S7075 (9%) (s7075-il)
S7075 (9%) - Selig S7075 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(s7075-il) S7075 (9%) Selig S7075 low Reynolds number airfoil Max thickness 9% at 29% chord. Max camber 2.8% at 46.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S7075 (9%)
1.00000 0.00000
0.99811 0.00030
0.99262 0.00130
0.98384 0.00301
0.97189 0.00532
0.95689 0.00825
0.93906 0.01183
0.91865 0.01599
0.89590 0.02064
0.87105 0.02565
0.84435 0.03084
0.81590 0.03603
0.78585 0.04114
0.75438 0.04596
0.72152 0.05039
0.68736 0.05452
0.65213 0.05833
0.61605 0.06181
0.57936 0.06492
0.54228 0.06762
0.50502 0.06988
0.46782 0.07165
0.43086 0.07290
0.39436 0.07362
0.35853 0.07377
0.32355 0.07334
0.28961 0.07232
0.25690 0.07072
0.22556 0.06854
0.19578 0.06579
0.16769 0.06249
0.14143 0.05868
0.11714 0.05438
0.09490 0.04963
0.07485 0.04451
0.05704 0.03906
0.04155 0.03336
0.02846 0.02751
0.01783 0.02158
0.00974 0.01572
0.00426 0.00983
0.00112 0.00396
0.00012 -0.00127
0.00205 -0.00532
0.00740 -0.00861
0.01586 -0.01154
0.02736 -0.01403
0.04182 -0.01616
0.05915 -0.01785
0.07927 -0.01912
0.10208 -0.01997
0.12746 -0.02041
0.15527 -0.02049
0.18536 -0.02022
0.21756 -0.01965
0.25167 -0.01880
0.28749 -0.01774
0.32478 -0.01649
0.36331 -0.01510
0.40283 -0.01360
0.44306 -0.01205
0.48375 -0.01047
0.52460 -0.00889
0.56534 -0.00734
0.60568 -0.00584
0.64532 -0.00438
0.68397 -0.00291
0.72149 -0.00140
0.75769 0.00009
0.79235 0.00160
0.82543 0.00301
0.85679 0.00399
0.88582 0.00420
0.91190 0.00378
0.93478 0.00312
0.95435 0.00237
0.97053 0.00163
0.98322 0.00099
0.99243 0.00051
0.99808 0.00016
1.00000 0.00000
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Polars for S7075 (9%) (s7075-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s7075-il | 50,000 | 9 | 38.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7075-il | 50,000 | 5 | 40.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7075-il | 100,000 | 9 | 59.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7075-il | 100,000 | 5 | 57.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7075-il | 200,000 | 9 | 81.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7075-il | 200,000 | 5 | 74 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7075-il | 500,000 | 9 | 108 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7075-il | 500,000 | 5 | 91.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7075-il | 1,000,000 | 9 | 123 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7075-il | 1,000,000 | 5 | 101.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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