback is 10k lbs

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The Superhornet is 9k

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Unread post14 Jun 2013, 21:44

All USN catapults including EMALS are able to launch a Maximum All Up Weight F-35C. According to LM Fast Facts Maximum Weight = 70,000 lb class : https://www.f35.com/assets/uploads/down ... _facts.pdf

"Current Estimate F-35C: Maximum approach speed (Vpa) at RCLW of less than approximately 144.6 kts with 15 kts WOD at RCLW (of approximately 46,000 lbs Max Landing Weight) | RCLW = Required Carrier Landing Weight | WOD = Wind Over Deck" [SEE RCLW DEFINITION below]

http://www.f-16.net/f-16_forum_download-id-14367.html
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Scorecard: A Case study of the Joint Strike Fighter Program by Geoffrey P. Bowman, LCDR, USN, — 2008 April
"...The capability to operate from a carrier is not as easy as it sounds. Additional weight comes in the form of stronger landing gear, fuselage center barrel strength, arresting hook structure, and additional electrical power requirements. The Navy has added approach speed as a service specific key performance parameter. The threshold for approach speed is 145 knots with 15 knots of wind over the deck. This must be possible at Required Carrier Landing Weight (RCLW). The RCLW is the sum of the aircraft operating weight, the minimum required bringback, and enough fuel for two instrument approaches & a 100nm BINGO profile to arrive at a divert airfield with 1000 pounds of fuel. The minimum required bringback is two 2000 pound air-to-ground weapons and two AIM-120s.

The Navy further requires that the CV JSF be capable of carrier recovery with internal and external stores; the external stations must have 1000 pound capability on the outboard stations & maximum station carriage weight on the inboard."..."

http://www.f-16.net/f-16_forum_download-id-14791.html
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F-35C Opt AoA: VX-23 'Salty Dogs' F-35C Update - LCDR Ken “Stubby” Sterbenz
VX-23 Ship Suitability Department Head - Paddles Monthly - Sept 2010
..."The F-35C is 51.5 ft long and has a wingspan of 43 ft and 668 ft2 of wing area (7 ft longer wingspan and 208ft2 more wing area than the Air force or Marine versions.) It also carries 19,800 lbs of internal fuel - 1,000 pounds more gas then the Air Force version. It is powered by a Pratt and Whitney F135 engine that produces 28k lbs and 43k lb of thrust in MIL and AB respectively.

The max trap weight will be around 46k lbs, with an empty weight of about 35k lbs. It will fly an on-speed AOA of 12.3° at 135-140 KCAS [Optimum AofA or Donut].

Due to the fact that flap scheduling is completely automatic, the cockpit was designed without a flaps switch. Additionally, the tail hook retracts into the fuselage and is covered by hook doors that have an as-yet-to-be-determined airspeed limitation..." LT. Dan "Butters" Radocaj VX-23 Ship Suitability...

http://www.hrana.org/documents/PaddlesM ... er2010.pdf
____________________

JSF Carrier Variant Meets First Flight Goals By Graham Warwick 7 June 2010
“Handling qualities of the F-35C Joint Strike Fighter “exceeded expectations” on the June 6 first flight, says Lockheed Martin test pilot Jeff Knowles.

Handling with landing gear down was a key focus of the first flight as the F-35C has a 30% larger wing and uprated flight controls to reduce takeoff and landing speeds compared with the other F-35 variants.

Knowles says the aircraft approached at 135 kt., compared with 155 kt. for the smaller-winged F-35A and B variants at the same 40,000-lb. gross weight. Takeoff rotation speed was 15-20 kt. slower, he says...."

http://web02.aviationweek.com/aw/generi ... ht%20Goals
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