1.
What causes the "Howl"?Here we try to give some answers to frequently asked questions about the Starfighter.
2. Who won the Collier Trophy 1958?
3. How many Starfighter were with the Marineflieger (German Navy)?
5. Does Jacqueline Cochran still hold women's world speed records?
7. How was the J-79 engine started?
8. What was the T-2 Reset/Cutback?
10. What was the fastest and highest operational flight known?
11. What was the difference between the so called "Lil-D" and "Big-D" F-104D?
13. Why does the F-104S have engine auxiliary inlet doors (EAID)?
14. Why was the "0" or "O" (depending on which source you read) serial presentation used?
15. How did the BLC system operate?
It is actually the simple event of two differing airflows coming together and causing a whistle! The engine is surrounded with bypass air, some of which is coming from the engine air bypass flaps, and some is coming from generator access doors and aft fuselage suck-in panels. This bypass air is mixed with heated air coming from within the engine, which has been heated due to it having passed through the compressor and hot section. The result is a mixture of heated air, that which has passed through the engine, and cooler air, that which has passed around the engine, all of which is forced to be mixed when it encounters the convergent/divergent exhaust nozzle system. What we have is two airflows, one heated and faster from the engine, mixed with a slower and cooler airflow, from around the engine, forced out through the exhaust. The result is a whistle. Some call it a howl. What it really is, is J-79 installed in F-104, in operation. The howl is different in the 104 from the F-4 due to the differing amount of bypass airflow in the 104. The howl is also different in dash -19 and -J1K engines due to the differences in the convergent/divergent nozzle systems. It's still J-79, and we all love it.
by Mike Vivian, former USAF F-104A to F-104G pilot, Luke IP and Luftwaffe Exchange pilot
2.
Who won the Collier
Trophy 1958?
Established in 1911, the Robert J. Collier Trophy was first granted in 1929 as a national award honoring those who had made significant achievements in the advancement of aviation. Collier, publisher, noted sportsman-pilot, and early president of the Aero Club of America, commissioned the 525-pound trophy's design to Ernest W. Keyser of Baltimore MD, and it was originally named the Aero Club of America Trophy. It wasn't until that organization was dissolved in 1922 and the National Aeronautic Association formed that Collier was honored in title. The name became official in 1944, and the award presented once each year by the President of the USA, with the trophy on permanent display at National Air & Space Museum (NASM).
The trophy is awarded for "the greatest achievement in aeronautics or astronautics in America, with respect to improving the performance, efficiency, and safety of air or space vehicles, the value of which has been thoroughly demonstrated by actual use during the preceding year."
1958
United States Air Force and industry team, for development of the F-104
Clarence L. Johnson Lockheed Aircraft Corporation for the design of the airframe
Neil Burgess and Gerhard Neumann of General Electric Company, Flight Propulsion
Division for development of the J-79 turbo jet engine
Maj Howard C. Johnson, USAF, for establishing a world land plane altitude
record of 91.249 feet (27.813 m) on May 7, 1958 with YF-104A 55-2969 of the
83rd FIS at Edwards AFB
Capt Walter W. Irwin, USAF, for establishing a world straightaway speed
record of 1.404,19 miles per hour (2.259 km/h) on May 16, 1958 with YF-104A
55-2969 "Speedy" of the 83rd FIS at Edwards AFB
3.
How many Starfighter
were with the Marineflieger (German Navy)?
| Initially the GN received 112 aircraft: | ||
| 79 F-104G (Fighter Bomber), 7 to RF-104G modified |
Sep 1963 - Oct 1965 | |
| 27 RF-104G (1st squadron of MFG 2) | Mar 1965 - Dec 1965 | |
| 6 TF-104G | 112 total initially | |
| 13 TF-104G | ||
| 36 F-104G (MBB) | 49 total additionally | Dec 1971 - Jan 1973 |
| 6+1 F-104G (on temporary loan from Luftwaffe) |
7 total | |
| 168 total overall | ||
Construction number 8222, a Fokker built RF-104G , with the callsign EB+121, but belonging to AG 51, was airlifted to USA 1966 for SLAR (Side Looking Airborne Radar) tests. It was modified into a RF-104G-1 and tested in 1967. The modification consisted in a large under-fuselage pod with the APQ-102 side-looking radar and an additional oblique camera. The nose-radome was lengthened by 1 meter for additional sensors for the terrain-following radar. The program was cancelled in favor for the RF-4E Phantom. The RF-104G-1 was stored at Palmdale and airlifted 1972 in non flyable status to MBB. Re-modification was not practicable. The aircraft was preserved on a pole at the main gate of LVR 1 at Erding AB in 1974 as "80+58" (8058 being the old postal code for the city of Erding).
5.
Does Jacqueline Cochran
still hold women's world speed records?
Jacqueline Cochran to set three women's world's speed records:
In the spring of 1963 Cochran brought the distinctive red-white-and-blue Starfighter, owned by Lockheed, to Edwards Air Force Base. Colonel Chuck Yeager was running the Aerospace Research Pilot School (ARPS) at the time, and thus was available to assist his old friend in her quest. Flying Lockheed owned TF-104G N104L demonstrator "Free World Defender" over the 15-25 kilometer straight-away course, she reached Mach 1.94 and beat her own record for the distance. Ms. Cochran's Model The TF-104G was delivered later to the Koninklijke Luchtmacht (KLU) with the Dutch serial D-5702; later delivered to Turkey on August 25, 1980 with serial "5702"; later recoded to Turkish AF "4-702" and later "9-702".
April 12th 1963, she averaged 1.273,10 mph over a 15-25 km straight line
course, she reached Mach 1.94 and beat her own record for the distance.
May 1st 1963 she flew at an average speed of 1.203,686 mph (1.937,14 km/h),
over a 100-km Closed Circuit course, taking the women's record away from the
French aviatrix Jacqueline Auriol.
Records are only made to be broken, however, and it was not long before Mme Auriol wrested the 100 km record back to France. Jackie Cochran interpreted this as a blatant affront. With a determined tilt to her chin, she returned to the Flight Test Center a fourth time in May 1964. This time, she was flying a completely bare-metal F-104G adorned only with a logo "Lockheed F-104G Super Starfighter" on the nose. Its General Electric J79-GE-11A turbojet was rated at 15,300 lbs. of thrust, which was rated at a top speed of some 1,320 mph. (F-104G serial number 62-12222)
May 11th 1964, she averaged 1.429,297 mph over a 15-25 km straight line course.
This speed was over 155 mph faster than her own previous record and the fastest
speed ever attained by a woman pilot.
June 1st 1964 she flew at an average speed of 1.303,241 mph over a 100-km Closed Circuit course, beating the existing women's record of 1.266 mph held by the well-known French Aviatrix Jacqueline Auriol.
June 3rd 1964 she flew at an average speed of 1.135 mph over a 500-km Closed Circuit course. This time, the old record that she broke was her own, established over the same course in 1961.
It is a small wonder that many of her flight records are still unbroken, 40 years later.
Jacqueline Cochran, the world fastest woman
CCV: Control Configured Vehicle F-104G
MBB became interested at an early date in highly maneuverable aircraft. A Fokker-built F-104G c/n 8100 (KG-200, renumbered to 23+91, later renumbered 98+36) was modified by MBB as part of a five-year research program into a control configured vehicle (CCV) and flyby wire technologies. Natural stability was replaced with computer controlled flyby wire systems that allowed the aircraft to be made unstable. This natural instability could then be controlled to provide extra agility. The aircraft was provided with a triple redundant flyby wire system in 1977. The transition from the naturally stable Starfighter aerodynamics was taken in gradual stages, first by adding ballast to alter the center of gravity. In 1980, a complete F-104 tailplane section was then grafted to the spine on the upper fuselage forward of the wing to further destabilize the aircraft. Fairings were added over the wings, and the aircraft was marked with extra Day-Glo panels for high visibility. 20 percent negative stability was finally achieved within the specified limits of Mach 1.3 and 650 knots by the time the trials were successfully concluded. The data gathered was of great assistance to the design of the EFA and was also used during the development of the Rockwell/MBB X-31 test bed. The F-104CCV was then transferred to the Wehrtechnisches Museum at Koblenz on Oct 6.1984.
7.
How was the J-79
engine started?
To start the General Electric J-79 or its MBB J-1K improvement AIR for rotation is needed. This is accomplished via a small starter turbine located on the front frame of the engine and in front of the Inlet Guide Vanes (IGV). This unit is connected to the main shaft and rotates the engine to an RPM capable of providing enough mass airflow through the engine so that when ignition and fuel are introduced the resulting fire is controlled and will escape to the rear and thru the three turbine wheels. These three wheels are directly connected, via the main shaft, to the compressor which is rotating because AIR was forced over the small starter turbine blades by the external AIR starting unit. AIR drives the starter turbine, air pressure connects the starter turbine to the engine main shaft and rotation occurs. Electricity is NOT required to rotate a J-79. Ignition is provided by one of two igniter spark plugs located within the engines burner cans. AIR provides mass airflow thru the engine so that at 10-12% RPM, when the throttle is opened, (that's when fuel is introduced to the burner cans) enough total mass airflow is available to keep the resulting fire from touching any of the sides of the burner cans and no damage results from overheat. At 40% RPM, AIR is removed from the starter turbine. Watch the pilots fingers as the engine accelerates during an engine start, (one finger=10%, two fingers=20%, three fingers= 30% four fingers = 40%, at which time the external AIR starting unit is turned OFF to remove all AIR pressure from the small starter turbine. The engine can now accelerate to its idle RPM which is 67%. (Coincidently 67%= 5.000 RPM) For those of you really interested, 100% = 7460 RPM and is called Military power, which is roughly 10.000 pounds of thrust.
by Mike Vivian, former USAF F-104A to F-104G pilot, Luke IP and Luftwaffe Exchange pilot
Engines installed in supersonic aircraft must deal with a large range of
airflow and inlet temperature. In the F-104, engine air by-pass flaps are
installed which permit some of the air coming into the engine air inlet ducts
to by-pass the engine entirely. These by-pass flaps open fully when the landing
gear is fully retracted and allow excess air to flow around the engine so
that the engine may, more or less, ingest what air it needs. Engine air inlet
temperature is another matter. As the intake air becomes warmer, air density
decreases for any given pressure. The engine fuel control unit takes at least
4 variables into account to determine how much fuel to give the engine. These
are: Compressor inlet temperature (CIT) or "T2", Compressor discharge pressure
or "P3", Engine RPM, and Power Lever Angle. How hot, how much pressure, how
much RPM, and how much thrust is desired. The fuel control uses these variables
to decide how much fuel to provide. As airspeed increases, the engine air
inlet temperature increases. Remember our old friend ram rise. As the air
gets warmer, the air density decreases. Compressor efficiency decreases proportionately.
The engine fuel control, from 92 to 104 deg C inlet temperature, compensates
for this by increasing rpm from 100 % to 104% to make up for the loss in air
density. This restores lost compressor efficiency and provides additional
thrust. This is called T-2 Reset. Reset changes the engine idle speed. This
is done to prevent engine stall if the throttle is suddenly brought to idle.
When the engine inlet temperature exceeds 105 deg C, the engine RPM remains
at 104% even when you retard the throttle to idle. CIT only climbs to 105
deg C for one reason, you are going fast! When you are going that fast, there
is a lot of air being stuffed into the intake. The RPM must be kept high in
order to ingest the air, or it will do the same thing you would do if you
drink a warm coke too fast, it will burp! It, however, will burp somewhat
louder than you. We all refer to airplanes as females. They are less attractive
when they burp. This one is designed not to. Don't worry, as speed and CIT
decrease, the RPM will again begin to respond to the throttle. This is all
normal. Another phenomenon is T-2 Cutback. Again, based upon the effects of CIT,
compressor efficiency increases as CIT decreases. At high altitude cruise
or at low airspeed and at high altitude, do not expect 100% RPM even though
the throttle may be at military. If the CIT is below minus 12 C and decreasing,
RPM will begin to decrease from 100%. This is to maintain an adequate margin
from compressor stall. T-2 Cutback is seen much less than T-2 Reset since
normally when we are flying high, we are going fast. by Mike Vivian, former USAF F-104A to F-104G pilot,
Luke IP and Luftwaffe Exchange pilot After a glance at my 104G Dash-1, I can't find any mention of the engine
secondary airflow system, which is where the A and B-Flaps reside. Perhaps
the reason is that their function is normally automatic, and the pilot has
no control or indication of whether they are working. Still, the F-104A-D
and CF-104 manuals talk about the flaps (though the CF-104 manual isn't fully
accurate in its description). Maybe they just wanted to simplify the 104G
manual a bit. There are ten secondary airflow bypass ports located at the mating point
of the engine inlet and the inlet duct. These ports are each covered by a
movable bypass flap. When these flaps are in the "closed" position
(they are set to ¼ inch open), they provide a total of 25 square inch open
area for secondary (bypass) air to flow around the engine. Bypass air is used
to cool the engine case, cool the afterburner, cool the aft fuselage and cool
the nozzle. In the -3, -7 and -11 engines, bypass air is also used to form
the diverging cone in the nozzle. In the -19 engine, the longer nozzle petals
serve to form the divergent cone, and the bypass air serves primarily to cool
these petals, though it does help smooth the effective divergent cone a bit.
It is the bypass flow through the nozzle that gives the -3, -7 and -11 birds
their distinctive in-flight howl. (Rapid shifting of the IGVs contributes
to some of the ground hoots) In all models of the F-104 up to the S-model
(and I'm just not sure about the S, because I don't have much knowledge about
what they did on that bird's inlet), the two lower flaps, termed the "A"
group, open when the landing gear is retracted. With the A-flaps open, a total
of 44 square inch of bypass port area is exposed. In the F-104A with the -19
engine (again, I'm not sure what they did on the F-104S), the next two adjacent
flaps on each side, termed the "B" group (B-flaps), open automatically
when accelerating through Mach 1.8, and close automatically when decelerating
through Mach 1.7. On the NF-104A, Joe Jordan's F-104C, and presumably Wing
Commander White's CF-104A, the B-flaps were opened by a pilot operated switch.
The purpose of opening the flaps was to increase the mass flow through the
inlet ducts and thus reposition the inlet shocks to keep the duct from going
supercritical (swallowing the shock). This would allow you more margin to
fly beyond Mach 2.0 without risking a compressor stall. Joe Jordan commented
that when he opened the B-flaps at Mach 1.8, he noticed a momentary decrease
in acceleration, which he attributed to the sudden distortion of the airflow,
followed by increased acceleration. The increased acceleration was due to
a decrease in total inlet drag when the flaps were opened at high Mach. by Walt BJ, retired USAF F-86, F102, F-104 and
F-4 pilot F-104C 56-0885 On 14.December 1959, Joe Jordan reached 103,395.5 feet in an F-104C. He achieved
this record on his fifth and last flight of the record series. For the record
flight, he started his zoom at an indicated of Mach 2.353 at 39,575 ft., pulled
a maximum of 3.15 G, and rotated to a maximum climb angle of 49.5 deg. His
afterburner blew out at 70,000 ft. (indicated); he shut down the engine at
81,700 ft., and he coasted over the top at 54 KTS IAS. Joe's F-104C (56-0885) was modified in the following manner for the record
attempt: In addition to the modifications, the F-104C's 121 deg. Celsius CIT limit
was waived and the following restrictions were imposed for up to 15 flights: unknown from a discussion group 1.Lt Thomas Delashaw in spring 1962 with Mach 2.5+ and 92.000 ft I flew this mission at Hahn AB, Germany in the spring of 1962, our Squadron
was tasked with a special project to show the East Germans and their new MiG
21s what we were capable of as well as test a new classified U.S. intercept
radar capability. All of the squadron pilots had their own pressure suits,
Ray Holt and I were picked to fly the mission. We were told the speed restriction
(Mach 2.0) was removed and to go as high and fast as possible without damaging
the ZIPS or ourselves. The 104s were equipped with tip launchers and we each
flew the jets with our names on them; mine was 56-901. This was an officially
sanctioned mission and fully briefed. One photo I am attaching talks about
a "Kite Intercept" that was just an idea our public affairs officer came up
with to include it in Domestic U.S. newspapers. The photos are official USAF.
There is a whole lot more to this story, but the salient facts are contained
in the attached. Oh! By the way, the top speed was in excess of 2.5 as that
was the average speed, and yes the 'SLOW' light was on and it was still accelerating;
the insignias and paint on the jet were burned. By Tom "Sharkbait" Delashaw, in a personal e-mail
in 20018.
What was the T-2
Reset/Cutback?
- An F-104B tail assembly was installed to increase rudder area
- A shock cone extension was added to generate an additional oblique shock
- A switch was installed to allow the pilot to open the B-flaps
- A switch was installed to decrease minimum fuel flow from 500 pph to 250
pph
- T2 reset max RPM was reset from 103.5% to 104.5%
- The afterburner fuel control was trimmed to provide 10% higher max fuel
flow
- Five minutes above 120 deg C
- Three minutes above 160 deg C
- Max temperature 199 deg C
10.
What was the
fastest and highest operational flight known?
Tom "Sharkbait" Delashaw in front of 56-910 in 1962
11.
What was the difference
between the so called "Lil-D" and "Big-D" F-104D?
F-104D: (Lil-D): no extra tank, no in-flight refueling capability
F-104D: (Big-D): extra tank (630 pounds), in-flight refueling capability
F-104B Gun test: There once was one model, (one of a kind) and just for demo
and fitting purposes, which had a gun installed.
When It was decided it was not feasible, it was decided to remove the gun.
So the area behind the electronics compartment (unpressurized) became a metal
fuel tank, and the area where the gun had been installed, became room for
a metal tank.
And, more importantly, space was gained was the provision for in-flight refueling.
The F-104B was not single point refuelable, therefore not in-flight refuelable, as was the F-104A
By Mike Vivian and Ben McAvoy
USAFE Headquarters in Ramstein AFB had a bunch of offices under the Directorate
of Operations (DO).
Our offices were near Ramstein AB, Germany at Kapaun Air Station in Kaiserslautern.
The NATO Training Division was evaluating 9 NATO countries in the STRIKE role.
We went on plenty of “Tac Evals” for many countries and not just
F-104 bases.
Most of those bases had an American detachment which was co-located on the
base for the weapons security and maintenance. Additionally, the loading crews
and pilots of the host base were charged with the safe loading and delivery
of the weapons if necessary and if released. Allied Command Europe Directives
75-5 and 75-6 applied. These directives laid out the standardization necessary
for the host nation personnel and their weapons associated duties. To ensure
compliance with these directives, DOON team members made visits to each base
where we observed and certified crews. Lastly we were permitted to fly the
host nations aircraft to ensure SACEUR of the reliability and indeed mission
preparedness of both crews and aircraft. The DOON team was an all-USAF pilot
& weapons loader team assigned to USAFE which evaluated all NATO fighter squadrons
that had a nuclear weapons mission and used US nuclear weapons.
The translation of the NATO DOON Team is as follows:
DO = Director of Operations for United States Air Forces Europe (USAFE), Ramstein
AB, Germany (2 Star General)
O = Operations which was the coordination division for such things as Training,
Exercises, Tactical Evaluations, Tactics, etc.
N = Nuclear which did the evaluations (Written Exams & Flight Checks) of all
NATO fighter nuclear-capable squadrons.
We typically gave 1 or 2 check rides a day for 4 days with two DOON check
pilots.
There was also a Weapons Loader Evaluation Team which was a part of the unit
as well.
By Gene West, former USAF F-104A to F-104G pilot and Luke IP
13.
Why does the F-104S
have engine auxiliary inlet doors (EAID)?
EAID (engine auxiliary inlet door)
These doors are located on each inlet duct.
The doors are opened only during takeoff to provide an increased air supply
to the engine for added thrust.
The only engine that needed this provision was the J79-GE-19 installed in
the F-104S of the Italian Air Force.
A three position guarded switch labeled ENGINE AIR INLET DOORS is located
on the left side panel, between the UHF- and Autopilot-panel. The switch is
spring-loaded from the OPEN and CLOSE position to the AUTO-CLOSE, guarded
position. The switch is used to control the hydraulic selector valve in the
main landing gear wheel-well. After takeoff and with the inlet door switch
in AUTO-CLOSE, the inlet door circuit is automatically energized by a speed
sensing switch and the doors will close as airspeed reaches 280 ± 10 knots.
A landing gear ground-air safety interlock switch prevents the doors from
being opened in flight; however, if the AUTO-CLOSE system malfunctions, placing
the switch to the CLOSE position can close the doors.
An INLET DOORS OPEN indicator light located adjacent to the inlet doors switch
illuminates to indicate both doors are fully open and ready for flight. After
takeoff, as speed is increased to 280 ± 10 knots, the light will go out as
the doors begin closing.
The engine auxiliary air inlet doors unsafe warning light and the master caution
light will illuminate after takeoff when airspeed reaches 330 ± 10 knots if
the doors are not closed and latched. This light alerts the pilot to reduce
air speed below 340 knots IAS (Indicated Air Speed) and to close the doors
by use of the manual close position of the switch.
On the ground, the doors can be used for engine FOD (foreign object damage)
inspection.
by Theo Stoelinga, member of the "Zipper" team
Take-off with engine auxiliary inlet door open
14.
Why was the "0"
or "O" (depending on which source you read) serial presentation
used?
The "0" or "O" (depending
on which source you read) was used to indicate an aircraft over 10 years old.
Some say it means "obsolete", but I'm not at all sure that was official.
Now that aircraft are in service much longer, they don't use that prefix any
more. It wasn't part of the official serial, just something painted on the
aircraft, so 56-0784 would have still been the actual serial number, even
when 0-60784 was painted on it.
When another aircraft comes out 10 years later it would have the same
serial number; 66-0784 as opposed to 56-0784. So the first
"60-784" gets renamed 0-60-784. Guess they never figured airplanes
would be in service 10 years or more when the numbering system was set up.
Up to the Vietnam era, the serial presentation for USAF was to use the last digit of the fiscal and the last 4 of the serial. So 56-0784 was serialed 60784. Even if the sequence went over 10,000, the last 4 were used, so 52-10022, North American F-86D-50-NA Sabre, was serialed 20022. This style goes back to well before WW2. The planes that lasted more than 10 years had an "O" for obsolete added in front. I think that this was official policy. Thus the 0-60784, which would date the picture to 1966 or later. When camo came in, the presentation changed to a small FY and large last 3 as seen on many Phantoms. There are still some USAF planes (mostly tankers and transports) using the older scheme. The "O" for obsolete has been dropped, since almost all aircraft now last more than 10 years. (more than 20, more than 30, more than 40...)
Tech Order 1-1-4 (exterior finishes, insignia and markings applicable to USAF aircraft), it states "normally, the last five numerals of the aircraft serial number are used to compose the radio call number (tail number). If five are not available, the second numeral of the contract year shall be used, followed by necessary quantities of zero to produce five numerals. (i.e. s/n 59-12 would become 90012)."
By Jeff Rankin-Lowe
15. How did the BLC (Boundary Layer Control) system operate?
Boundary Layer Control - artificial lift created by engine air
Normally
the lift is physically created by high speed air from the jet's own speed.
The difference in the F-104, during landing with full flaps, is that lift
is created technically through blown air to the flaps.
Boundary Layer Control (BLC) uses air from the engine compressors last stage, the 17th stage. The air is ducted from high pressure air bleed ports through a pipe to the boundary layer control manifold in the root of the trailing edge flap. It then exits through very small nozzles which direct this high-pressure, high temperature air over the upper surface of the flap when the “LAND” flap position is used. The system operation is completely automatic. This is accomplished by a valve which is mechanically driven by the flap actuator; thus, the position of the valve always corresponds to that of the flaps. The valve remains closed from 0 to 15 degrees flap angle, for angles greater than 15 degrees, the valve moves until it is full open at 45 degrees.
That requires increase of power when the flaps transition beyond the 15 degrees “TAKEOFF” position towards the 45 degrees full down “LAND” position. There is a significant loss of thrust here and requires a high RPM setting to maintain proper sink rate or level flight when the flaps are in "LAND" position.
By Hubert Peitzmeier
