33:
209:
of the AA-1 Yankee, the loss of cruise speed amounted to 2 mph or 2% and there was no speed loss in climb. Impact on cruise speed of the Piper PA-28 RX (modified T-tail) was not measurable. For the
Questair Venture, "In carefully controlled performance tests, the penalty in cruise performance was found to be imperceptible (1 kt)".
515:
Zimmerman, NACA TN 539, 1935 , "Aerodynamic characteristics of several airfoils of low aspect ratio". "The preservation of unturbuled flow to very high angles of attack ... is apparently due to the action of the tip vortices in removing the boundary layer that ends to build up near the trailing edge
208:
Depending on the cuff length and shape, the leading-edge cuff can exert an aerodynamic penalty for the stall/spin resistance speed obtained, resulting in some loss of cruise airspeed, although sometimes too small "to be detected with production instruments". In the case of the best wing modification
162:
According to a NASA stall/spin report, "The basic airplanes: AA-1 (Yankee), C-23 (Sundowner), PA-28 (Arrow), C-172 (Skyhawk) entered spins in 59 to 98 percent of the intentional spin-entry attempts, whereas the modified aircraft entered spins in only 5 percent of the attempts and required prolonged,
153:
An important point is that the wing seems to be aerodynamically split in two parts, the inner stalled part and the outer part that behaves as an isolated low-aspect-ratio wing, able to reach a high angle of attack. The sharp discontinuity of the cuff is a key factor; all attempts by gradual fairing
138:
A 1979 NASA report explains that at high angles of attack the cuff discontinuity generates a vortex that acts as a fence, preventing the separated flow from progressing outboard. The lift slope has a flatter top and the stall angle is delayed to a higher angle. To reach high angles of attack, the
78:
The main goal is to produce a more gradual and gentler stall onset, without any spin departure tendency, particularly where the original wing has a sharp/asymmetric stall behaviour with a passive, non-moving, low-cost device that would have a minimal impact on performance. A further benefit is to
149:
Getting higher lift coefficients as a result of boundary layer removal is well known on propellers (centrifugal force causing an outward displacement of the boundary layer), or wings (boundary-layer suction). The leading-edge cuff inboard vortex and wing tip vortex act both to remove the boundary
171:
The most successful NASA experimental results were obtained on a quite low 6:1 aspect ratio wing (Grumman Yankee AA-1), with a DLE placed at 57% of the semi-span. As the vortices (inboard cuff and wing tip) are efficient on a limited span length (about 1.5 times the local chord), a DLE alone is
566:(Cessna 210), Leading-Edge Modifications, p.9, "The data for the outboard-droop configuration show significantly enhanced roll damping characteristics at the stall; however, unstable roll damping characteristics are not completely eliminated with the outboard droop alone."
199:
showed that the outboard leading-edge cuff alone was not sufficient to prevent a spin departure, the aircraft lacking directional stability at high angles of attack. With a ventral fin added, the aircraft entered a controlled spiral in lieu of a spin.
172:
unable to preserve enough outboard lift to keep the roll control in case of high aspect ratio wing. Wings of more than 8 or 9 aspect ratio features other devices to complete the cuff effect, for example stall strips (as used on the
126:
The effect of a central notch at mid-span on the wing maximum lift was demonstrated in 1976. Following the testing of different leading-edge modifications on models and full-sized aircraft NASA eventually selected the semi-span
122:
NASA led a general aviation stall/spin research program during the 1970s and 1980s, using model and full-scale experiments, seeking an effective means to improve stall/spin characteristics of general aviation airplanes.
490:
NACA TN 423, Weick, Fred E. Investigation of lateral control near the stall flight investigation with a light high-wing monoplane tested with various amounts of washout and various lengths of leading-edge slot.
368:
Location referred to half-span : Beech C23 0.54, Piper PA-28 0.55, Yankee AA-1 0.57, Cirrus SR20 0.61, Lancair 300 0.66, Questair
Venture 0.70, Cessna 172 0.71 - according to SAE TP 2000-01-1691, page
552:
July 1998, Wind Tunnel, Foiling stalls is the month's topic : "It has been found that the single-droop cuff configuration described in NASA TP 1589 is not sufficient to prevent spins on high ratio
146:
report about the effect of leading-edge slots of various lengths said, "this is an indication that the slotted portion on each tip of the wing operates to some extent as a separate wing".
139:
outboard airfoil has to be drooped, some experiments investigating "exaggerated" drooped leading edges. The physical reason for the cuff effect was not clearly explained.
623:
Flight
Investigation of the Effects of an Outboard Wing-Leading-Edge Modification on Stall/Spin Characteristics of a Low-Wing, Single-Engine, T-Tail Light Airplane
228:
Following aircraft were modified for experiments with the addition of an outboard leading-edge cuff as a result of NASA stall/spin research program :
753:
273:
75:. In most cases of outboard leading-edge modification, the wing cuff starts about 50–70% half-span and spans the outer leading edge of the wing.
850:
481:
NASA TP 1589 : "The mechanism by which the outer-panel lift is maintained to such improved stall/spin characteristics has been unclear".
1427:
1073:
575:
NASA TP 2722, "... an unsteady stalling and reattaching behavior occurring inboard on the wing upper surface as wing stall progressed."
780:
625: : "within the measurement accuracy, no difference was found in airplane drag for lift coefficients typical of cruising flight."
79:
lowering stall speed, with lower approach speeds and shorter landing distances. They may also, depending on cuff location, improve
635:
538:
405:
1467:
17:
1422:
1367:
1232:
1487:
564:
Wind-Tunnel
Investigation of a Full-Scale General Aviation Airplane Equipped With an Advanced Natural Laminar Flow Wing
471:
Wind-Tunnel
Investigation of a Full-Scale General Aviation Airplane Equipped With an Advanced Natural Laminar Flow Wing
1801:
843:
357:
1257:
289:
192:). In the case of the high aspect ratio Cessna 210 wing (AR =11:1), roll damping at stall was not as efficient.
1457:
1055:
150:
layer of the wing's outer section, helping this low-aspect-ratio virtual wing to achieve a higher stall angle.
1806:
132:
37:
1750:
585:
Investigations of modifications to improve the spin resistance of a high-wing, single engine, light airplane
525:
Addition of a fairing ... to eliminate the discontinuity reintroduced abrupt tip stall (SAE TP 2000-01-1691)
1740:
1581:
836:
757:
1462:
1417:
1108:
154:
to suppress the vortex and the positive effects of the modification reintroduced an abrupt tip stall.
1648:
1492:
1442:
303:
make use of leading-edge cuffs, in some cases in conjunction with such other aerodynamic devices as
1432:
985:
915:
806:
1760:
1735:
1497:
1477:
1402:
1292:
1262:
1237:
1103:
1068:
316:
824:
1775:
1576:
1472:
1297:
1113:
72:
610:
Effects of Wing-Leading-Edge
Modifications on a Full-Scale, Low-Wing General Aviation Airplane
68:
characteristics. Cuffs may be either factory-designed or an after-market add-on modification.
1755:
1673:
1663:
1168:
880:
232:
71:
A leading-edge cuff is a wing leading-edge modification, usually a lightly drooped outboard
1720:
1523:
1317:
1128:
1083:
784:
326:
244:
238:
492:
433:
8:
1699:
1606:
1322:
1030:
859:
195:
The case of high-wing configuration wing was different. Full scale testing of a modified
65:
57:
1407:
1387:
1382:
1356:
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980:
380:
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800:
353:
321:
1770:
1653:
1327:
1222:
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863:
293:
262:
256:
217:
The first use of outboard cuffs, other than on NASA research airplanes, was on the
185:
181:
828:
1780:
1745:
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1447:
1242:
890:
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1015:
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61:
1546:
280:
Leading-edge cuffs are used on 1900s high-performance light aircraft like the
1795:
1694:
1633:
1437:
1372:
1010:
990:
905:
655:
218:
221:
in 1978. They were wind tunnel tested in 1982, and later (1984) replaced by
107:
in technical reports on stall/spin resistance. In these reports and others
1730:
1658:
1621:
1601:
1591:
1566:
1531:
1312:
1282:
1252:
1218:
1198:
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1153:
1088:
955:
925:
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285:
163:
aggravated control inputs or out-of-limit loadings to promote spin entry."
53:
32:
1678:
1561:
1277:
1133:
281:
173:
111:
reports on the same object, "leading-edge cuff" expression was not used.
731:
458:
Reduction of stall-spin Entry
Tendencies Through Wing Aerodynamic Design
1668:
1556:
1551:
1507:
1502:
1337:
1272:
1247:
1203:
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196:
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1173:
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1005:
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910:
535:
Summary of results for spin attempts for four NASA research aircraft.
300:
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871:
222:
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1063:
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970:
445:
Spin
Resistance Development for Small Airplanes - A Retrospective
402:
Spin
Resistance Development for Small Airplanes - A Retrospective
80:
404:, SAE TP 2000-01-1691 or "Nasa Stall Spin Paper from 1970s, or
1118:
1025:
1000:
930:
749:
1541:
1143:
995:
703:
Sport
Aviation Nov. 88. Meyer et Yip, AIAA 89-2237-CP report.
429:(1979), "Wing cuff improves VariEze stalls" or more recent
143:
108:
41:
142:
Some much older reports gave some similar results. A 1932
166:
416:
Nasa TP 2011 (Yankee AA-1), Nasa TP 2772 (Cessna 210)
352:, page 144. Aviation Supplies & Academics, 1997.
858:
1793:
721:DOT/FAA/CT-92/17, AIAA/FAA Joint symposium on GA
114:Other authors use simply "cuff" or "wing cuff".
350:Dictionary of Aeronautical Terms, third edition
188:or segmented droop (as used on a NASA modified
844:
658:, NASA TP 2382 (1985) et NASA TP 2623 (1986)
36:A drooped leading-edge cuff installed on an
612:, Nasa TP 2011, Drag characteristics, p. 13
851:
837:
778:
598:Nasa's general aviation stall/spin program
443:H. Paul Stough III and Daniel J. DiCarlo,
742:
31:
344:
342:
14:
1794:
772:
748:
372:
167:Wing aspect ratio and location effects
832:
516:of the upper surface of the airfoil".
157:
781:"Description of the Horton STOL Kit"
754:"This beauty is more than skin deep"
339:
378:
24:
299:Several after-market suppliers of
131:(DLE) that was tested first on an
25:
1818:
817:
456:Kroeger, R. A.; and Feistel, T,
724:
715:
706:
697:
688:
679:
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628:
615:
603:
590:
578:
569:
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528:
519:
509:
496:
484:
475:
431:Wing Cuff Design for Cessna CJ1
270:(1987), high wing aspect ratio,
212:
203:
180:), "Rao slots" (as used on the
91:Leading-edge cuffs were called
1761:In-flight entertainment system
1458:Horizontal situation indicator
600:, Sport Aviation, January 1989
463:
450:
437:
419:
410:
394:
362:
105:modified outboard leading edge
86:
13:
1:
562:Murri, Jordan, Nasa TP 2772,
332:
133:American Aviation AA-1 Yankee
38:American Aviation AA-1 Yankee
27:Fixed aerodynamic wing device
1741:Environmental control system
447:, SAE TP series 2000-01-1691
381:"Questair Venture, Part Two"
7:
676:NASA CT 3636, NASA TP 2691
379:Cox, Jack (November 1988).
310:
10:
1823:
1418:Course deviation indicator
1109:Electro-hydraulic actuator
667:NASA TP 1589, Nasa TP 2011
117:
1708:
1687:
1649:Conventional landing gear
1620:
1516:
1351:
1217:
1054:
870:
587:, SAE Paper 891039 (1989)
259:, high-wing pusher (1986)
1802:Aircraft wing components
1433:Flight management system
247:modified (T-tail) (1981)
56:wing device employed on
1736:Emergency oxygen system
1498:Turn and slip indicator
1293:Leading-edge droop flap
1263:Drag-reducing aerospike
1238:Adaptive compliant wing
1233:Active Aeroelastic Wing
317:Leading-edge droop flap
307:and drooping ailerons.
1776:Passenger service unit
1577:Self-sealing fuel tank
1473:Multi-function display
83:control at low speed.
73:leading-edge extension
45:
1756:Ice protection system
1674:Tricycle landing gear
1664:Landing gear extender
881:Aft pressure bulkhead
233:Grumman American AA-1
35:
1807:Aircraft wing design
1721:Auxiliary power unit
1129:Flight control modes
823:Wing Vortex Devices
805:: CS1 maint: year (
327:Strake (aeronautics)
288:, which both gained
129:drooped leading edge
97:drooped leading edge
18:Drooped leading edge
1700:Escape crew capsule
1607:War emergency power
1478:Pitot–static system
1323:Variable-sweep wing
1031:Vertical stabilizer
787:on 21 November 2008
779:Horton Inc (n.d.).
58:fixed-wing aircraft
1408:Attitude indicator
1388:Airspeed indicator
1383:Aircraft periscope
504:Fluid Dynamic lift
460:, SAE paper 760481
427:Canard Pusher n°19
158:Stall/spin results
46:
1789:
1788:
1716:Aircraft lavatory
1453:Heading indicator
1398:Annunciator panel
1378:Air data computer
1288:Leading-edge cuff
636:"Spin Resistance"
548:Barnaby Wainfan,
322:Leading-edge slat
296:with the device.
186:vortex generators
50:leading-edge cuff
16:(Redirected from
1814:
1771:Navigation light
1751:Hydraulic system
1726:Bleed air system
1654:Drogue parachute
1328:Vortex generator
946:Interplane strut
853:
846:
839:
830:
829:
811:
810:
804:
796:
794:
792:
783:. Archived from
776:
770:
769:
767:
765:
756:. Archived from
746:
740:
739:
728:
722:
719:
713:
710:
704:
701:
695:
692:
686:
685:SAE paper 891039
683:
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423:
417:
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408:
400:Stough, DiCarlo
398:
392:
391:
389:
387:
376:
370:
366:
360:
346:
263:Questair Venture
257:Verilite Sunbird
239:Beechcraft C-23X
182:Questair Venture
21:
1822:
1821:
1817:
1816:
1815:
1813:
1812:
1811:
1792:
1791:
1790:
1785:
1781:Ram air turbine
1746:Flight recorder
1704:
1683:
1616:
1597:Thrust reversal
1521:
1512:
1483:Radar altimeter
1448:Head-up display
1358:
1347:
1243:Anti-shock body
1225:
1213:
1074:Artificial feel
1056:Flight controls
1050:
916:Fabric covering
866:
862:components and
857:
820:
815:
814:
798:
797:
790:
788:
777:
773:
763:
761:
760:on 26 July 2009
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89:
60:to improve the
28:
23:
22:
15:
12:
11:
5:
1820:
1810:
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1804:
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1786:
1784:
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1766:Landing lights
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1712:
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1689:
1688:Escape systems
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1681:
1676:
1671:
1666:
1661:
1656:
1651:
1646:
1641:
1636:
1630:
1628:
1626:arresting gear
1618:
1617:
1615:
1614:
1609:
1604:
1599:
1594:
1589:
1584:
1582:Splitter plate
1579:
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901:Cruciform tail
898:
896:Crack arrestor
893:
888:
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875:
868:
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855:
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841:
833:
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826:
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818:External links
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1154:Rudder pedals
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1011:Trailing edge
1009:
1007:
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991:Stressed skin
989:
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656:Rutan VariEze
652:
644:
643:whycirrus.com
637:
631:
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358:1-56027-287-2
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348:Crane, Dale:
345:
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297:
295:
294:certification
291:
287:
283:
275:
274:Smith Trainer
272:
269:
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261:
258:
255:
252:
249:
246:
245:Piper PA28 RX
243:
240:
237:
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219:Rutan VariEze
210:
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98:
94:
93:droop concept
84:
82:
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69:
67:
63:
59:
55:
51:
43:
40:as part of a
39:
34:
30:
19:
1731:Deicing boot
1659:Landing gear
1602:Townend ring
1592:Thrust lever
1567:NACA cowling
1532:Autothrottle
1524:fuel systems
1522:devices and
1313:Stall strips
1287:
1283:Krueger flap
1253:Channel wing
1199:Wing warping
1189:Stick shaker
1184:Stick pusher
1104:Dual control
1089:Centre stick
956:Leading edge
926:Flying wires
886:Cabane strut
789:. Retrieved
785:the original
774:
762:. Retrieved
758:the original
744:
735:
726:
717:
712:NASA TP 2772
708:
699:
694:AIAA 86-2596
690:
681:
672:
663:
651:
642:
630:
622:
617:
609:
605:
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592:
584:
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549:
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486:
477:
470:
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457:
452:
444:
439:
430:
426:
425:Burt Rutan,
421:
412:
401:
396:
384:. Retrieved
374:
364:
349:
298:
286:Columbia 350
279:
227:
216:
213:Applications
207:
204:Drag penalty
194:
170:
161:
152:
148:
141:
137:
128:
125:
121:
113:
104:
100:
96:
92:
90:
77:
70:
49:
47:
29:
1679:Tundra tire
1562:Intake ramp
1493:Transponder
1278:Gurney flap
1219:Aerodynamic
1134:Fly-by-wire
1016:Triple tail
736:grumman.net
596:H. Holmes,
305:wing fences
282:Cirrus SR20
174:Cirrus SR22
87:Terminology
54:aerodynamic
52:is a fixed
1796:Categories
1669:Oleo strut
1557:Inlet cone
1552:Gascolator
1518:Propulsion
1508:Yaw string
1503:Variometer
1359:instrument
1338:Wing fence
1273:Gouge flap
1248:Blown flap
1204:Yaw damper
1179:Stabilator
1164:Side-stick
1099:Dive brake
986:Stabilizer
961:Lift strut
951:Jury strut
333:References
268:Cessna 210
251:Cessna 172
197:Cessna 172
190:Cessna 210
178:Cessna 400
44:experiment
1644:Autobrake
1572:NACA duct
1547:Fuel tank
1537:Drop tank
1520:controls,
1403:Astrodome
1393:Altimeter
1258:Dog-tooth
1223:high-lift
1174:Spoileron
1159:Servo tab
1139:Gust lock
1094:Deceleron
1079:Autopilot
1036:Wing root
1021:Twin tail
1006:Tailplane
941:Hardpoint
911:Empennage
874:structure
550:KitPlanes
502:Hoerner,
301:STOL kits
253:X (1983),
223:vortilons
1612:Wet wing
1587:Throttle
1333:Vortilon
1194:Trim tab
1124:Flaperon
1114:Elevator
1069:Airbrake
1041:Wing tip
966:Longeron
936:Fuselage
872:Airframe
860:Aircraft
801:cite web
791:8 August
764:8 August
752:(2009).
386:8 August
311:See also
235:X (1978)
135:(1978).
1622:Landing
1413:Compass
1361:systems
1353:Avionic
1343:Winglet
1226:devices
1169:Spoiler
1064:Aileron
1046:Wingbox
971:Nacelle
921:Fairing
864:systems
553:wings."
506:, 12-24
118:History
81:aileron
1357:flight
1318:Strake
1149:Rudder
1119:Elevon
1084:Canard
1026:V-tail
1001:T-tail
931:Former
891:Canopy
750:Cessna
732:"Data"
356:
276:(1992)
241:(1980)
103:), or
1542:FADEC
1428:EICAS
1303:Slats
1144:HOTAS
996:Strut
639:(PDF)
62:stall
1624:and
1488:TCAS
1468:ISIS
1423:EFIS
1368:ACAS
1355:and
1308:Slot
1268:Flap
1221:and
1209:Yoke
981:Spar
906:Dope
807:link
793:2009
766:2009
388:2009
354:ISBN
284:and
176:and
144:NACA
109:NASA
66:spin
64:and
42:NASA
1463:INS
1443:GPS
1298:LEX
976:Rib
290:FAA
184:),
101:DLE
95:or
1798::
803:}}
799:{{
734:.
641:.
537:,
369:14
341:^
225:.
48:A
852:e
845:t
838:v
809:)
795:.
768:.
738:.
645:.
407:.
390:.
292:-
99:(
20:)
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