NASA Technical Paper 2256 - CAFE Foundation

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¸ ¢xlc)u O, 00000 ,00000 ,00026 .00212 .00503 ,00793 01215. 01665 02244 02S52 03617 05180 06966 08944 11106 1321-6 15114 16828 18647 20492 22311 26654 30034 33566 ,37308 41103 44872 r, 48077 52225 55967 59550 63346 67035 ,70513 74518 7-8129 82003 85191 88959 9,:,o,35 97392 1 00000 TABLE 6.-. Concluded (z/c.).u 0 00000 (i 0018 0fi283 00809 01365 018.14 02315 02754 03245 03695 04213 05134 06052 06838 07551 08187 08619 08940 09211 (19431 09609 ,09815 ,09818 09663 09418 0£132 08802 EO 084_,_ 08048 ,07621 ,07147 ,06575 ,05958 05382 04719 04109 03436 02869 0-2194 01408 00695 00185 (c).-Winqlet tip (×/C)L 0 00000 00000 00053 00210 00394 00841 01369 02107- 02923 03977 07508 11172 14940 18656 22346 2601O 29489 33311 37185 40744 44302 48057 _'_1124 ,_. Lr ._,_821 59037 52938 66549 70371 13930 78200 82734 86768 ,91196 ,94366 ,97620 ,99947 ORIGINAL PAGE IS OF POOR QUALITY (zlC)L 0 (10000 - 00018 --00370 - 00727 - 00951 - 01251. - 01495 - 017%7 -01968 - 02189 - 02793 - 03275 -,03597 -- 03770 - 03885 - 6395? - 04012 - 04061 - 04052 - 03976 - 03876 - 6374:'; -. 03527 %'13"%_ "" J,,: L i - - 02998 t,...710 19 - 02459 - 6218_, - 01933 - 01632 - 01332 - 01072 -00779 -, 00559 - ,00323 -.00184 ®
!+ • + _;+ TABLE 7.- +PHYSICAL CHARACTERISTICS OF BIPLANE RACER Gross weight, Ib ................................................................ i200 Wing (forward): Area, f+t2 .................................................................. 47.6 Span, in .................................................................... 213.6 Aspect ratio ................................................................ 6.68 Taper ratio (main wing) .................................................... 0.68 Airfoil section (main wing) ........................................... See table 6 Root chord (main wing), in ................................................... 37 Tip chord (main wing), in .................................................... 26 Mean aerodynamic chord, in ................................................... 32 Twist (washout), deg., ....................................................... 0 Anhedral, deg ................................................................ 6.5 Incidence at root, deg ....................................................... 0 Sweep at leading edge, deg ................................................... 6 Wing (aft): Area, ft 2 ................................................................... 44.1 Span, in ................................................................... 270 Aspect ratio ............................................................... 11.48 Taper-ratio ................................................................ 0.52 Airfoil section ...................................................... See table 6 Mean aerodynamic chord, in ................................................... 23 Root chord, in ................................... ,.................................... 29 Tip chord, in ................................................................ 16 Twist, deg .... .....,., ......,..,.....,,,..,...,.,,,..,,,,,,....,.,,.,...,,.., 0 Dihedral, deg .,..,..........,,...,......,,..........o..,,,..,,,.,,,,o.,..,o,. 4 Incidence at root, deg .................... . .................................. 0 Sweep at leading edge, deq ................................................... 3.2 Powerplant: Manufacturer .................................................. Avco Lycoming Corp. Model ..................................................................... I0-320 Takeoff and maximum continuous power, hp .................................... 160 Revolutions per minute, maximum ............................................. 2800 Propeller (fixed pitch): 66 Number of blades 2 io,oQoQIooQeleOOOlileQl•oleollooloolieoooloeQtlleeelo,eol,ool Diameter in • 60 , • °oele0+eeoOlOleeeollloooeoloooooloooleeloeelOllllesloleeOlllleo
Page 1 and 2:
3 I" NASA Technical Paper 225.6 Jun
Page 3 and 4:
m_ Use of trademarks or names of ma
Page 5 and 6:
'*l ,_5 7,,4+-. + + +_''_m'_T _+_
Page 7 and 8:
This report presents the results of
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i Rc R 0 r S s T t/c U.s. V V c V i
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_i._J •J k_ Reynolds number_, Mat
Page 13 and 14:
I installation of an outboard leadi
Page 15 and 16:
ii, p,. _2 ,'ZI Reynolds numberof-1
Page 17 and 18:
L r ...... _ 11 , Airplane level-fl
Page 19 and 20: I',/ L figures 20 to 23. The reduct
Page 21 and 22: i 7: region of the airfoil. Further
Page 23 and 24: k! k K , " _Rmlmlllll_lNiiillnp v 9
Page 25 and 26: k.L" F i' N apparent small velocity
Page 27 and 28: _T"_T _ 7] I _ - _'_' T occurred on
Page 29 and 30: shape as an indication of transitio
Page 31 and 32: level. Analysis shows that at a mor
Page 33 and 34: i< 1 11 APPENDIX SURFACE WAVINESS O
Page 35 and 36: 3O Airplane VariEze in flight Long-
Page 37 and 38: Relative gauge- reading, in. 8O 80
Page 39 and 40: k' F' &. _', b ,_ .-wT 7- Relative
Page 41 and 42: i ;:7" --..i iI m :, r, •_ $ 36 A
Page 43 and 44: 38 BO x 10-.3 70 BO 5O 4O 3O 2O I0
Page 45 and 46: 70 x 10-3 B0 l l 50 I. 4o \;,_.=.\
Page 47 and 48: 42 Relative gauge 6O 50 reading, in
Page 49 and 50: 6O 50 40 30 20 iO 0 B0 50 40 Relati
Page 51 and 52: L!I L C 46 70 BO 50 4O 30 20 iO 0 R
Page 53 and 54: _I 48 REFERENCES I. Loftin, Laurenc
Page 55 and 56: _i _ 30. Braslow, Albert L.; and Kn
Page 57 and 58: [ 52 m v ._ :_ ._ v o = "_" II x °
Page 59 and 60: i" 54 e3 ! URIGINAL PAt_E Ig OF POO
Page 61 and 62: 2, r"-" r. .! . 7L I g _ , _. ,,9®
Page 63 and 64: 58 OI_IGINAL PAGE-Ig _F POOR QUALrT
Page 65 and 66: i 60 _IOINJU,, pAOli Ill _I p_OR OU
Page 67 and 68: 62 TABLE 5.- PHYSICAL CIIARACTERIST
Page 69: 64 (x/e)u 0 0000O 00000 00196 00644
Page 73 and 74: Z :c 68 (x/c)i_ 000000 00288 00575
Page 75 and 76: TABLE 10.- PHYSICAL CHARACTERISTICS
Page 77 and 78: ;_ i_ "_. 72 TABLE12.- PHYSICALCHAR
Page 79 and 80: _r i ..............................
Page 81 and 82: I 76 >- ,----7"I __ -_---qnlmwmnm_-
Page 83 and 84: ; , L i L_ _, k "/B // I _JRIGINALP
Page 85 and 86: °?. ORIGINAl.. PAGE IB OF pOOR OUA
Page 87 and 88: ORIGINAL PAGE 18 OF POOR QUALITY ®
Page 89 and 90: i _NAt, I'VE IS OF POOROUAUTY
Page 91 and 92: il_ _. 86 ! ORIGINAL PAGE Ig OF =PO
Page 93 and 94: If 'i " F t: i k"!.. ORIGINAL PAaE
Page 95 and 96: 9O ORI_NAL PAGE Ig OF POOR OI,JAL.I
Page 97 and 98: 92 (x/c) t = 55 percent Z ORIGINAL
Page 99 and 100: _4 . OR/a/_,_ PAQE 18 OF POOR quALr
Page 101 and 102: 96 i ] i i!......J J ! i i ( I i I
Page 103 and 104: 98 _ z_ tt // /V (_ _, ORI_K/D,L, p
Page 105 and 106: loo 0 oi.._ L F-. 0 II ÷ 0 ORIGINA
Page 107 and 108: ii, _..:j ._t _ ....... 102 ORIGINA
Page 109 and 110: 7, I!/ , T & / .J l i CL 1.2 1.0 0.
Page 111 and 112: i ORIGINAL PAGE |_] OF POOR QUALITY
Page 113 and 114: ORIGINAL PAGE IR OF POOR OUALITY I
Page 115 and 116: ORIQINAL PAGF..i_ OF POOR QUALITY 3
Page 117 and 118: 112 0 e.o ORIGINAL PAGE IS OF POOR
Page 119 and 120: i., L-.. _A / 114 ORIGINAL PA(.._._
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116 .p 0 × o II \ II co H ¢) °¢
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_i-_ , ORIGI/NAL PAGE _9 OF POOR QU
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_20 i_' POOR QUALI'_( o_ ¢N I O 0
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122 OP POORQuALrry I ¢; _k _J o_ o
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i _. / ,p. _'- CO ¢t_ 4J ORIGINAL
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126 ORI_NAL PAGF. I_ OF POOR QUALIT
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L'_::; : • 128 ORi_NAI.,PAGEIB OF
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130 _e8 , • , ".4 Cp 0 .4 .8 z/c
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SECTION DRAG COEFFIClENT, 132 Cd .0
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I ,,, z/c 134 .O6 .05 .04 .03 .02 .
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i.- _ l! I' h . MINIGLOVE NLF GLOVE
Page 143 and 144:
__ F_ Experimental transition ,| OR
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