S3021-095-84 (s3021-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3021-095-84 (s3021-il) Reynolds number: 500,000 Max Cl/Cd: 91.64 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3021-il-500000-n5.txt Download as CSV file: xf-s3021-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4111 0.08564 0.08342 -0.0283 1.0000 0.0061
-8.750 -0.4162 0.08059 0.07841 -0.0305 1.0000 0.0064
-8.500 -0.4197 0.07669 0.07454 -0.0322 1.0000 0.0062
-8.250 -0.4278 0.07242 0.07033 -0.0340 1.0000 0.0063
-8.000 -0.4425 0.06814 0.06610 -0.0357 1.0000 0.0064
-7.750 -0.4487 0.06342 0.06140 -0.0393 0.9998 0.0061
-7.500 -0.4367 0.05040 0.04820 -0.0541 0.9856 0.0063
-7.250 -0.4360 0.03234 0.02938 -0.0634 0.9687 0.0065
-7.000 -0.4226 0.02546 0.02176 -0.0648 0.9528 0.0064
-6.750 -0.4023 0.02157 0.01727 -0.0650 0.9366 0.0065
-6.500 -0.3793 0.01906 0.01429 -0.0647 0.9189 0.0065
-6.000 -0.3323 0.01610 0.01062 -0.0633 0.8806 0.0067
-5.750 -0.3101 0.01460 0.00882 -0.0623 0.8620 0.0070
-5.500 -0.2864 0.01374 0.00775 -0.0615 0.8444 0.0073
-5.250 -0.2617 0.01315 0.00702 -0.0609 0.8282 0.0077
-5.000 -0.2366 0.01265 0.00637 -0.0603 0.8129 0.0082
-4.750 -0.2113 0.01216 0.00574 -0.0597 0.7987 0.0087
-4.500 -0.1858 0.01169 0.00512 -0.0592 0.7852 0.0093
-4.000 -0.1342 0.01086 0.00406 -0.0582 0.7600 0.0111
-3.750 -0.1080 0.01055 0.00367 -0.0579 0.7484 0.0124
-3.500 -0.0815 0.01026 0.00328 -0.0575 0.7373 0.0136
-3.250 -0.0549 0.01002 0.00292 -0.0571 0.7269 0.0152
-3.000 -0.0283 0.00974 0.00258 -0.0568 0.7165 0.0188
-2.750 -0.0014 0.00952 0.00233 -0.0565 0.7067 0.0266
-2.500 0.0252 0.00929 0.00212 -0.0562 0.6972 0.0449
-2.250 0.0518 0.00905 0.00194 -0.0560 0.6878 0.0760
-2.000 0.0786 0.00884 0.00181 -0.0558 0.6786 0.1104
-1.750 0.1050 0.00859 0.00169 -0.0556 0.6698 0.1620
-1.500 0.1311 0.00828 0.00160 -0.0554 0.6606 0.2395
-1.250 0.1576 0.00806 0.00152 -0.0552 0.6516 0.3021
-1.000 0.1840 0.00787 0.00146 -0.0549 0.6428 0.3634
-0.750 0.2099 0.00760 0.00142 -0.0546 0.6332 0.4493
-0.500 0.2351 0.00730 0.00139 -0.0542 0.6238 0.5476
-0.250 0.2592 0.00699 0.00137 -0.0534 0.6143 0.6562
0.000 0.2820 0.00666 0.00139 -0.0521 0.6044 0.7715
0.250 0.3060 0.00641 0.00146 -0.0508 0.5950 0.8896
0.500 0.3474 0.00646 0.00149 -0.0534 0.5843 0.9537
0.750 0.3855 0.00654 0.00149 -0.0555 0.5732 0.9750
1.000 0.4228 0.00661 0.00149 -0.0575 0.5620 0.9862
1.250 0.4605 0.00668 0.00149 -0.0597 0.5506 0.9942
1.500 0.4988 0.00676 0.00149 -0.0621 0.5382 1.0000
1.750 0.5236 0.00685 0.00152 -0.0614 0.5270 1.0000
2.000 0.5484 0.00696 0.00157 -0.0608 0.5147 1.0000
2.500 0.5980 0.00719 0.00168 -0.0595 0.4886 1.0000
2.750 0.6227 0.00732 0.00175 -0.0589 0.4742 1.0000
3.000 0.6474 0.00747 0.00185 -0.0582 0.4589 1.0000
3.250 0.6720 0.00762 0.00195 -0.0576 0.4430 1.0000
3.500 0.6965 0.00779 0.00206 -0.0569 0.4262 1.0000
3.750 0.7208 0.00798 0.00218 -0.0563 0.4089 1.0000
4.000 0.7450 0.00819 0.00234 -0.0556 0.3905 1.0000
4.250 0.7693 0.00841 0.00249 -0.0549 0.3714 1.0000
4.500 0.7934 0.00866 0.00266 -0.0543 0.3509 1.0000
4.750 0.8174 0.00892 0.00285 -0.0536 0.3303 1.0000
5.000 0.8413 0.00921 0.00308 -0.0529 0.3089 1.0000
5.250 0.8651 0.00951 0.00330 -0.0523 0.2891 1.0000
5.500 0.8890 0.00981 0.00354 -0.0517 0.2691 1.0000
5.750 0.9127 0.01014 0.00381 -0.0510 0.2503 1.0000
6.000 0.9364 0.01047 0.00409 -0.0504 0.2316 1.0000
6.250 0.9599 0.01081 0.00438 -0.0497 0.2130 1.0000
6.500 0.9829 0.01121 0.00471 -0.0490 0.1933 1.0000
6.750 1.0060 0.01160 0.00504 -0.0484 0.1740 1.0000
7.000 1.0287 0.01201 0.00540 -0.0476 0.1563 1.0000
7.250 1.0512 0.01245 0.00580 -0.0469 0.1398 1.0000
7.500 1.0733 0.01291 0.00621 -0.0461 0.1222 1.0000
7.750 1.0938 0.01351 0.00669 -0.0451 0.0998 1.0000
8.000 1.1142 0.01410 0.00719 -0.0441 0.0800 1.0000
8.250 1.1343 0.01470 0.00772 -0.0431 0.0648 1.0000
8.500 1.1543 0.01529 0.00829 -0.0421 0.0521 1.0000
8.750 1.1737 0.01592 0.00887 -0.0409 0.0402 1.0000
9.000 1.1925 0.01656 0.00949 -0.0397 0.0303 1.0000
9.250 1.2101 0.01728 0.01018 -0.0384 0.0211 1.0000
9.500 1.2258 0.01811 0.01098 -0.0368 0.0129 1.0000
9.750 1.2420 0.01886 0.01176 -0.0353 0.0096 1.0000
10.000 1.2567 0.01968 0.01261 -0.0335 0.0076 1.0000
10.250 1.2720 0.02037 0.01340 -0.0318 0.0069 1.0000
10.500 1.2841 0.02111 0.01425 -0.0296 0.0063 1.0000
10.750 1.2940 0.02195 0.01516 -0.0272 0.0057 1.0000
11.000 1.3015 0.02297 0.01627 -0.0246 0.0052 1.0000
11.250 1.3069 0.02416 0.01757 -0.0220 0.0048 1.0000
11.500 1.3150 0.02522 0.01874 -0.0200 0.0046 1.0000
11.750 1.3216 0.02645 0.02008 -0.0180 0.0044 1.0000
12.000 1.3268 0.02785 0.02160 -0.0162 0.0043 1.0000
12.250 1.3308 0.02944 0.02330 -0.0146 0.0041 1.0000
12.500 1.3354 0.03107 0.02505 -0.0133 0.0039 1.0000
12.750 1.3366 0.03312 0.02722 -0.0121 0.0038 1.0000
13.000 1.3390 0.03519 0.02940 -0.0113 0.0036 1.0000
13.250 1.3390 0.03761 0.03196 -0.0106 0.0035 1.0000
13.500 1.3390 0.04016 0.03462 -0.0103 0.0034 1.0000
13.750 1.3390 0.04282 0.03739 -0.0102 0.0032 1.0000
14.000 1.3323 0.04639 0.04108 -0.0104 0.0031 1.0000
14.250 1.3224 0.05053 0.04536 -0.0110 0.0030 1.0000
14.500 1.3141 0.05469 0.04965 -0.0119 0.0029 1.0000
14.750 1.3058 0.05903 0.05414 -0.0130 0.0029 1.0000
15.000 1.3030 0.06278 0.05801 -0.0142 0.0029 1.0000
15.250 1.2939 0.06761 0.06298 -0.0160 0.0029 1.0000
15.500 1.2852 0.07264 0.06815 -0.0179 0.0028 1.0000
15.750 1.2764 0.07786 0.07351 -0.0201 0.0028 1.0000
16.000 1.2644 0.08384 0.07963 -0.0228 0.0027 1.0000
16.250 1.2554 0.08951 0.08544 -0.0254 0.0027 1.0000
16.500 1.2439 0.09579 0.09185 -0.0285 0.0027 1.0000
16.750 1.2324 0.10222 0.09842 -0.0316 0.0027 1.0000
17.000 1.2207 0.10886 0.10518 -0.0350 0.0027 1.0000
17.250 1.2084 0.11578 0.11223 -0.0386 0.0027 1.0000
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Polar data table (+)
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