FX S 02-196 AIRFOIL (fxs02196-il)
FX S 02-196 AIRFOIL - Wortmann FX S 02-196 airfoil
| Details | Dat file | Parser | |
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(fxs02196-il) FX S 02-196 AIRFOIL Wortmann FX S 02-196 airfoil Max thickness 19.6% at 37.1% chord. Max camber 3.7% at 43.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX S 02-196 AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010200 0.0085000
0.0042200 0.0179100
0.0096000 0.0260000
0.0170200 0.0336900
0.0265000 0.0404700
0.0380200 0.0504400
0.0515800 0.0578100
0.0669400 0.0673900
0.0842200 0.0748300
0.1033000 0.0838400
0.1240300 0.0909300
0.1464300 0.0991400
0.1703700 0.1055700
0.1955800 0.1126200
0.2222100 0.1179400
0.2499800 0.1234700
0.2789100 0.1273200
0.3086100 0.1309900
0.3393300 0.1330600
0.3705600 0.1344400
0.4024300 0.1338500
0.4346900 0.1317600
0.4673300 0.1277600
0.4999700 0.1229400
0.5327400 0.1169500
0.5652500 0.1104600
0.5975000 0.1033400
0.6293800 0.0960200
0.6607400 0.0882800
0.6913300 0.0805800
0.7211500 0.0727400
0.7499501 0.0651200
0.7777300 0.0575400
0.8043500 0.0503200
0.8297000 0.0433800
0.8535000 0.0369500
0.8759000 0.0309400
0.8964400 0.0255100
0.9157100 0.0206000
0.9329900 0.0162700
0.9484800 0.0124400
0.9619200 0.0091800
0.9734400 0.0064300
0.9829100 0.0041500
0.9903400 0.0023500
0.9957100 0.0010700
0.9989100 0.0002600
1.0000000 0.0000000
0.0000000 0.0000000
0.0010200 -.0035000
0.0042200 -.0080000
0.0096000 -.0129300
0.0170200 -.0160300
0.0265000 -.0216400
0.0380200 -.0248400
0.0515800 -.0299300
0.0669400 -.0331500
0.0842200 -.0379000
0.1033000 -.0410400
0.1240300 -.0454000
0.1464300 -.0482600
0.1703700 -.0520800
0.1955800 -.0544700
0.2222100 -.0574700
0.2499800 -.0590600
0.2789100 -.0610300
0.3086100 -.0616200
0.3393300 -.0622500
0.3705600 -.0614300
0.4024300 -.0602600
0.4346900 -.0569900
0.4673300 -.0532200
0.4999700 -.0482600
0.5327400 -.0433700
0.5652500 -.0379300
0.5975000 -.0327800
0.6293800 -.0274400
0.6607400 -.0225900
0.6913300 -.0178300
0.7211500 -.0136200
0.7499501 -.0097000
0.7777300 -.0063300
0.8043500 -.0033300
0.8297000 -.0009300
0.8535000 0.0011100
0.8759000 0.0025800
0.8964400 0.0036300
0.9157100 0.0042500
0.9329900 0.0045000
0.9484800 0.0043800
0.9619200 0.0039500
0.9734400 0.0032400
0.9829100 0.0023600
0.9903400 0.0014700
0.9957100 0.0007000
0.9989100 0.0001900
1.0000000 0.0000000
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Polars for FX S 02-196 AIRFOIL (fxs02196-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fxs02196-il | 50,000 | 9 | 4.7 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs02196-il | 50,000 | 5 | 10.2 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs02196-il | 100,000 | 9 | 16.8 at α=13.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs02196-il | 100,000 | 5 | 37.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs02196-il | 200,000 | 9 | 68.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs02196-il | 200,000 | 5 | 56 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs02196-il | 500,000 | 9 | 53.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs02196-il | 500,000 | 5 | 46.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs02196-il | 1,000,000 | 9 | 60.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs02196-il | 1,000,000 | 5 | 54.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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