22:
198:
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)".
504:
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
197:
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
151:
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,
142:
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
127:
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
67:
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
138:
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
160:
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
555:(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."
188:
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.
161:
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
115:
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
111:
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.
479:
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.
357:
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
541:
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
135:
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".
128:
outboard airfoil has to be drooped, some experiments investigating "exaggerated" drooped leading edges. The physical reason for the cuff effect was not clearly explained.
612:
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
217:
Following aircraft were modified for experiments with the addition of an outboard leading-edge cuff as a result of NASA stall/spin research program :
742:
262:
64:. 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.
839:
470:
NASA TP 1589 : "The mechanism by which the outer-panel lift is maintained to such improved stall/spin characteristics has been unclear".
1416:
1062:
564:
NASA TP 2722, "... an unsteady stalling and reattaching behavior occurring inboard on the wing upper surface as wing stall progressed."
769:
614: : "within the measurement accuracy, no difference was found in airplane drag for lift coefficients typical of cruising flight."
68:
lowering stall speed, with lower approach speeds and shorter landing distances. They may also, depending on cuff location, improve
624:
527:
394:
1456:
1411:
1356:
1221:
1476:
553:
Wind-Tunnel
Investigation of a Full-Scale General Aviation Airplane Equipped With an Advanced Natural Laminar Flow Wing
460:
Wind-Tunnel
Investigation of a Full-Scale General Aviation Airplane Equipped With an Advanced Natural Laminar Flow Wing
1790:
832:
346:
1246:
278:
181:). In the case of the high aspect ratio Cessna 210 wing (AR =11:1), roll damping at stall was not as efficient.
1446:
1044:
139:
layer of the wing's outer section, helping this low-aspect-ratio virtual wing to achieve a higher stall angle.
1795:
121:
26:
1739:
574:
Investigations of modifications to improve the spin resistance of a high-wing, single engine, light airplane
514:
Addition of a fairing ... to eliminate the discontinuity reintroduced abrupt tip stall (SAE TP 2000-01-1691)
1729:
1570:
825:
746:
1451:
1406:
1097:
143:
to suppress the vortex and the positive effects of the modification reintroduced an abrupt tip stall.
1637:
1481:
1431:
292:
make use of leading-edge cuffs, in some cases in conjunction with such other aerodynamic devices as
1421:
974:
904:
795:
1749:
1724:
1486:
1466:
1391:
1281:
1251:
1226:
1092:
1057:
305:
813:
1764:
1565:
1461:
1286:
1102:
61:
599:
Effects of Wing-Leading-Edge
Modifications on a Full-Scale, Low-Wing General Aviation Airplane
57:
characteristics. Cuffs may be either factory-designed or an after-market add-on modification.
1744:
1662:
1652:
1157:
869:
221:
60:
A leading-edge cuff is a wing leading-edge modification, usually a lightly drooped outboard
1709:
1512:
1306:
1117:
1072:
773:
315:
233:
227:
481:
422:
8:
1688:
1595:
1311:
1019:
848:
184:
The case of high-wing configuration wing was different. Full scale testing of a modified
54:
46:
1396:
1376:
1371:
1345:
1256:
1197:
969:
369:
1704:
1441:
1386:
1366:
1296:
1291:
964:
789:
342:
310:
1759:
1642:
1316:
1211:
934:
909:
852:
282:
251:
245:
206:
The first use of outboard cuffs, other than on NASA research airplanes, was on the
174:
170:
817:
1769:
1734:
1585:
1506:
1471:
1436:
1231:
879:
1137:
1004:
1754:
1614:
1331:
889:
884:
50:
1535:
269:
Leading-edge cuffs are used on 1900s high-performance light aircraft like the
1784:
1683:
1622:
1426:
1361:
999:
979:
894:
644:
207:
210:
in 1978. They were wind tunnel tested in 1982, and later (1984) replaced by
96:
in technical reports on stall/spin resistance. In these reports and others
1719:
1647:
1610:
1590:
1580:
1555:
1520:
1301:
1271:
1241:
1207:
1187:
1177:
1172:
1142:
1077:
944:
914:
874:
274:
152:
aggravated control inputs or out-of-limit loadings to promote spin entry."
42:
21:
1667:
1550:
1266:
1122:
270:
162:
100:
reports on the same object, "leading-edge cuff" expression was not used.
720:
447:
Reduction of stall-spin Entry
Tendencies Through Wing Aerodynamic Design
1657:
1545:
1540:
1496:
1491:
1326:
1261:
1236:
1192:
1167:
1152:
1087:
949:
939:
293:
256:
239:
185:
178:
166:
1714:
1632:
1560:
1525:
1381:
1162:
1147:
1127:
1082:
1067:
1024:
1009:
994:
929:
899:
524:
Summary of results for spin attempts for four NASA research aircraft.
289:
1627:
1600:
1575:
1341:
1321:
1182:
1112:
1029:
954:
924:
860:
211:
1401:
1052:
1034:
959:
434:
Spin
Resistance Development for Small Airplanes - A Retrospective
391:
Spin
Resistance Development for Small Airplanes - A Retrospective
69:
393:, SAE TP 2000-01-1691 or "Nasa Stall Spin Paper from 1970s, or
1107:
1014:
989:
919:
738:
1530:
1132:
984:
692:
Sport
Aviation Nov. 88. Meyer et Yip, AIAA 89-2237-CP report.
418:(1979), "Wing cuff improves VariEze stalls" or more recent
132:
97:
30:
131:
Some much older reports gave some similar results. A 1932
155:
405:
Nasa TP 2011 (Yankee AA-1), Nasa TP 2772 (Cessna 210)
341:, page 144. Aviation Supplies & Academics, 1997.
847:
1782:
710:DOT/FAA/CT-92/17, AIAA/FAA Joint symposium on GA
103:Other authors use simply "cuff" or "wing cuff".
339:Dictionary of Aeronautical Terms, third edition
177:or segmented droop (as used on a NASA modified
833:
647:, NASA TP 2382 (1985) et NASA TP 2623 (1986)
25:A drooped leading-edge cuff installed on an
601:, Nasa TP 2011, Drag characteristics, p. 13
840:
826:
767:
587:Nasa's general aviation stall/spin program
432:H. Paul Stough III and Daniel J. DiCarlo,
731:
20:
333:
331:
1783:
761:
737:
361:
156:Wing aspect ratio and location effects
821:
505:of the upper surface of the airfoil".
146:
770:"Description of the Horton STOL Kit"
743:"This beauty is more than skin deep"
328:
367:
13:
288:Several after-market suppliers of
120:(DLE) that was tested first on an
14:
1807:
806:
445:Kroeger, R. A.; and Feistel, T,
713:
704:
695:
686:
677:
668:
659:
650:
638:
617:
604:
592:
579:
567:
558:
545:
531:
517:
508:
498:
485:
473:
464:
420:Wing Cuff Design for Cessna CJ1
259:(1987), high wing aspect ratio,
201:
192:
169:), "Rao slots" (as used on the
80:Leading-edge cuffs were called
1750:In-flight entertainment system
1447:Horizontal situation indicator
589:, Sport Aviation, January 1989
452:
439:
426:
408:
399:
383:
351:
94:modified outboard leading edge
75:
1:
551:Murri, Jordan, Nasa TP 2772,
321:
122:American Aviation AA-1 Yankee
27:American Aviation AA-1 Yankee
16:Fixed aerodynamic wing device
1730:Environmental control system
436:, SAE TP series 2000-01-1691
370:"Questair Venture, Part Two"
7:
665:NASA CT 3636, NASA TP 2691
368:Cox, Jack (November 1988).
299:
10:
1812:
1407:Course deviation indicator
1098:Electro-hydraulic actuator
656:NASA TP 1589, Nasa TP 2011
106:
1697:
1676:
1638:Conventional landing gear
1609:
1505:
1340:
1206:
1043:
859:
576:, SAE Paper 891039 (1989)
248:, high-wing pusher (1986)
1791:Aircraft wing components
1422:Flight management system
236:modified (T-tail) (1981)
45:wing device employed on
1725:Emergency oxygen system
1487:Turn and slip indicator
1282:Leading-edge droop flap
1252:Drag-reducing aerospike
1227:Adaptive compliant wing
1222:Active Aeroelastic Wing
306:Leading-edge droop flap
296:and drooping ailerons.
1765:Passenger service unit
1566:Self-sealing fuel tank
1462:Multi-function display
72:control at low speed.
62:leading-edge extension
34:
1745:Ice protection system
1663:Tricycle landing gear
1653:Landing gear extender
870:Aft pressure bulkhead
222:Grumman American AA-1
24:
1796:Aircraft wing design
1710:Auxiliary power unit
1118:Flight control modes
812:Wing Vortex Devices
794:: CS1 maint: year (
316:Strake (aeronautics)
277:, which both gained
118:drooped leading edge
86:drooped leading edge
1689:Escape crew capsule
1596:War emergency power
1467:Pitot–static system
1312:Variable-sweep wing
1020:Vertical stabilizer
776:on 21 November 2008
768:Horton Inc (n.d.).
47:fixed-wing aircraft
1397:Attitude indicator
1377:Airspeed indicator
1372:Aircraft periscope
493:Fluid Dynamic lift
449:, SAE paper 760481
416:Canard Pusher n°19
147:Stall/spin results
35:
1778:
1777:
1705:Aircraft lavatory
1442:Heading indicator
1387:Annunciator panel
1367:Air data computer
1277:Leading-edge cuff
625:"Spin Resistance"
537:Barnaby Wainfan,
311:Leading-edge slat
285:with the device.
175:vortex generators
39:leading-edge cuff
1803:
1760:Navigation light
1740:Hydraulic system
1715:Bleed air system
1643:Drogue parachute
1317:Vortex generator
935:Interplane strut
842:
835:
828:
819:
818:
800:
799:
793:
785:
783:
781:
772:. Archived from
765:
759:
758:
756:
754:
745:. Archived from
735:
729:
728:
717:
711:
708:
702:
699:
693:
690:
684:
681:
675:
674:SAE paper 891039
672:
666:
663:
657:
654:
648:
642:
636:
635:
629:
621:
615:
608:
602:
596:
590:
583:
577:
571:
565:
562:
556:
549:
543:
535:
529:
521:
515:
512:
506:
502:
496:
489:
483:
477:
471:
468:
462:
456:
450:
443:
437:
430:
424:
412:
406:
403:
397:
389:Stough, DiCarlo
387:
381:
380:
378:
376:
365:
359:
355:
349:
335:
252:Questair Venture
246:Verilite Sunbird
228:Beechcraft C-23X
171:Questair Venture
1811:
1810:
1806:
1805:
1804:
1802:
1801:
1800:
1781:
1780:
1779:
1774:
1770:Ram air turbine
1735:Flight recorder
1693:
1672:
1605:
1586:Thrust reversal
1510:
1501:
1472:Radar altimeter
1437:Head-up display
1347:
1336:
1232:Anti-shock body
1214:
1202:
1063:Artificial feel
1045:Flight controls
1039:
905:Fabric covering
855:
851:components and
846:
809:
804:
803:
787:
786:
779:
777:
766:
762:
752:
750:
749:on 26 July 2009
736:
732:
719:
718:
714:
709:
705:
700:
696:
691:
687:
682:
678:
673:
669:
664:
660:
655:
651:
643:
639:
627:
623:
622:
618:
609:
605:
597:
593:
584:
580:
572:
568:
563:
559:
550:
546:
536:
532:
522:
518:
513:
509:
503:
499:
490:
486:
478:
474:
469:
465:
457:
453:
444:
440:
431:
427:
413:
409:
404:
400:
388:
384:
374:
372:
366:
362:
356:
352:
336:
329:
324:
302:
204:
195:
158:
149:
109:
78:
49:to improve the
17:
12:
11:
5:
1809:
1799:
1798:
1793:
1776:
1775:
1773:
1772:
1767:
1762:
1757:
1755:Landing lights
1752:
1747:
1742:
1737:
1732:
1727:
1722:
1717:
1712:
1707:
1701:
1699:
1695:
1694:
1692:
1691:
1686:
1680:
1678:
1677:Escape systems
1674:
1673:
1671:
1670:
1665:
1660:
1655:
1650:
1645:
1640:
1635:
1630:
1625:
1619:
1617:
1615:arresting gear
1607:
1606:
1604:
1603:
1598:
1593:
1588:
1583:
1578:
1573:
1571:Splitter plate
1568:
1563:
1558:
1553:
1548:
1543:
1538:
1533:
1528:
1523:
1517:
1515:
1503:
1502:
1500:
1499:
1494:
1489:
1484:
1479:
1474:
1469:
1464:
1459:
1454:
1449:
1444:
1439:
1434:
1429:
1424:
1419:
1414:
1409:
1404:
1399:
1394:
1389:
1384:
1379:
1374:
1369:
1364:
1359:
1353:
1351:
1338:
1337:
1335:
1334:
1329:
1324:
1319:
1314:
1309:
1304:
1299:
1294:
1289:
1284:
1279:
1274:
1269:
1264:
1259:
1254:
1249:
1244:
1239:
1234:
1229:
1224:
1218:
1216:
1204:
1203:
1201:
1200:
1195:
1190:
1185:
1180:
1175:
1170:
1165:
1160:
1155:
1150:
1145:
1140:
1135:
1130:
1125:
1120:
1115:
1110:
1105:
1100:
1095:
1090:
1085:
1080:
1075:
1070:
1065:
1060:
1055:
1049:
1047:
1041:
1040:
1038:
1037:
1032:
1027:
1022:
1017:
1012:
1007:
1002:
997:
992:
987:
982:
977:
972:
967:
962:
957:
952:
947:
942:
937:
932:
927:
922:
917:
912:
907:
902:
897:
892:
890:Cruciform tail
887:
885:Crack arrestor
882:
877:
872:
866:
864:
857:
856:
845:
844:
837:
830:
822:
816:
815:
808:
807:External links
805:
802:
801:
760:
730:
712:
703:
694:
685:
676:
667:
658:
649:
637:
616:
610:Nasa TP 2691,
603:
591:
578:
566:
557:
544:
530:
516:
507:
497:
484:
472:
463:
458:NASA TP 1589,
451:
438:
425:
407:
398:
382:
360:
350:
326:
325:
323:
320:
319:
318:
313:
308:
301:
298:
267:
266:
260:
254:
249:
243:
237:
231:
225:
203:
200:
194:
191:
157:
154:
148:
145:
108:
105:
77:
74:
15:
9:
6:
4:
3:
2:
1808:
1797:
1794:
1792:
1789:
1788:
1786:
1771:
1768:
1766:
1763:
1761:
1758:
1756:
1753:
1751:
1748:
1746:
1743:
1741:
1738:
1736:
1733:
1731:
1728:
1726:
1723:
1721:
1718:
1716:
1713:
1711:
1708:
1706:
1703:
1702:
1700:
1698:Other systems
1696:
1690:
1687:
1685:
1684:Ejection seat
1682:
1681:
1679:
1675:
1669:
1666:
1664:
1661:
1659:
1656:
1654:
1651:
1649:
1646:
1644:
1641:
1639:
1636:
1634:
1631:
1629:
1628:Arrestor hook
1626:
1624:
1623:Aircraft tire
1621:
1620:
1618:
1616:
1612:
1608:
1602:
1599:
1597:
1594:
1592:
1589:
1587:
1584:
1582:
1579:
1577:
1574:
1572:
1569:
1567:
1564:
1562:
1559:
1557:
1554:
1552:
1549:
1547:
1544:
1542:
1539:
1537:
1534:
1532:
1529:
1527:
1524:
1522:
1519:
1518:
1516:
1514:
1508:
1504:
1498:
1495:
1493:
1490:
1488:
1485:
1483:
1480:
1478:
1475:
1473:
1470:
1468:
1465:
1463:
1460:
1458:
1455:
1453:
1450:
1448:
1445:
1443:
1440:
1438:
1435:
1433:
1430:
1428:
1427:Glass cockpit
1425:
1423:
1420:
1418:
1415:
1413:
1410:
1408:
1405:
1403:
1400:
1398:
1395:
1393:
1390:
1388:
1385:
1383:
1380:
1378:
1375:
1373:
1370:
1368:
1365:
1363:
1362:Air data boom
1360:
1358:
1355:
1354:
1352:
1349:
1343:
1339:
1333:
1330:
1328:
1325:
1323:
1320:
1318:
1315:
1313:
1310:
1308:
1305:
1303:
1300:
1298:
1295:
1293:
1290:
1288:
1285:
1283:
1280:
1278:
1275:
1273:
1270:
1268:
1265:
1263:
1260:
1258:
1255:
1253:
1250:
1248:
1245:
1243:
1240:
1238:
1235:
1233:
1230:
1228:
1225:
1223:
1220:
1219:
1217:
1213:
1209:
1205:
1199:
1196:
1194:
1191:
1189:
1186:
1184:
1181:
1179:
1176:
1174:
1171:
1169:
1166:
1164:
1161:
1159:
1156:
1154:
1151:
1149:
1146:
1144:
1143:Rudder pedals
1141:
1139:
1136:
1134:
1131:
1129:
1126:
1124:
1121:
1119:
1116:
1114:
1111:
1109:
1106:
1104:
1101:
1099:
1096:
1094:
1091:
1089:
1086:
1084:
1081:
1079:
1076:
1074:
1071:
1069:
1066:
1064:
1061:
1059:
1056:
1054:
1051:
1050:
1048:
1046:
1042:
1036:
1033:
1031:
1028:
1026:
1023:
1021:
1018:
1016:
1013:
1011:
1008:
1006:
1003:
1001:
1000:Trailing edge
998:
996:
993:
991:
988:
986:
983:
981:
980:Stressed skin
978:
976:
973:
971:
968:
966:
963:
961:
958:
956:
953:
951:
948:
946:
943:
941:
938:
936:
933:
931:
928:
926:
923:
921:
918:
916:
913:
911:
908:
906:
903:
901:
898:
896:
893:
891:
888:
886:
883:
881:
878:
876:
873:
871:
868:
867:
865:
862:
858:
854:
850:
843:
838:
836:
831:
829:
824:
823:
820:
814:
811:
810:
797:
791:
775:
771:
764:
748:
744:
740:
734:
726:
722:
716:
707:
698:
689:
680:
671:
662:
653:
646:
645:Rutan VariEze
641:
633:
632:whycirrus.com
626:
620:
613:
607:
600:
595:
588:
582:
575:
570:
561:
554:
548:
540:
534:
528:
525:
520:
511:
501:
494:
488:
482:
476:
467:
461:
455:
448:
442:
435:
429:
423:
421:
417:
411:
402:
395:
392:
386:
371:
364:
354:
348:
347:1-56027-287-2
344:
340:
337:Crane, Dale:
334:
332:
327:
317:
314:
312:
309:
307:
304:
303:
297:
295:
291:
286:
284:
283:certification
280:
276:
272:
264:
263:Smith Trainer
261:
258:
255:
253:
250:
247:
244:
241:
238:
235:
234:Piper PA28 RX
232:
229:
226:
223:
220:
219:
218:
215:
213:
209:
208:Rutan VariEze
199:
190:
187:
182:
180:
176:
172:
168:
164:
153:
144:
140:
136:
134:
129:
125:
123:
119:
113:
104:
101:
99:
95:
91:
87:
83:
82:droop concept
73:
71:
65:
63:
58:
56:
52:
48:
44:
40:
32:
29:as part of a
28:
23:
19:
1720:Deicing boot
1648:Landing gear
1591:Townend ring
1581:Thrust lever
1556:NACA cowling
1521:Autothrottle
1513:fuel systems
1511:devices and
1302:Stall strips
1276:
1272:Krueger flap
1242:Channel wing
1188:Wing warping
1178:Stick shaker
1173:Stick pusher
1093:Dual control
1078:Centre stick
945:Leading edge
915:Flying wires
875:Cabane strut
778:. Retrieved
774:the original
763:
751:. Retrieved
747:the original
733:
724:
715:
706:
701:NASA TP 2772
697:
688:
683:AIAA 86-2596
679:
670:
661:
652:
640:
631:
619:
611:
606:
598:
594:
586:
581:
573:
569:
560:
552:
547:
538:
533:
523:
519:
510:
500:
492:
487:
475:
466:
459:
454:
446:
441:
433:
428:
419:
415:
414:Burt Rutan,
410:
401:
390:
385:
373:. Retrieved
363:
353:
338:
287:
275:Columbia 350
268:
216:
205:
202:Applications
196:
193:Drag penalty
183:
159:
150:
141:
137:
130:
126:
117:
114:
110:
102:
93:
89:
85:
81:
79:
66:
59:
38:
36:
18:
1668:Tundra tire
1551:Intake ramp
1482:Transponder
1267:Gurney flap
1208:Aerodynamic
1123:Fly-by-wire
1005:Triple tail
725:grumman.net
585:H. Holmes,
294:wing fences
271:Cirrus SR20
163:Cirrus SR22
76:Terminology
43:aerodynamic
41:is a fixed
1785:Categories
1658:Oleo strut
1546:Inlet cone
1541:Gascolator
1507:Propulsion
1497:Yaw string
1492:Variometer
1348:instrument
1327:Wing fence
1262:Gouge flap
1237:Blown flap
1193:Yaw damper
1168:Stabilator
1153:Side-stick
1088:Dive brake
975:Stabilizer
950:Lift strut
940:Jury strut
322:References
257:Cessna 210
240:Cessna 172
186:Cessna 172
179:Cessna 210
167:Cessna 400
33:experiment
1633:Autobrake
1561:NACA duct
1536:Fuel tank
1526:Drop tank
1509:controls,
1392:Astrodome
1382:Altimeter
1247:Dog-tooth
1212:high-lift
1163:Spoileron
1148:Servo tab
1128:Gust lock
1083:Deceleron
1068:Autopilot
1025:Wing root
1010:Twin tail
995:Tailplane
930:Hardpoint
900:Empennage
863:structure
539:KitPlanes
491:Hoerner,
290:STOL kits
242:X (1983),
212:vortilons
1601:Wet wing
1576:Throttle
1322:Vortilon
1183:Trim tab
1113:Flaperon
1103:Elevator
1058:Airbrake
1030:Wing tip
955:Longeron
925:Fuselage
861:Airframe
849:Aircraft
790:cite web
780:8 August
753:8 August
741:(2009).
375:8 August
300:See also
224:X (1978)
124:(1978).
1611:Landing
1402:Compass
1350:systems
1342:Avionic
1332:Winglet
1215:devices
1158:Spoiler
1053:Aileron
1035:Wingbox
960:Nacelle
910:Fairing
853:systems
542:wings."
495:, 12-24
107:History
70:aileron
1346:flight
1307:Strake
1138:Rudder
1108:Elevon
1073:Canard
1015:V-tail
990:T-tail
920:Former
880:Canopy
739:Cessna
721:"Data"
345:
265:(1992)
230:(1980)
92:), or
1531:FADEC
1417:EICAS
1292:Slats
1133:HOTAS
985:Strut
628:(PDF)
51:stall
1613:and
1477:TCAS
1457:ISIS
1412:EFIS
1357:ACAS
1344:and
1297:Slot
1257:Flap
1210:and
1198:Yoke
970:Spar
895:Dope
796:link
782:2009
755:2009
377:2009
343:ISBN
273:and
165:and
133:NACA
98:NASA
55:spin
53:and
31:NASA
1452:INS
1432:GPS
1287:LEX
965:Rib
279:FAA
173:),
90:DLE
84:or
1787::
792:}}
788:{{
723:.
630:.
526:,
358:14
330:^
214:.
37:A
841:e
834:t
827:v
798:)
784:.
757:.
727:.
634:.
396:.
379:.
281:-
88:(
Text is available under the Creative Commons Attribution-ShareAlike License. Additional terms may apply.
