FX 66-S-196 V1 AIRFOIL (fx66196v-il)
FX 66-S-196 V1 AIRFOIL - Wortmann FX 66-S-196 V1 airfoil
| Details | Dat file | Parser | |
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(fx66196v-il) FX 66-S-196 V1 AIRFOIL Wortmann FX 66-S-196 V1 airfoil Max thickness 19.6% at 37.1% chord. Max camber 4% at 46.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 66-S-196 V1 AIRFOIL
44. 44.
0.0000000 0.0000000
0.0010700 0.0062100
0.0042800 0.0122300
0.0096100 0.0191800
0.0170200 0.0269200
0.0265300 0.0352000
0.0380600 0.0438300
0.0515600 0.0527300
0.0669900 0.0617000
0.0842700 0.0706700
0.1033200 0.0794600
0.1240800 0.0880300
0.1464500 0.0962100
0.1703300 0.1039800
0.1956200 0.1111400
0.2222100 0.1177200
0.2500000 0.1234800
0.2786600 0.1284800
0.3086600 0.1324300
0.3392800 0.1353700
0.3705900 0.1369000
0.4024500 0.1369100
0.4347400 0.1346700
0.4673000 0.1309500
0.5000000 0.1258500
0.5327000 0.1199500
0.5652600 0.1132100
0.5975500 0.1060700
0.6294100 0.0984400
0.6607200 0.0906700
0.6913400 0.0827200
0.7211400 0.0748200
0.7500000 0.0669900
0.7777900 0.0593600
0.8043801 0.0519700
0.8296700 0.0450100
0.8535500 0.0384500
0.8759201 0.0324200
0.9157300 0.0219300
0.9484400 0.0135700
0.9734700 0.0072900
0.9903900 0.0028400
0.9989300 0.0003900
1.0000000 0.0000000
0.0000000 0.0000000
0.0010700 -.0035400
0.0042800 -.0078400
0.0096100 -.0121100
0.0170400 -.0163900
0.0265300 -.0206500
0.0380600 -.0248900
0.0515600 -.0290300
0.0669900 -.0330700
0.0842700 -.0369500
0.1033200 -.0406300
0.1240800 -.0441000
0.1464500 -.0472900
0.1703300 -.0502200
0.1956200 -.0527900
0.2222100 -.0550300
0.2500000 -.0568100
0.2786600 -.0582000
0.3086600 -.0590100
0.3392800 -.0593100
0.3705900 -.0588000
0.4024500 -.0574300
0.4347400 -.0545100
0.4673000 -.0507600
0.5000000 -.0462800
0.5327000 -.0416100
0.5652600 -.0366700
0.5975500 -.0318600
0.6294100 -.0270700
0.6607200 -.0225600
0.6913400 -.0182700
0.7211400 -.0143500
0.7500000 -.0108000
0.7777900 -.0076400
0.8043801 -.0048900
0.8296700 -.0026000
0.8535500 -.0006800
0.8759201 0.0008000
0.9157300 0.0025400
0.9484400 0.0028800
0.9734700 0.0020600
0.9903900 0.0006600
0.9989300 -.0001700
1.0000000 0.0000000
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Polars for FX 66-S-196 V1 AIRFOIL (fx66196v-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx66196v-il | 50,000 | 9 | 4.6 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66196v-il | 50,000 | 5 | 7.8 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66196v-il | 100,000 | 9 | 5.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66196v-il | 100,000 | 5 | 26.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66196v-il | 200,000 | 9 | 49.9 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66196v-il | 200,000 | 5 | 61.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66196v-il | 500,000 | 9 | 110.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66196v-il | 500,000 | 5 | 104.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66196v-il | 1,000,000 | 9 | 139 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66196v-il | 1,000,000 | 5 | 132.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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