NASA Technical Paper 2256 - CAFE Foundation

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ORIGINAL PAGE IS OF POOR QUALITY TABLE 4,- Concluded (d) VariEze and Long-EZ canard (x/c) U (z/c) U (x/c) L (z/c) L 0,00000 .00130 .00492 .01057 .01777 .02676 .03907 05088 07473 10035 12444 15030 17745 20049 22661 25016 27677 30006 32718 34970 37"502 .39902 .42566 .44662 .47449 49954 52330 54555 57413 59865 62444 64946 69951 74980 79934 84963 89993 .94869 1.00000 0 00000 00583 01387 62288 03-154 04068 05166 06099 07725 09211 10402 11494 .12488 13280 14103 14713 15771 16248 16539 16757 1691_ 17.041 17077 16972 16686 16275 15758 15045 14332 13530 12720 10997 09171 07345 05496 03638 ..... 01843 00025 0.00000 .00076 .00203 60406 00814 01707 02678 03827 05079 07482 10063 12747 1.5074 17784 0,0034 22668 25019 27550 30056 .32512 .35043 .:,7606 39978 42536 45041 50003 55066 59977 65015 69951 74937 79976 84937 89949 94477 1.00000 0 00000 - 00273 00438 - 06651 - 00955 01412 01749 02030 - 0<strong>2256</strong> - 02558 - 02752 - 02822 - 0_946 o -.03013 -.03046 • U OUl_,. - .03143 - 03178 - 03145 - 03076 - 03017 - 02990 02925 •- 02815 - 02700 -. O2472 - 02253 02057 - 01850 01639 - 01417 - 01183 -.00924 -.00617 -.00312 -.00025 " : - '
62 TABLE 5.- PHYSICAL CIIARACTERISTICS OF LONG-EZ Gross weight ]b 1325 , • _ • e • .'go qe 00 o .o • • • • , e ...,..go eooeoooo o. ooe.ooe(Jooeoe o.oo.o.oeoo Wing: Area, ft 2 .,.............. .... ..... ........ . .... ..,,......,,...%.._.......... 81.99 in " 313 2 Span , . eeeoeeee0eeo0ooeeeeoeo.oeeieoeeeeoeeeeoeo.ee.ee.eooe..eeoeo..eo0o.. • Aspect ratio .......... .... ..... .... .......................... .... .. ..... .... 8.3 Taper ratio (main wing) ..... i ......... , ..................................... 0,48 Airfoil section (main wing) ...-........................................ See table 4 Root chord (main wing), in .................................................. 41.4 Tip chord (main wing), in ................................................... 20 Mean aerodynamic chord, in ......... .... . .................................... 37.6 Root chord (outboard strake), in ............................................ 76 Tip chord (outboard strake), in ...................................... • ...... 41.4 Twist (washout), deg ................................................... BL157:-2.7 BLI06.25:-0.46 BL55.5:-0.6 Dihedral, deg .. .... ....... ............o.........,...........oo............... 0 Incidence at root, deg ....................................................... 0 Sweep at leading edge (main wing), deg ....................................... 23 Sweep at leading edge (outboard strake), deg ................................. 51 Sweep at leading edge (inb0ar_ strake), deg .................................. 64 Canard: Area, ft 2 ................................................................... 12.8 Span, in. .. .......... J ............... ... .......................... .... ...... 141.6 Aspect ratio ..................................... • ....................... .,. 10,88 Taper-ratio ................................ • ................................ 1.0 Airfoil section (see table 2) ......................................... GU25-5(11)8 Mean aerodynamic chord, in ................................................... 13 Twist, deg ..................................... • .............................. 0 Dihedral, deg ................................................................ 0 Incidence at root, deg ............... . .......................... .. ......... .. 0.6 Sweep at leading edge, deq ...... . .... , ......................... . ........... .. 0 Winglet (upper): Length, in ........................................ • ..................... ...0. 49 _oot chord, in ................ . ...... . ................................ .. 27._ Tip chord, in ............................................................. 11 Mean aerodynamic chord, in ................................................... 20.5 Area (projected vertically), ft 2 .. ............................................ 6.57 Aspect ratio (based on vertically projected geometry) ........................ 2.54 Taper ratio ..................... . .... . ........... . ...... • ..... . ......... ..... 0.40 Sweep at leading edge, .deq ................................................... 28 Twist, deg ..........., ........ . ..... . ......... •........... ....... ............ 0 Incidence at root, deg ...... .,..... ..... • ........ .,,..,,., ...... •........... • 0.5 Cant angle, deg .................................. ........ .... .... ....... ..... 0 Airfoil section ....................................................... See table 4 Powerplant: Manufacturer .............. ... ....... . ...... . ....... .. ......... Avco Lycoming Corp. Model .............. ...... . .... • ....................... • ..... _ ............... -0.235 Takeoff and maximum continuous power,.hp ....................... . ............. 118 Revolutions per minute, maximum ........................... • ................ 2800 Propeller (fixed pitch): Manufacturer ..... i ....................... .. Ted Hendrickson, Snohomish, Washington Number of blades -... ......... ......... .... ..........,._...,....i............o.. 2 Pitch, in ...... . ................................. -..... , ........... • ........... 70 Diameter, in. ....._ ..... .. .... ,...... ....... ... .... ...............,...,....... 58
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3 I" NASA Technical Paper 225.6 Jun
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m_ Use of trademarks or names of ma
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This report presents the results of
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I installation of an outboard leadi
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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
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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: i 60 _IOINJU,, pAOli Ill _I p_OR OU
Page 69 and 70: 64 (x/e)u 0 0000O 00000 00196 00644
Page 71 and 72: !+ • + _;+ TABLE 7.- +PHYSICAL CH
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
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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
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Page 111 and 112: i ORIGINAL PAGE |_] OF POOR QUALITY
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112 0 e.o ORIGINAL PAGE IS OF POOR
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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
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__ F_ Experimental transition ,| OR
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NASA Technical Paper 2256 - CAFE Foundation

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