Oxford Aero Equipment ASW22B/ASW22BL/ASH25 Wing Airfoils

ASW22B / ASW22BL / ASH25 Wing Design
Wind Tunnel Simulations

The ASW22B, ASW22BL and ASH25 wings are similar. The ASW22B and ASH25 have a span of 25 m, whereas the ASW22BL has a longer span of 26.4 m.

The inner wing, from the root to near the inboard end of the aileron, is a Horstmann and Quast HQ17 airfoil. From there a transition zone takes the wing to a Delft University DU84-132V3. Alexander-Schleicher does not give out the actual airfoil coordinates. However, coordinates from photographs of the root and tip of an ASW22BLE were used to obtain coordinates. These are reported below and and are used for the wind tunnel simulations.

The wings have no aerodynamic twist but they are twisted slightly to allow for the different α₀ of the two profiles, and the varying Reynolds numbers, such that the whole wing produces zero lift at a particular angle of attack. The α₀ for the profiles were deduced from wind tunnel testing. There is no significant aerodynamic twist in the ailerons and flaps themselves in flight.

Thanks to Russell Cheetham for technical assistance.

ASW22BLE 3-View:

ASW22BL Wing Planform:

Inner Airfoil: HQ17
from photo of wing root
Chord Upper Lower 0.00000 0.00000 0.00000 0.00235 0.00657 -0.00469 0.00704 0.01408 -0.00845 0.01642 0.02346 -0.01180 0.02581 0.03130 -0.01408 0.03519 0.03754 -0.01595 0.04458 0.04317 -0.01750 0.05397 0.04786 -0.01890 0.06335 0.05256 -0.02020 0.08212 0.06100 -0.02210 0.10089 0.06851 -0.02360 0.12905 0.07790 -0.02520 0.15720 0.08620 -0.02640 0.18536 0.09330 -0.02740 0.21351 0.09920 -0.02820 0.24167 0.10430 -0.02900 0.26983 0.10887 -0.02970 0.29798 0.11262 -0.03020 0.32614 0.11544 -0.03070 0.34960 0.11760 -0.03090 0.37306 0.11919 -0.03090 0.39653 0.12050 -0.03097 0.41999 0.12120 -0.03097 0.44345 0.12120 -0.03097 0.46692 0.12100 -0.03090 0.49038 0.12030 -0.03060 0.51384 0.11910 -0.03003 0.53731 0.11732 -0.02930 0.56077 0.11490 -0.02850 0.58423 0.11200 -0.02750 0.60770 0.10887 -0.02640 0.63116 0.10511 -0.02500 0.65462 0.10042 -0.02360 0.67809 0.09573 -0.02180 0.70155 0.09010 -0.01980 0.72501 0.08450 -0.01750 0.74847 0.07790 -0.01480 0.77194 0.07133 -0.01150 0.79540 0.06382 -0.00845 0.81886 0.05631 -0.00469 0.84233 0.04850 -0.00140 0.86579 0.04130 0.00188 0.88925 0.03350 0.00375 0.91272 0.02570 0.00420 0.93618 0.01877 0.00370 0.95964 0.01150 0.00250 0.98311 0.00469 0.00100 1.00000 0.00000 0.00000

Outer Airfoil: DU84-132V3

from photo of wing tip

Chord   Upper    Lower
0.00000	0.00000	 0.00000
0.00228	0.01002	-0.00547
0.00683	0.01731	-0.01185
0.01595	0.02642	-0.01670
0.02506	0.03371	-0.02005
0.03417	0.03918	-0.02278
0.04328	0.04465	-0.02440
0.06606	0.05467	-0.02880
0.08884	0.06287	-0.03189
0.11162	0.07016	-0.03462
0.13440	0.07563	-0.03620
0.15718	0.08109	-0.03736
0.17995	0.08520	-0.03840
0.20273	0.08860	-0.03918
0.22551	0.09112	-0.03940
0.24829	0.09294	-0.03960
0.27107	0.09476	-0.03960
0.29385	0.09590	-0.03950
0.31663	0.09690	-0.03930
0.33941	0.09740	-0.03890
0.36219	0.09749	-0.03827
0.38497	0.09749	-0.03736
0.40774	0.09740	-0.03645
0.43052	0.09658	-0.03554
0.45330	0.09567	-0.03462
0.47608	0.09390	-0.03371
0.49886	0.09203	-0.03250
0.52164	0.09021	-0.03120
0.54442	0.08800	-0.03000
0.56720	0.08565	-0.02840
0.58998	0.08320	-0.02690
0.61276	0.08018	-0.02510
0.63554	0.07730	-0.02290
0.65831	0.07380	-0.02050
0.68109	0.07050	-0.01750
0.70387	0.06651	-0.01440
0.72665	0.06287	-0.01093
0.74943	0.05850	-0.00729
0.77221	0.05467	-0.00364
0.79499	0.05000	 0.00000
0.81777	0.04520	 0.00273
0.84055	0.04009	 0.00456
0.86333	0.03520	 0.00547
0.88610	0.03007	 0.00547
0.90888	0.02470	 0.00547
0.93166	0.01920	 0.00480
0.95444	0.01310	 0.00364
0.97722	0.00680	 0.00180
1.00000	0.00000	 0.00000

Inner and Outer Airfoils

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