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 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
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I installation of an outboard leadi
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L'_::; : • 128 ORi_NAI.,PAGEIB OF
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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