FORMULA V AIR RACING ASSOCIATION AIRCRAFT

FORMULA V AIR RACING ASSOCIATION
AIRCRAFT TBCHNICAL SPECIFICAnON
.
Revision 2.2 • JanuaI)' 19M
.
•~
SECnON2
AIRCRAFT TEOINICAL SPEGFlCAll0NS
FOR FORMULA. V AIR MONG
2.1
General InfonDation
2.1.1
The ~
of the Formula V dass is to provide a sale and imlovative
fr~e.work of moderate cost to the competitor in which to mnduct
spectator-pleasing dosed-mwse pylon air racing on a 2 mile rourse.
Safe racing is of ~ount
interest aJ\d all other goals and
considerations are seCxmdary.Only SlIfeaircraft and profident pilots
will mmpete.
A)
B) It is intended that Formula V aifcraft always be able to race on a 2
mile cowse, allowingitccess to a greater number of sites. It is the
intent of the rules tti8t the airaaft notiexceed 190 Mph, in straight
and level fljght.~ .'
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C) It is reco«nized'.that dynamic and iimovative individuals are
essential to lhe gro~qf
ihe spott. ThaefOJE, i~is the intent of the
rules that the stridFoiliwla ~~
expi sed herein be the
liJiUting factor aJId~.iiWdm~'latitude
for experimentation be
. allowed within. them.
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D) It Is assumed tba~raclns fdi. ~'dUlD\UIt
be perfoniled in the air
show setting with spo~
lAIPPCJrt.It is the irilent of the rules to
provide .raciJlB01 the ~urA.1nterest
to the spectator.
E) It is intended that the GlIIt of Formula V aircraft be kept moderate in
order to ~
the dus...
!bleto a ~
number of competitorB.It
shall therefore be the intent' of die rules to subordinate cost to all
other fact0i'8~ a determiJw\t of aircraft petfoimance.
2.1.2
In case of confucdftg or ~
d~
within this specification,
resolution or Interpretation Will be baled on the basic J)hilO8Ophical
pls of the FormUla V Air ~.
dus, and amen.:: In the follOwing
order of precedence (degree of hn~):
A)
(most important)
B) Falml!8l to all mmpetltors 0 LOwCost Oeasl important)
2.2
Rape
2.2.1
The ~ed
engbie for Formula V air racing is based on the air-<lllOled
flat-fOur cylinder configuration of automotive enable developed by
Volbwa~erk
AG, adapted for aircraft UlIE. MaxUnum displliCement
Is nOlftlnj1ly91.632cubic inches (1600 oc.)(see paragraph 2.2.7l). Bnglne
Installation is limited to tractor configurations.
2.2.2
Each individual owner, pilot, engine builder, and worker must beer in
mind that, In. adapting the Volkswagen-type automotive enlt1ne to
aircraft use, he is usiilg the engine in a manner not inten'iled or
designed for by VolkswBgenwerk .AG.The owner, P!lot. and mechanic
assume all rish in determining the suitability of the Volkswagen
engine or any components thereOf for aircraft use, and are responsible
for ensuring that aD modifications, changes, aJ\d additions made to the
engine in adapting it to aircraft use are performed in an airworthy
manner.
Induction - The enJdne induction system is free of restriction with the
ex~on
of the fonowing items:
No pump or blOwerto increase the induction air pressure is allowed.
Only aqtDient air and aircraft fuel are allowed Coenter the induction
syStem. No. other solid, UqUid,or gaseous substance may enter. the
induction system.
.
The indu~stem
may be insulated, or cooled using ambient air.
No other
of cooIirig the induction system is alloWed.
2.2.3
2.2.3.1
2.2.3.2
2.2.3.3
Carburetor - The carburetor is free of restridion with the exception of
the fOllowing ib!mS:
Any type carburetor is allowed. Only one carburetor is allowed, of
eitiier ~e
or dual barrel (throat,)type.
The carbUretor must. have a single restricting venturi .not exceeding
1.26 inches (32 mm.) diameter. A carburetor not meeting this rule due
to excessive venturi diameter shall have a restrietor ~ently
installed in the intake manifold to Umit total air-fuel mass flow. The
restrietor musth8ve • sinde round hole not 0ca!eding 1.26 inches (32
maL) inside diameter ana must be located adjacent to the carburetor
and in the manifold on the ~
side of the Carburetor. A carburetor
restric:torO1l'theupstream side 01 the fuel entry ~
is nOt ~cceptable.
The restrtetor (or CarburetOrventurl.1f a restridOr is not required) must
be easil~le
loti ~on.
.
.
Fuel In
on - Fuel inJeCtionlI}'lltemllwhich provide individual fuel
flow 10 each intake port are prohibited.
:
2.2.4
2.2.4.1
. 2.2.4.2
2.2.4.3
2.2.5
2.2.5.1
2.2.6
2.2.6.1
2.2.1
2.2.7.1
2.2.8
2.2.8.1
2.2.8.2
2.2.9
Crankcase - The crankcase is free of restriction with the fOllowing
exceptions:.
.
. .
.
The Crankcase must be "VoUcswagen-manufacmred .lntemal baffling
in the crankcase may be lClded to oontrol oil slosh. .
R
Crankshaft • the aanbhaft 111 free of restriction with the fOllowing
~ons:
.
The ilwdmwn stroke ls2.716 inches (69 mm.) (+ 0.0196 inch [0.5 mm.]
measurement tolerance)
.
CyUnders - cyUnden are free of restriction with the following
~ons:
The lnaximum sw.ePtvolume 01 any cylinder is 24.408cubic inches (400
oc.) (no additional ~t
to1er8nce).
CvUnder Heads - Cylinder heads are free of restriction with the
following exoepdons:
The cylfnder neads must be "Volkswagen-manufactured
Bither
sinde-port or dual-por:theads may be used.
Eitner one or t\Yospark plugs per cylinder are allowed.
R
•
Pistons - l'istonll are free of restriction. Any type of commerciallyavailable pulton ~
may be used. .
Camshaft - the camihaft is free of restriction.
2.2.10
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2.2.11
Valves - valvei are free of resbiction.
2.2.12
I~tion System • The ignition system is free of resbict10n with the
following exceptions:
.
Ignition timing must be non-adjustable in flight
Any type of mmmercially-avalliible spark plugs are allowed.
2.2.12.1
. 2.2.12.2
2.2.13
En~l! Retention Cables. of a Dtinimum diameter of 3/16 in. muSt be
fitted in accordance with Appendix A
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2.2.14
Power Transmission • The propeller' of the aircraft must be driven at
crankshaft speed. Ulie of an extension shaft is allowed; any extension
shaft coupling devices used must be of a type which will not cause an
increase of torque applied to the propener over the direct drive
configuration.
2.2.15
Cooling. The engine must be cooled only by ambient ~. No other
substance may be used to cool the engine. Ifngine heat may also be
dissipated Viaan oil oooIer•
2.2.16
. Substances used for.Starting Aisistance ~ The ~
aid in starting the engine is p~hlbited.
. '.
of any substance to
2.2.17
Fuel ~ Only .stUidardunmiXeci ahcraft fuel available from an on-site
common source is aUow~. NOthing may be added to the fuel, air, or
fuel/air mixture used in the engine.. At any time a fuel sample may be
taken from any or all ~
from some logical and practiCal pI!blt in
the fuel system. This ~Ie
may be analyzed, or lI!lIlI!Qbythe Ti!d\nical
Committee or sealed and sent to an acxreQitedfadlity for analysis.
2.2.18
Oil - Only aircraft oll, racing on, or c:oauru;:::rIecf.adeoil which passes
SAE ratirig may be used. AI[ oil must be in
ClIIlS and be avidlable
to all. Onfy oil additives which when added to the oil will increase its
lubricating QUalitlesand not inaease the combustlon PJwatlea of the
oil and th:eluel-air ratio in.the combustion chamber and appioved by
the Technical Committee and available to all, are alloWed. Any
additives must be SDedfled '~::a:les
of all the additives used must
be avallable to the 1'.10'1
tift befOre Us&At any time an oil
sample may be taken from any or all.airplanes from eome l~cal and
praCtical ~t
in the oil system. ThiSsample may be analyzed or lI!lIted.
. l?Ythe Tei:IInkal Committee or sealed and sent to an aca1!dited fadlity
roranalysis.
.
2.2.19
Oil System - OIl coolers if used must utilize ambient air for cooling.
'Ql.eremust be no aocetl&from the cockpit to the oil ~tem other than
the oil pressUre line, which must be cOnnected from the c:rankase to
the indicator only. A crankcase breather with or without oil separator
may be installed.
.
Fire Extinguisher Sys~ - Fire extinguisher ~stema Installed on
board the iin:raft are permitted only if equi~
with • seal over the
~
nozzle such that use of the fire ex6Dguisher wiD rupture the
seal. In-flight use of the fire extinguisher system shall automatically
•• ••
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the airaaft from the qualifying a~
whia\ the use occurred.
2.2.21
or race heat during
Misce1Ja~eous - All other engine components not specified are free of
restriction.
Definiqon of "Volbwagen-Manufactured"It is rl!CORlllzedthat man)'
diffei'ent manufacturers provide (Xlmponents whicl\ are capable of
in
assembled
into a Volkswagen-type
engine. Where the
s
cation calls !OF a component to be "Volkswagen-manufactured",
e intention is to define the m;rrent
as having been. designed and
manufactured ~ VoIkswagenw
AG, or any wOIidwi4e Volkswagen
subsidiary, such as Volkswagen factories in Btazll, Mexico, Ni~,
etx:.
For purposes
of identification, .. the component
specified
as
"VolkSwagen-manufactured" must retain the "Volbwagen" or "VW"
logo or VolbwagE;n origiJ.UIlpart number as affixed to the m~ent
dUring the origirial manUfactUring process. Only cmn~ts
from, or
. compatible with. the Volkswagen Type 1,2, or 3 series of air-cxloled flatfour cylinder enginelIare l1loWed..
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a
2.3
Airplme mel Pilot WeJsht
2.3.1
The empty weipt of the airplane must be a minimum of 450 pounds
with full on ana no fueL Any ballast added to bring. the aitpIan:e up to
the minimum weight must De attached solidly to. the airfI'aJne.
2.3.2
Pilot weight must be a minimum of 170 pounds ready for flight. If
flown by a pilot of 1eIeer ~t,
balIut must be carrieclfo make up the
difference rn weight to 170 poun~ Sum ballast must be removable,
and adequately sicured to t1Ie airframe. In the case that a parachUb! is
used as ballast, this paragraph applies with the ~tfon
that the
parachub! shall be secUred to the pilot instead of the airfriune.
%.4
PwpeIler
2.4.1
The propeller must be fixed pitch in operation. It must have only two
blades.
.
2.4.2
With the ~
of any airaaft equipPed with a metal propeller that
has ~dpatec1
without a change m ownership in a teCX)~
FonriWa V iir race prior to Jan. 1st., 1985, the use ora metal propeller is
prohibib!d.
2.5
Winp
2.5.1
A minimum of 75 ~
feet of wing area is ~ed.
Wing area is
measured to include that area dlspfaced by the fuselage, lNt not
including fillets or stall strips. A fillet is any deviation froIn the basic
pl~orm
that. starts inboard of 25,. semi-span. Flaps are permitted;
wmg area must be figured with the flaps retracted. The taper ratio (i.e.
root moni divided tiY tip moni) shall not exceed 2.0 TI\e wing span
cannot exceed 22 feet. Aiicraft of canard or multiple wing conflguralion
are not l1lowed.
D_
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The root chord is defined as the wing chord at the point where the
wing plariform, not including fillets, intersects the fuSela~ structure.
The tip chord is defined as the wing chord at a point 24 inChes in from
the extreme outboard tip of the wing.
2.5.2
Ailerons must be balanced in a manner which will demonstrate
ab5erlce of flutter over the entire speed range of the aircraft (le. up to
1.2 Vh).
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2.53
The minimum wing .thidcness for cantilever (unbraced) wina designs
is 12 'l(, of chord. The minimum wing thickness for externany-braCed
wing designs is 1.8 'l(, of dlmd. . '.
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2.5.4
Wing leading
rearWard.
2.6
I.andiD8 Gear ..
2.6.1
Lan~g
~
must be non-retractable. It must be fixed in position,
len~
and angle, with the exception of minor deflection fOr shock
absOrbing purposes
.
2.6.2
The aircraft: must have two wheels and tires of standard 5.00 X 5 type or
larger, Which must both touch the ground when the aircraft is at rest.
2.63
Wheelbrakea'are
edge sweep shall not exceed 5 degrees
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forward
or
requiied on ~th mai8 w~.
2.6.4
.The aircraft must have a ateerable au,oUary wheel with a non-metallic
tire, which must be fixed to the aircraft and non-retractable in flight.
The crclsa section (diameter times width) of the a"xlUary wheel must
be a minimum of 2.0 in2• ..
.
2.6.5
When conventional (tailwheel) type landing gear is used. the point of
contact of the main wheels must be at least 15 degrees forwariI of the
C.G. of the aircraft when the longitudinal axiS of the aira'aft is
horizontal and the aircraft: is at racing gross weight.
2.7
Vision
2.7.1
When seated in. the cockpit with crash helmet. eeat belt and shoulder
hamess on, the. pilot must be able to lICIIIl a field of vision measured
from a datum plane parallel to the aira'aft's longitudinal axis of at
least:
.
5 d~ ! e s down over nose.
.
20 d~ees field of vision down over the wing IeadlnIJ edge. This must
be demonstrated
for each pilot of a sp!cific lW'ccaft to ensure
compliance.
.
45 degrees UJ'Wll!d
270 cfegaees in the horizontal plane (45 degaees to the rear to left and
right).
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Any obstructions In the field of vision must be of a minor nature.
2.7.1.1
2.1.1.2
2.7.1.3
2.7.1.4
2.7.1.5
2.7.2
Definition of longitudinal axis - in the absence of a dearly defined
longitudinal axis reference externally visible on the aira'aft and
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Provision must be made such tNt all fuel can be easily drained from
the ainnit.'
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2.11.2
The airaaft must carry at takeoff for all race heats or ~ng
attempts iI minimum of 5 US. gallons of fuel. all of which is Usable.
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2.12
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2.12.1
Center oi Gravity location at nlCing gro.saweight must faD between 8 %
to 25'1> of MAC of"Witlg unleu deviationi are permitted by the
Technical Director. Aira6ft operatinlt at m aft of 25" may be ~
to cumply with Procedural and Safety Rule Para~aph 2.' at the
disa'etion of the TeduUcal Director. Mmmum allowabre aft CG limit
under any cirCUlNltana!sis 3q')i~
2.13
MateriaIa ••••• Wcnkmarithlp , ,
~
2.13.1
2.1f
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Mat:erla1sand worJananalllb muSt -conform to ahi:raft standards or
, equivalenl. ,The T~Cak
Committee is empowued to refuse
~
tiltfly, attewpt to pal ~~
or to auaUfvan airaaft"
Whidt in their ~
.•. not up to
yeafe alandUds in either
materWa; WQI'=~' detail design. or Q)ndltion. ThIs applies to
new, modified.
.
ell' damapd iirc:raft.
RM;e,Namber,
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2.14.1
J.
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Bach aircraft partidpatiJlg in. a Formula V raa! must have a race
number. ThIs number must be applied to both aides of the fuselage
between winp and' taU.or for airCrlIftWithout a amventiOll81fuselage,
the race number, Il\U8l be ,applied' to both sides of' the vertical t8il
surfaces. All digits oi the race number must be at least 12 in. hiaIL The
race number must be'~
~
view!cl &om adistana! of 500 feet
froJn the side of the:a1rCi'aft.Use 'of the entire nWnerical pOrtion of the
aira'aft's Naticmal ~
number as a race number is a.CXleptable,
provided the nmneriQl field meets'the si2ieand
cxmatraints
Ciescribedabove. Bach alrcraft's race number wU11le
gned by the
Formula V class Sea«ary. .
~a:r.
2.15
AJrcraft FIDfah ••••• Appeaz ••• af'
2.15.1
The aircraft shall: be attractivel~ted
in a gloss finish. The color
scheme must have at leut two'
cu1ors,or one overall color and
a trim color. No silver undercuat, pq.tet or unfinished lIWfacea shall
be perm!tted on major airaaft components, exce~t for temporary
r~iin.
Determination of 'attractively fainted' sh811 be at tl\e sore
diScretion of the Board' of Directon 0 the Formula., V Air Radng
Association. Inc:.
2.15.2
Alliettez:ing and graphics~
the aircraft sba11be sub\eCt to the
Of the lkWd
1'8 of the Formula V A1r Racing
ation, Inc:..Lettering and! or graphics not in good taste or
otherwise Wl600:ptable wilf not be perii\itIJecL.
.~ v,.
%~:;~rl
acceptable to the Technical Committee, the longitudiJull axis will be
(Xnwdered parallel to the wing chord at 3/8 wing semi-span.
.
2.8
Noee-Over Structure
2.8.1
Substantial protection for the pilot other than the fin must be provided
either fore or aft of the coCkpit. This structure must not obstruct
forwird visibility. The nose-over structure must be made of 4130
Chrome-moly aircraft tubina; it must be attached to the primary
structure of the aircraft; and It must extend higher then the top of the
pilot's h~eted head.
2.9
COr\pit
2.9.1
The minimumc:ockpit height, measured vertically iii. level f1i~t
attitude from the highest point iJlside the canopy down to a polnt
where the fuselage structure restricts the possi6fe seat width 10 16
inches must be at least 36 Inches. lThis point 36 Inches below the
canopy may be below the actual instaUed seato) This must be readily
measurable with aJD:lD\onmeasuring tools or by use of ~
owner
supplied tools. It ls the owner's risponsibUi~ to proVide proof of
compliance. This may be required at any-race. (Measurement tolerance
is 1f4 inch.]'
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2.9.2
The minimum inside coc:Icpltwidth, measured at the back of the seat
within a range of between 12 to 18 inches below the inside of the
canopy must be, at some point within this raJ18e,at least 20 inches.
2.9.3
The ~t
must be deslgued to accommodate a pilot of 110 lb. dressed
for flight and wearing a Crashhelmet and parachute.
.
2.9.4 .
The cockpit must be equlPJ)ed with a seat belt and shoulder harness.
This harness must be attached to the primary structure of the aircraft.
. ..
Aircraft desiped to aexmllD\odatetile pilot in a prone position are not
permitted.
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2.9.5
2.9.6
The cockpit canopy must nave a means of opening from both the
outside and the inside of the aira'aft in case of an emergency. A
desaiption of the canopy opening POC£dure shall be Installed on the
exterior of the ainraIt. next to the canOpy releese.
.
2.10
RequJrecl InstramentatiCm.
2.10.1
The aircraft must be fitted With a remJ'd!ng accelerometer (G meter)
~0!U'ted on or near the Instrument panel Within the pUot's range of
VISion.
2.11
Fuel Tank
2.11.1
The fuel tank or tanks must have a total minimum usable capacity of
10 U.S. gallons. All fuel tanks shall be accessible for ~on.
There
must be no access from the cockpit into the fuel tank or tanks.
'0-.
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'1'__ ."""'.
215.3
The &iraaft shall ~ly
with all the sponsor lettering and logo
requirements as set
by the Board of Directors of the Formula V
Air Racing Association, Inc.
.
215.4
Aircraft not appropriately painted or marked will not be permitted
onto the racin8 Siteor to lie publicly displayed.
2.16
FiIMIi Aircnft
2.16.1
In a situation where insuffident legal ral:eJ)Ianesto fill the entry field
are pi sent. BIl-in aircraft with larger d!sPlacementVW engines may
be6oa!pted for the mnainingopen grid pOsitions. Fill-in a1rcraft are
exemptid from the requirements of ~graphs
2.2.4.1, 2.2.4.2, 22.6.1,
2.2.7.1 and 2.2.&.1 of this spedftc:ation ONL-Y; all other requirements
must be.annpUed with. Each aircraft entered as a BIl-in entry mUst be
declared as sUchbefore ~race technic:aUnspedion begins. .
2.16.2
_For purposes of distribution of c.:e, money, trophies, or other
remuneration, fill-in aircraft must
positions beh1nd the slowest
legal partidpant. instead of their actUal race finishing position.
NatioriillltlCDds are DOtrecognized for
.
, fill-in airaaft.
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REVISION HISTORY
Rev. 0-
_Issued February 1965.
Rev. 1.0-
Issued F~,
1986. Completely revised uslng format of the 1981
FAI. Pormula One rules. Major Changes incluae: Engine - removed
requirement for stock carburetor; adeled car~r
intake restrictor
requiiement; provided- ;lIUnplified' measurement- of major powergenerating componen~ Jiliftame -- added 400 lb. empty weidtt
- requirement; disallowed ~ use of a metal FOJM!ller(with -pndfatlier
clause exempting' Wittman'. N3259); addeCl requirements for 'fill-in'
entries.
.: : ..' ~.';./1~
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t ...
Rev. 1.1 -
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'.':~'II~:;l
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Issued April/l986..l~esta~ tilt ClilCkplthept and width requirements
to cal1 for outside measurement rather than inside measurement;
addedrequbement for~
tnunber:" -- -- ._ ", ~'." ,;,"
._,";" .... ~..~.t;;
.:."
' .. ", •.
Rev. 2.0-
Issued Juuaryl991-.
Revised purpose _of class; deleted metric
dimensiOning;- elimlnAted - ~tier.prop
- confiSW'ationS; restated
carburetor restrietor; added neW restrairits on wmg span, taper and
minimum thickness; eliminated canard configurations; adeled new
restraints on tall volume; revised cockpit -vfaibllity ~uirements;
revised CIDCkplt
helJdtt and width requireDienllland added &e4tbotlODt
width; rewed C' of G requirements; moved flight and pUot
requirements to Procedural Rules; elimlrtated Appendii A (carbuJ'etor
restrictor drawing); revised Appendix B (enpe -retention cable
drawing); revised Appendix C (whig area meaaureutent).
Rev. 2.1 -
Issued January 1992.Added requirement !or G meter; added paragraphs
on aircraft finlsh and appearance.
Rev. 2.2
Issued Janu.arf 1994.Chan~2.3.1 and 2.3.2 airframe and pilot ballast
to allow ballast to be locatid anrwJu!r'e within aira'aft; deleted 2.6 Tail
Volume (md renumbered aD fOllowing paragraphs); added to 2.10.6
~ulrement for label on extemal canopy releUei changed 2.13 C of G
location to provide more rearWard CG.
Appendix A • EDslne ReleiitioD Cable IDsIaDatioa:
••••
ll ••v ?? _Ta" 1QQ4
2-10
r.
,
AppencUxB.
5 <leg. maxfwd. or aft
leading
edge
sweep
•••••-
Raps to be
~6bid&d
. 22 ft. max.
25%
_.
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'0 __
"''''
9 __
.~6