The Aerodynamic Characteristics of Flaps

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No. grime B I13 L I OG RAP HY~conti~¢ued Title, etc. 61 ~-- 62 Blackburn Aircraft Research Dept. Harris mad Recant . . . . . .. .. A Study of the Slotted Flap. Blackburn Report No. WT.49/40. 1940. Wind Tunnel Investigation of Three Airfoils Equipped with 40 per cent Double Flaps. N.A.C.A. Advance Report. A.R.C. Report No. 4834. 1940.
No. Name 77 Wenzinger and Harris .. 78 Rogallo and Spano .. 79 J° Wallace .. 80 Serby and Hufton 81 Serby and Shone 82 Francis .... 83 Serby, Francis and Fortescue .. 84 Ellis and Morgan ..... 85 Woodward Nutt and Hufton .. 86 Francis . . . . . . . . 87 Sherman . . . . . . . . 88 Davies, Adamson and Brown •. 89 Do. 90 House and Wallace .... c,I 91 Morgan and Morris 92 Stewart .... 93 Silverstein and Katzoff .. 94 Silverstein, Katzoff and Bullivant 95 Blackburn Aircraft Ltd. .. BIBLIOGRAPHY--continued I. Venetian-blind Flaps Title, etc. ..... Preliminary Wind Tunnel Investigation of and NACA 23012 Airfoil with Various Arrangements of Venetian-blind Flaps• N.A.C.A. Report No. 689. 1940. .... Wind Tunnel Investigation of an NACA 23012 Airfoil with 30 per cent Chord Venetian-blind Flap. N.A.C.A. Report No. 742. A.R.C. Report No. 5702. 1942. See also Ref. 3. Fla~s on Wing-body Combinations. Interference Effects . . . . . . The Effect of Split Trailing Edge Wing Flaps on the Aerodynamic Characteristics of a Parasol Monoplane• N.A.C.A. Tech. Note No. 475. 1933. . . . . . . Full Scale Tests of Landing Flaps on a Percival 'Gull.' R. & M. 1697. 1935. . . . . . . Full Scale Tests of Landing Flaps on a Miles ' Hawk Major.' Report No. BA 1179. A.R.C. 1807. 1935. (Unpublished). . . . . . . Full Scale Tests of the Effect of Flaps on Lateral Stability and Control. Part I. Tests of Falcon with Standard Planform. Part II. Tests of Falcon with High Taper Wing. R. & M. 1961. December, 1936. •. Full Scale Tests of the Airspeed Envoy Type AG. 69. R. & M. 1816. 1937. .. Wind Tunnel Tests on Slotted Flaps on a Low Wing Monoplane, Flap Angles, 0 deg to 90 deg. R. & M. 1735. 1936. •. Full Scale Tests of the Hendy Heck. R. & M. 1719. 1936. •. Full Scale Tests of Slotted Flaps and Ailerons on a Courier• R. & M. 1819. 1937. .. Interference of Wing and Fuselage from Tests of 18 Combinations in the N.A.C.A. Variable Density Tunnel• Combinations with split flaps• N.A.C.A. Tech. Note No. 640. 1938. ., Wind Tunnel Tests on the Bristol B1/39. A.R.C. 4797. 1940. (Unpublished.) Wind Tunnel Tests on the Supermarine $24/37. R. & M. 2451. March, 1941. .. Wind Tunnel Investigation of Effect of Interference on Lateral Stability Characteristics of Four NACA 23012 Wings on an Elliptical and a Circular I~uselage and Vertical Fins. N.A.C.A. Report No. 705. 1940. . . . . . . Flight Tests of a Youngman Flap on the Fairey P4/34 K7555. A.R.C. 5281. 1941. (To be published.) . . . . . . Flight Measurements of Maximum Lift Coefficients. A.R.C. 7889. 1944. (Unpublished.) See also Refs. 4, 36. K. Flap Downwash Effects .. Design Charts for Predicting Downwash Angles and Wake Characteristics Behind Plain and Flapped Wings. N.A.C.A. Report •. No. 648. 1939. Downwash and Wake Behind Plain and Flapped Aerofoils. N.A.C.A. Report No. 651. 1939. .. Investigation of the Effect of Full Span High Lift Flaps on the Flow in the Region of the Taitplane and Upon Stability anc~ Trim. Part I. Without Slipstream. Blackburn Report WT. ! 88/43. A.R.C. 7115. 1943. See also Ref. 74. 7
Page 1 and 2: "'% ~ ~.:~1 _~ ~,-:~.~-,~ ~,~, L',t
Page 3 and 4: A Aspect ratio Lift-curve slope Not
Page 5 and 6: 1. Introductio~.--The invention of
Page 7 and 8: m Since the optimum slot shape is a
Page 9 and 10: In the case of a split flap set for
Page 11 and 12: Hence ACre' = AC,,, CLc --2 -- C ..
Page 13 and 14: here estimated for an aspect ratio
Page 15 and 16: partially retracted positions, the
Page 17 and 18: the type of chordwise lift distribu
Page 19 and 20: (2) With the arrangements illustrat
Page 21 and 22: Kruger's nose ftap is illustrated i
Page 23 and 24: Generally speaking, a lower surface
Page 25 and 26: 13.3. Maximum Lift Coefficient Incr
Page 27 and 28: formula for A C,,o is generally cor
Page 29 and 30: 14.10 Flaps on swept-back wlngs.--O
Page 31 and 32: Main TABLE 2 Characteristics of Hig
Page 33 and 34: BIBLIOGRAPHY No. Name 1 Alston :. .
Page 35: No. N~,lytg B IB L I OG RAPHY--cont
Page 39 and 40: N~me Purser and Turner .... Davis .
Page 41 and 42: PLAIN WING . . . . WING WITH FLAP~
Page 43 and 44: 3-0 2.O ' I / ~-- ¢/~= . i/ , / TH
Page 45 and 46: 17"/C ---- O-'l~ / t/.. ,~ 0- 30 3.
Page 47 and 48: I*~- m I,O Zt, J I TAPER RATIO oo
Page 49 and 50: ,55 ° • 0"2 (o.~ BLACKBURN SLOTT
Page 51 and 52: NOSE FLAP (CL) ILLUSTRATION OF KRU(
Page 53 and 54: , +o.,~ +~1 t .A~/l I I F~A'~- . I.
Page 55 and 56: O,0~5 - - ~ I O RECTANGULAR WINrm X

The Aerodynamic Characteristics of Flaps

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