The F5 Prefix now supersedes the previous F3 and F4 series
prefixes due to the smoothing of the Pressure Coefficient (Cp)
curve for cruise and landing/stall speeds. There are enough
numbers to go around. You do not have to plot all of them to make
a smooth airfoil curve, unless you want to.

Multiply the Percent values (X,Y) given below by the chord length
you desire.

X% (Chord)   Y% (±Vertical)

1.00000000        0.00000000    Trailing Edge (Starting on top airfoil surface)
0.99931477        0.00011773
0.99726095        0.00046942
0.99384417        0.00105063
0.98907380        0.00185384
0.98296291        0.00286834
0.97552826        0.00408010
0.96679021        0.00547153
0.95677273        0.00702132
0.94550326        0.00868796
0.93301270        0.01040148
0.90797428        0.01409645
0.88293587        0.01790256
0.85574811        0.02202610
0.82468880        0.02697095
0.78391318        0.03351420
0.73672200        0.04119440
0.69561525        0.04816814
0.65450850        0.05511409
0.62940952        0.05927017
0.60395585        0.06348405
0.57821723        0.06774699
0.55226423        0.07204542
0.52616798        0.07637947
0.50000000        0.08076075
0.46807074        0.08606324
0.43576126        0.09103684
0.41143408        0.09451375
0.39109807        0.09723138
0.37076206        0.09977881
0.34896891        0.10223555
0.32754149        0.10425311
0.30574361        0.10587802
0.28685302        0.10694635
0.26845381        0.10755812
0.24765233        0.10762329
0.22799738        0.10721930
0.20593541        0.10580913
0.18518853        0.10373444
0.16534368        0.10084792
0.14874617        0.09769078
0.13151723        0.09372181
0.11230381        0.08821938
0.09480426        0.08190511
0.08001082        0.07568104
0.06639004        0.06900103
0.05250233        0.06122449
0.03878766        0.05205498
0.02845287        0.04386485
0.01923802        0.03534089
0.01185536        0.02687216
0.00603546        0.01852441
0.00273905        0.01173198
0.00171214        0.00909954
0.00068523        0.00566938
0.00034262        0.00398471
0.00000000        0.00000000        
Leading edge
0.00034262        -0.00299172
0.00068523        -0.00421012
0.00171214        -0.00663924
0.00273905        -0.00810491
0.00617992        -0.01112386
0.01130043        -0.01377240
0.01915776        -0.01633266
0.02885704        -0.01822030
0.03878766        -0.01913754
0.05258885        -0.01954609
0.06639004        -0.01955852
0.08022130        -0.01943995
0.09489446        -0.01917703
0.11216705        -0.01891281
0.12882187        -0.01869441
0.14547669        -0.01855429
0.16543470        -0.01851024
0.18533980        -0.01873618
0.20594016        -0.01924163
0.22799738        -0.02008124
0.24822560        -0.02100703
0.26845381        -0.02202297
0.28685302        -0.02300557
0.30574361        -0.02407739
0.32561695        -0.02525884
0.34896891        -0.02666508
0.37076206        -0.02790013
0.39109807        -0.02898579
0.41143408        -0.03001075
0.43576126        -0.03113907
0.46788063        -0.03237555
0.49702431        -0.03318960
0.52616798        -0.03374483
0.55226423        -0.03397473
0.57821723        -0.03400280
0.60312424        -0.03392726
0.62940952        -0.03368377
0.65768348        -0.03311366
0.68595745        -0.03229143
0.71198438        -0.03148645
0.76083005        -0.02863288
0.78667318        -0.02684891
0.80837777        -0.02512088
0.82399613        -0.02382386
0.85523283        -0.02090057
0.88293587        -0.01794665
0.90390685        -0.01540877
0.92487783        -0.01264436
0.94233865        -0.01007167
0.95677273        -0.00784591
0.96679021        -0.00617816
0.97552826        -0.00464475
0.98296291        -0.00328591
0.98907380        -0.00213384
0.99384417        -0.00121351
0.99726095        -0.00054347
0.99931477        -0.00013648
1.00000000        0.00000000       
Trailing Edge (Ending at lower airfoil surface)
Ray_Stits_Aircraft
Updated with Smoothed Pressure Coefficient Curves
Copyright © 2000- 2016 by Richard W. Fraser  All Rights Reserved
F5Fras15 Airfoil Coordinates
(For General Release December, 2007)
F5Fras15
Copyright © 2000- 2016 by Richard W. Fraser  All Rights Reserved
F3Fras13 and 15 Airfoil
The F5Fras13 & 15 airfoil coordinates are free for you to copy

FRASER AERO TECHNOLOGY COMPANY  
Technical Page

The F5 Prefix now supersedes the previous F3 and F4 series
prefixes due to the smoothing of the Pressure Coefficient (Cp)
curve for cruise and landing/stall speeds. There are enough
numbers to go around. You do not have to plot all of them to
make a smooth airfoil curve, unless you want to.

Multiply the Percent values (X,Y) given below by the chord
length you desire.

X% (Chord)   Y% (±Vertical)

0.00000000        0.00000000    Trailing Edge (Starting on top airfoil surface)
0.99931477        0.00013733
0.99726095        0.00054754
0.99384417        0.00122524
0.98907380        0.00216137
0.98296291        0.00334296
0.97552826        0.00475297
0.96679021        0.00636997
0.95677273        0.00816790
0.94550326        0.01009786
0.93301270        0.01208833
0.90797428        0.01633209
0.88293587        0.02066729
0.85574811        0.02533268
0.82468880        0.03088362
0.78391318        0.03818513
0.73672200        0.04669967
0.69561525        0.05435195
0.65450850        0.06192413
0.62940952        0.06643887
0.60395585        0.07099621
0.57821723        0.07559404
0.55226423        0.08022180
0.52616798        0.08487237
0.50000000        0.08955391
0.46807074        0.09519783
0.43576126        0.10045917
0.41143408        0.10411721
0.39109807        0.10696538
0.37076206        0.10962554
0.34896891        0.11217650
0.32754149        0.11425011
0.30574361        0.11590032
0.28685302        0.11696838
0.26845381        0.11755155
0.24765233        0.11754128
0.22799738        0.11703685
0.20593541        0.11545316
0.18518853        0.11317932
0.16534368        0.11005294
0.14874617        0.10665485
0.13151723        0.10238931
0.11230381        0.09648138
0.09480426        0.08970078
0.08001082        0.08301706
0.06639004        0.07583083
0.05250233        0.06745359
0.03878766        0.05754542
0.02845287        0.04864890
0.01923802        0.03932753
0.01185536        0.03002385
0.00603546        0.02080346
0.00273905        0.01326182
0.00171214        0.01031333
0.00068523        0.00643130
0.00034262        0.00452274
0.00000000        0.00000000     Leading edge
0.00034262        -0.00352975
0.00068523        -0.00497204
0.00171214        -0.00785303
0.00273905        -0.00963475
0.00603546        -0.01330622
0.01185536        -0.01714639
0.01923802        -0.02033901
0.02845287        -0.02295219
0.03878766        -0.02462798
0.05250233        -0.02577501
0.06639004        -0.02638832
0.08001082        -0.02677841
0.09480426        -0.02697420
0.13151723        -0.02733398
0.14874617        -0.02750706
0.16534368        -0.02771527
0.18518853        -0.02817871
0.20593541        -0.02888552
0.22799738        -0.02989879
0.24765233        -0.03089756
0.26845381        -0.03201640
0.28685302        -0.03302760
0.30574361        -0.03409968
0.32754149        -0.03537136
0.34896891        -0.03660603
0.37076206        -0.03774686
0.39109807        -0.03871979
0.41143408        -0.03961421
0.43576126        -0.04056140
0.46807074        -0.04151628
0.50000000        -0.04205002
0.52616798        -0.04223773
0.55226423        -0.04215111
0.57821723        -0.04184985
0.60395585        -0.04143548
0.62940952        -0.04085247
0.65450850        -0.03999924
0.69561525        -0.03819881
0.73672200        -0.03569570
0.78391318        -0.03172289
0.82468880        -0.02767588
0.85574811        -0.02415565
0.88293587        -0.02071138
0.90797428        -0.01712793
0.93301270        -0.01315808
0.94550326        -0.01100354
0.95677273        -0.00899249
0.96679021        -0.00707660
0.97552826        -0.00531762
0.98296291        -0.00376053
0.98907380        -0.00244137
0.99384417        -0.00138812
0.99726095        -0.00062159
0.99931477        -0.00015608
1.00000000         0.00000000    
(Trailing edge ending at lower airfoil surface)
Click on Graph below to Enlarge.
An additional click on a viewer that generally
shows up in the lower right part of the widow
will greatly enlarge and sharpen the image.
Click on Graph below to Enlarge.
An additional click on a viewer that generally
shows up in the lower right part of the widow
will greatly enlarge and sharpen the image.