S3021-095-84 (s3021-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3021-095-84 (s3021-il) Reynolds number: 50,000 Max Cl/Cd: 32.24 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3021-il-50000.txt Download as CSV file: xf-s3021-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S3021-095-84
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3930 0.10745 0.10070 -0.0162 1.0000 0.2196
-8.500 -0.3823 0.10336 0.09665 -0.0159 1.0000 0.2269
-8.250 -0.3995 0.10277 0.09622 -0.0176 1.0000 0.2356
-8.000 -0.3765 0.09764 0.09107 -0.0161 1.0000 0.2460
-7.750 -0.3752 0.09467 0.08820 -0.0161 1.0000 0.2551
-7.500 -0.3980 0.09433 0.08805 -0.0167 1.0000 0.2650
-7.250 -0.3811 0.09012 0.08385 -0.0153 1.0000 0.2783
-7.000 -0.3718 0.08663 0.08042 -0.0141 1.0000 0.2905
-6.750 -0.3705 0.08386 0.07775 -0.0127 1.0000 0.3035
-6.500 -0.3723 0.08143 0.07541 -0.0110 1.0000 0.3183
-6.250 -0.3776 0.07932 0.07344 -0.0092 1.0000 0.3356
-6.000 -0.3922 0.07787 0.07216 -0.0079 1.0000 0.3529
-5.750 -0.3732 0.07412 0.06844 -0.0042 1.0000 0.3749
-5.500 -0.3801 0.07213 0.06660 -0.0009 1.0000 0.4003
-5.250 -0.3893 0.07073 0.06533 0.0028 1.0000 0.4263
-4.500 -0.3736 0.04814 0.04118 -0.0345 1.0000 0.1480
-4.250 -0.3576 0.04396 0.03649 -0.0347 1.0000 0.1335
-4.000 -0.3427 0.04095 0.03330 -0.0339 1.0000 0.1292
-3.750 -0.3213 0.03755 0.02898 -0.0339 1.0000 0.1196
-3.500 -0.3023 0.03503 0.02619 -0.0332 1.0000 0.1173
-3.250 -0.2812 0.03276 0.02351 -0.0325 1.0000 0.1156
-3.000 -0.2590 0.03090 0.02123 -0.0318 1.0000 0.1154
-2.750 -0.2361 0.02932 0.01922 -0.0310 1.0000 0.1174
-2.500 -0.2144 0.02801 0.01769 -0.0302 1.0000 0.1235
-2.250 -0.1928 0.02706 0.01650 -0.0294 1.0000 0.1336
-2.000 -0.1707 0.02597 0.01537 -0.0285 1.0000 0.1472
-1.750 -0.1469 0.02486 0.01437 -0.0278 1.0000 0.1804
-1.500 -0.1069 0.01997 0.01294 -0.0274 1.0000 1.0000
-1.250 -0.0887 0.02038 0.01273 -0.0268 1.0000 1.0000
-1.000 -0.0711 0.02084 0.01272 -0.0262 1.0000 1.0000
-0.750 -0.0537 0.02133 0.01285 -0.0257 1.0000 1.0000
-0.500 -0.0174 0.02218 0.01328 -0.0288 0.9925 1.0000
-0.250 0.0284 0.02317 0.01386 -0.0335 0.9798 1.0000
0.000 0.0723 0.02411 0.01449 -0.0379 0.9668 1.0000
0.250 0.1148 0.02502 0.01514 -0.0418 0.9538 1.0000
0.500 0.1564 0.02588 0.01577 -0.0454 0.9406 1.0000
0.750 0.1977 0.02671 0.01641 -0.0489 0.9273 1.0000
1.000 0.2384 0.02750 0.01706 -0.0522 0.9138 1.0000
1.250 0.2768 0.02824 0.01768 -0.0549 0.9000 1.0000
1.500 0.3129 0.02895 0.01831 -0.0571 0.8858 1.0000
1.750 0.3486 0.02965 0.01895 -0.0591 0.8715 1.0000
2.000 0.3843 0.03032 0.01958 -0.0610 0.8570 1.0000
2.250 0.4203 0.03096 0.02021 -0.0628 0.8423 1.0000
2.500 0.4568 0.03155 0.02081 -0.0645 0.8275 1.0000
2.750 0.4927 0.03210 0.02139 -0.0659 0.8125 1.0000
3.000 0.5215 0.03276 0.02208 -0.0663 0.7965 1.0000
3.250 0.5510 0.03337 0.02274 -0.0666 0.7802 1.0000
3.500 0.5811 0.03393 0.02339 -0.0668 0.7638 1.0000
3.750 0.6118 0.03442 0.02395 -0.0669 0.7476 1.0000
4.000 0.6437 0.03478 0.02441 -0.0668 0.7311 1.0000
4.250 0.6773 0.03498 0.02475 -0.0667 0.7147 1.0000
4.500 0.7121 0.03500 0.02489 -0.0664 0.6985 1.0000
4.750 0.7476 0.03485 0.02487 -0.0659 0.6823 1.0000
5.000 0.7639 0.03571 0.02583 -0.0639 0.6623 1.0000
5.250 0.7928 0.03577 0.02606 -0.0626 0.6438 1.0000
5.500 0.8274 0.03532 0.02576 -0.0614 0.6262 1.0000
5.750 0.8553 0.03525 0.02582 -0.0597 0.6068 1.0000
6.000 0.8792 0.03539 0.02611 -0.0578 0.5858 1.0000
6.250 0.9179 0.03429 0.02516 -0.0563 0.5666 1.0000
6.500 0.9360 0.03482 0.02585 -0.0541 0.5432 1.0000
6.750 0.9691 0.03404 0.02516 -0.0522 0.5210 1.0000
7.000 0.9961 0.03374 0.02500 -0.0502 0.4965 1.0000
7.250 1.0193 0.03377 0.02514 -0.0481 0.4706 1.0000
7.500 1.0443 0.03367 0.02511 -0.0460 0.4436 1.0000
7.750 1.0685 0.03372 0.02520 -0.0439 0.4156 1.0000
8.000 1.0911 0.03398 0.02546 -0.0418 0.3865 1.0000
8.250 1.1121 0.03449 0.02600 -0.0397 0.3570 1.0000
8.500 1.1316 0.03528 0.02676 -0.0376 0.3277 1.0000
8.750 1.1498 0.03625 0.02769 -0.0355 0.2984 1.0000
9.000 1.1665 0.03740 0.02876 -0.0333 0.2688 1.0000
9.250 1.1829 0.03868 0.02984 -0.0312 0.2380 1.0000
9.500 1.1901 0.04035 0.03157 -0.0283 0.2081 1.0000
9.750 1.1887 0.04150 0.03266 -0.0247 0.1769 1.0000
10.000 1.1849 0.04294 0.03395 -0.0212 0.1487 1.0000
10.250 1.1845 0.04537 0.03623 -0.0182 0.1243 1.0000
10.500 1.1876 0.04828 0.03920 -0.0157 0.1076 1.0000
10.750 1.1961 0.05197 0.04306 -0.0139 0.0973 1.0000
11.000 1.2107 0.05560 0.04663 -0.0129 0.0889 1.0000
11.250 1.2008 0.05912 0.05067 -0.0100 0.0866 1.0000
11.500 1.1892 0.06277 0.05469 -0.0075 0.0850 1.0000
11.750 1.1749 0.06644 0.05865 -0.0056 0.0832 1.0000
12.000 1.1575 0.07069 0.06318 -0.0045 0.0827 1.0000
12.250 1.1335 0.07583 0.06861 -0.0046 0.0837 1.0000
12.500 1.1062 0.08172 0.07473 -0.0061 0.0846 1.0000
12.750 1.0805 0.08845 0.08164 -0.0087 0.0865 1.0000
13.000 1.0581 0.09557 0.08887 -0.0118 0.0880 1.0000
13.250 1.0355 0.10335 0.09673 -0.0157 0.0890 1.0000
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Polar data table (+)
Polar graphs
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