SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SELIG 3002-099-83 (s3002-il) Reynolds number: 50,000 Max Cl/Cd: 39.17 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3002-il-50000-n5.txt Download as CSV file: xf-s3002-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SELIG 3002-099-83
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3734 0.10493 0.09804 -0.0324 1.0000 0.1220
-8.500 -0.3661 0.09739 0.09046 -0.0354 1.0000 0.0772
-8.250 -0.3672 0.09257 0.08571 -0.0370 1.0000 0.0637
-8.000 -0.3665 0.08925 0.08248 -0.0369 1.0000 0.0611
-7.500 -0.3957 0.08005 0.07353 -0.0440 1.0000 0.0535
-7.250 -0.3960 0.07712 0.07067 -0.0433 1.0000 0.0527
-7.000 -0.3994 0.07392 0.06753 -0.0433 1.0000 0.0518
-6.750 -0.4038 0.07060 0.06424 -0.0434 1.0000 0.0509
-6.500 -0.4079 0.06712 0.06075 -0.0437 1.0000 0.0500
-6.250 -0.4104 0.06340 0.05697 -0.0442 1.0000 0.0491
-6.000 -0.4098 0.05946 0.05290 -0.0449 1.0000 0.0482
-5.750 -0.4053 0.05530 0.04852 -0.0459 1.0000 0.0473
-5.500 -0.3963 0.05105 0.04395 -0.0470 1.0000 0.0465
-5.250 -0.3830 0.04716 0.03966 -0.0479 1.0000 0.0463
-5.000 -0.3670 0.04408 0.03626 -0.0484 1.0000 0.0474
-4.750 -0.3482 0.04118 0.03297 -0.0490 1.0000 0.0491
-4.500 -0.3266 0.03829 0.02957 -0.0496 1.0000 0.0509
-4.250 -0.2973 0.03534 0.02604 -0.0510 0.9979 0.0521
-4.000 -0.2592 0.03266 0.02265 -0.0534 0.9927 0.0539
-3.750 -0.2248 0.03085 0.02073 -0.0556 0.9870 0.0585
-3.500 -0.1888 0.02919 0.01870 -0.0572 0.9814 0.0627
-3.250 -0.1539 0.02775 0.01699 -0.0584 0.9753 0.0678
-3.000 -0.1196 0.02671 0.01583 -0.0596 0.9691 0.0756
-2.750 -0.0869 0.02572 0.01474 -0.0604 0.9621 0.0836
-2.500 -0.0513 0.02489 0.01383 -0.0620 0.9556 0.0984
-2.250 -0.0172 0.02400 0.01296 -0.0635 0.9478 0.1253
-2.000 0.0221 0.02236 0.01216 -0.0668 0.9422 0.2583
-1.750 0.0344 0.02097 0.01274 -0.0627 0.9332 0.6764
-1.500 0.0498 0.02103 0.01288 -0.0581 0.9237 0.8186
-1.250 0.0743 0.02077 0.01259 -0.0553 0.9151 0.9142
-1.000 0.1300 0.02062 0.01211 -0.0605 0.9069 1.0000
-0.750 0.1703 0.02071 0.01187 -0.0633 0.8983 1.0000
-0.500 0.2028 0.02084 0.01174 -0.0647 0.8870 1.0000
-0.250 0.2407 0.02094 0.01161 -0.0668 0.8775 1.0000
0.000 0.2776 0.02101 0.01148 -0.0686 0.8674 1.0000
0.250 0.3090 0.02113 0.01143 -0.0694 0.8552 1.0000
0.500 0.3427 0.02122 0.01138 -0.0705 0.8439 1.0000
0.750 0.3817 0.02119 0.01121 -0.0722 0.8343 1.0000
1.000 0.4113 0.02130 0.01122 -0.0725 0.8208 1.0000
1.250 0.4414 0.02139 0.01122 -0.0727 0.8074 1.0000
1.500 0.4719 0.02145 0.01122 -0.0730 0.7939 1.0000
1.750 0.5026 0.02149 0.01120 -0.0731 0.7803 1.0000
2.000 0.5331 0.02152 0.01119 -0.0732 0.7663 1.0000
2.250 0.5629 0.02153 0.01117 -0.0731 0.7517 1.0000
2.500 0.5920 0.02155 0.01116 -0.0728 0.7361 1.0000
2.750 0.6205 0.02158 0.01119 -0.0724 0.7197 1.0000
3.000 0.6488 0.02159 0.01119 -0.0720 0.7025 1.0000
3.250 0.6772 0.02160 0.01119 -0.0715 0.6847 1.0000
3.500 0.7059 0.02158 0.01115 -0.0709 0.6663 1.0000
3.750 0.7325 0.02167 0.01125 -0.0702 0.6458 1.0000
4.000 0.7590 0.02177 0.01135 -0.0695 0.6241 1.0000
4.250 0.7867 0.02184 0.01136 -0.0688 0.6027 1.0000
4.500 0.8118 0.02206 0.01161 -0.0679 0.5785 1.0000
4.750 0.8379 0.02227 0.01176 -0.0671 0.5549 1.0000
5.000 0.8630 0.02257 0.01202 -0.0663 0.5301 1.0000
5.250 0.8874 0.02295 0.01239 -0.0654 0.5051 1.0000
5.500 0.9120 0.02335 0.01270 -0.0645 0.4811 1.0000
5.750 0.9348 0.02389 0.01322 -0.0636 0.4559 1.0000
6.000 0.9578 0.02445 0.01372 -0.0627 0.4321 1.0000
6.250 0.9800 0.02508 0.01436 -0.0618 0.4084 1.0000
6.500 1.0019 0.02577 0.01500 -0.0609 0.3856 1.0000
6.750 1.0231 0.02650 0.01573 -0.0599 0.3631 1.0000
7.000 1.0441 0.02728 0.01649 -0.0590 0.3422 1.0000
7.250 1.0641 0.02813 0.01739 -0.0580 0.3208 1.0000
7.500 1.0838 0.02900 0.01826 -0.0569 0.3011 1.0000
7.750 1.1030 0.02993 0.01915 -0.0559 0.2825 1.0000
8.000 1.1213 0.03093 0.02027 -0.0548 0.2637 1.0000
8.250 1.1389 0.03197 0.02137 -0.0537 0.2459 1.0000
8.500 1.1560 0.03308 0.02252 -0.0525 0.2295 1.0000
8.750 1.1720 0.03424 0.02373 -0.0513 0.2138 1.0000
9.000 1.1876 0.03548 0.02503 -0.0500 0.1994 1.0000
9.250 1.2022 0.03679 0.02644 -0.0487 0.1859 1.0000
9.500 1.2164 0.03820 0.02792 -0.0474 0.1737 1.0000
9.750 1.2296 0.03964 0.02941 -0.0461 0.1627 1.0000
10.000 1.2418 0.04113 0.03095 -0.0447 0.1526 1.0000
10.250 1.2525 0.04286 0.03289 -0.0432 0.1431 1.0000
10.500 1.2626 0.04453 0.03463 -0.0416 0.1352 1.0000
10.750 1.2709 0.04639 0.03668 -0.0401 0.1276 1.0000
11.000 1.2807 0.04837 0.03877 -0.0388 0.1215 1.0000
11.250 1.2857 0.05056 0.04119 -0.0373 0.1154 1.0000
11.500 1.2948 0.05246 0.04307 -0.0361 0.1102 1.0000
11.750 1.2944 0.05540 0.04641 -0.0348 0.1057 1.0000
12.000 1.2968 0.05807 0.04931 -0.0337 0.1018 1.0000
12.250 1.3075 0.06008 0.05125 -0.0329 0.0978 1.0000
12.500 1.2952 0.06416 0.05578 -0.0322 0.0953 1.0000
12.750 1.2831 0.06845 0.06040 -0.0320 0.0928 1.0000
13.000 1.2718 0.07287 0.06507 -0.0324 0.0906 1.0000
13.250 1.2628 0.07723 0.06961 -0.0330 0.0886 1.0000
13.500 1.2624 0.08074 0.07321 -0.0334 0.0865 1.0000
13.750 1.2496 0.08608 0.07871 -0.0350 0.0851 1.0000
14.000 1.2182 0.09453 0.08744 -0.0390 0.0850 1.0000
14.250 1.1809 0.10506 0.09819 -0.0450 0.0851 1.0000
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Polar data table (+)
Polar graphs
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