conrad booze - Experimental Aircraft Builder's Log

Conrads X-10 Build Log


Date: 4-8-2009
Number of Hours: 2.00
Manual Reference: None
Brief Description: X-10 NACA 23013.5 Air Foil

The RV-10 has an Airfoil of NACA 23013.5 and has the following properties: 1) A maximum thickness of 13.5% of cord length 2) A design lift coefficient of 0.33. 3) And a maximum camber located 15% back from the leading edge. NACA 23013.5 Airfoil is determined by the follwoing: This can be defined as the first digit, when multiplied by 3/2, yields the design lift coefficient (cl) in tenths. The next two digits, when divided by 2, give the position of the maximum camber (p) in tenths of chord. The final two digits again indicate the maximum thickness (t) in percentage of chord. The following is a set of computer software programs for analyis=, design and study of airfoils. Free software for printing air foils X-FOILS Subsonic Airfoil Development System New updated Summer 2008 http://web.mit.edu/drela/Public/web/xfoil/ Is new, styandard versionis $49, but is expensive for the complete edition http://www.dreesecode.com/index.html CB........ Spring 2009

NACA 23013.5 Air Foil

NACA 23013.5 Air Foil with Fowler Style Flap of the RV-10

Calculate the X-10 NACA 23013.5 Air Foil AOA

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Category		# Logs	# Hours

All		510	2382

Avionics		24	176

EAA and FAA Inspecti		2	1

Empennage		3	26

Engine		3	54

FAB		2	30

FF		5	38

FF1 Engine Installat		4	31

FF2 Cowl Baffle		9	88

Final_Kit		2	14

Flight_Training_and_		3	36

FUEL TANK Section 18		9	42

Fuselage		2	11

Gas_Expense		1	6

Hanger_Rent		1	90

Interior Finishing		6	37

Lights Nav and Strob		3	19

Miscellaneous		10	32

OP-37 Wiring Harness		12	18

Oxygen System		5	30

Paint Empennage		3	40

Paint Fuselage		2	14

Paint Wings		4	14

Perry_Apt_Hanger		7	88

Propeller		3	16

Section 10 Tail Cone		22	72

Section 11 Empennage		8	22

Section 12 Empennage		7	22

Section 13 Main Spar		5	11

Section 14 Wing Ribs		6	25

Section 15 Rear Spar		3	8

Section 16 Top Wing		2	12

Section 17 Outboard		6	47

Section 18 Fuel Tank		12	58

Section 19 Stall War		1	2

Section 20 Bottom Wi		16	56

Section 21 Aileron		15	32

Section 22 Flaps		9	42

Section 23 Aileron A		7	18

Section 24 Wing Tips		4	23

Section 25 Mid Fusel		5	25

Section 26 Mid Fusel		10	45

Section 27 Fire Wall		6	29

Section 28 Forward F		16	77

Section 29 Fuselage		24	84

Section 30 Step Inst		3	5

Section 31 Upper For		10	27

Section 32 Tail Cone		7	27

Section 33 Baggage A		10	24

Section 34 Baggage D		7	8

Section 35 Access Co		7	10

Section 36 Brake Lin		3	3

Section 37 Fuel Syst		5	13

Section 38 Rudder Pe		5	10

Section 39 Control S		7	14

Section 40 Flap Syst		1	10

Section 41 Upper For		3	10

Section 42 Rear Seat		3	7

Section 43 Cabin Cov		15	51

Section 44 Wing Atta		1	5

Section 45 Cabin Doo		21	100

Section 45A Cabin Do		7	15

Section 46 Engine Mo		8	29

Section 47 Spinner &		7	42

Section 48 Gear Leg		18	68

Section 49 Seats & S		4	8

Section 50 Cabin hea		1	2

Section 6 Vertical S		3	28

Section 7 Rudder		6	35

Section 8 Horizontal		9	54

Section 9 Elevators		20	83

Stall Warning Sectio		1	2

Tools		2	5

Wing Expenses		1

Wings		6	26