S3010-103-84 (s3010-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3010-103-84 (s3010-il) Reynolds number: 500,000 Max Cl/Cd: 95.79 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3010-il-500000.txt Download as CSV file: xf-s3010-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S3010-103-84
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4381 0.07353 0.07142 -0.0328 1.0000 0.0265
-8.250 -0.4567 0.06271 0.06058 -0.0449 1.0000 0.0265
-8.000 -0.4808 0.05319 0.05086 -0.0518 1.0000 0.0269
-7.750 -0.4695 0.05138 0.04914 -0.0514 1.0000 0.0273
-7.500 -0.4618 0.04942 0.04717 -0.0514 1.0000 0.0277
-7.250 -0.4409 0.04640 0.04407 -0.0548 0.9908 0.0284
-7.000 -0.4140 0.04176 0.03921 -0.0603 0.9787 0.0297
-6.750 -0.3866 0.03761 0.03419 -0.0647 0.9618 0.0329
-6.500 -0.3870 0.02206 0.01748 -0.0649 0.9434 0.0201
-6.250 -0.3682 0.01892 0.01384 -0.0635 0.9294 0.0190
-6.000 -0.3461 0.01719 0.01179 -0.0623 0.9166 0.0188
-5.750 -0.3226 0.01592 0.01029 -0.0613 0.9047 0.0188
-5.500 -0.2985 0.01496 0.00916 -0.0604 0.8936 0.0191
-5.250 -0.2739 0.01410 0.00815 -0.0595 0.8829 0.0193
-5.000 -0.2482 0.01344 0.00740 -0.0589 0.8714 0.0199
-4.750 -0.2223 0.01289 0.00674 -0.0583 0.8607 0.0207
-4.500 -0.1964 0.01232 0.00606 -0.0577 0.8505 0.0211
-4.250 -0.1702 0.01169 0.00534 -0.0572 0.8394 0.0215
-4.000 -0.1442 0.01093 0.00452 -0.0568 0.8287 0.0226
-3.750 -0.1174 0.01053 0.00405 -0.0564 0.8185 0.0239
-3.500 -0.0901 0.01021 0.00365 -0.0560 0.8074 0.0256
-3.250 -0.0627 0.00983 0.00322 -0.0558 0.7965 0.0284
-3.000 -0.0352 0.00951 0.00287 -0.0555 0.7858 0.0361
-2.750 -0.0085 0.00889 0.00251 -0.0553 0.7749 0.1014
-2.500 0.0189 0.00855 0.00233 -0.0552 0.7633 0.1536
-2.250 0.0463 0.00829 0.00219 -0.0551 0.7521 0.2055
-2.000 0.0735 0.00798 0.00207 -0.0550 0.7408 0.2755
-1.750 0.1007 0.00767 0.00198 -0.0549 0.7288 0.3544
-1.500 0.1277 0.00733 0.00192 -0.0547 0.7165 0.4475
-1.250 0.1547 0.00707 0.00187 -0.0545 0.7044 0.5316
-1.000 0.1815 0.00687 0.00184 -0.0541 0.6922 0.6057
-0.750 0.2076 0.00667 0.00183 -0.0536 0.6799 0.6851
-0.500 0.2335 0.00651 0.00183 -0.0528 0.6670 0.7539
-0.250 0.2585 0.00638 0.00184 -0.0518 0.6542 0.8159
0.000 0.2820 0.00627 0.00184 -0.0504 0.6415 0.8768
0.250 0.3081 0.00621 0.00182 -0.0494 0.6286 0.9387
0.500 0.3505 0.00622 0.00175 -0.0523 0.6137 0.9862
0.750 0.3836 0.00630 0.00172 -0.0533 0.5993 1.0000
1.000 0.4107 0.00640 0.00172 -0.0531 0.5853 1.0000
1.250 0.4379 0.00651 0.00173 -0.0529 0.5713 1.0000
1.500 0.4652 0.00663 0.00176 -0.0527 0.5574 1.0000
1.750 0.4927 0.00675 0.00179 -0.0526 0.5434 1.0000
2.000 0.5203 0.00687 0.00184 -0.0524 0.5293 1.0000
2.250 0.5478 0.00699 0.00190 -0.0523 0.5155 1.0000
2.500 0.5753 0.00713 0.00196 -0.0522 0.5014 1.0000
2.750 0.6028 0.00727 0.00204 -0.0520 0.4876 1.0000
3.000 0.6303 0.00743 0.00213 -0.0519 0.4734 1.0000
3.250 0.6577 0.00759 0.00223 -0.0518 0.4593 1.0000
3.500 0.6850 0.00775 0.00233 -0.0517 0.4450 1.0000
3.750 0.7123 0.00793 0.00245 -0.0515 0.4308 1.0000
4.000 0.7395 0.00811 0.00258 -0.0514 0.4165 1.0000
4.250 0.7667 0.00830 0.00272 -0.0513 0.4019 1.0000
4.500 0.7937 0.00851 0.00287 -0.0511 0.3872 1.0000
4.750 0.8207 0.00872 0.00303 -0.0510 0.3719 1.0000
5.000 0.8475 0.00894 0.00321 -0.0509 0.3566 1.0000
5.250 0.8743 0.00917 0.00340 -0.0507 0.3408 1.0000
5.500 0.9008 0.00942 0.00360 -0.0505 0.3249 1.0000
5.750 0.9272 0.00968 0.00382 -0.0503 0.3085 1.0000
6.000 0.9535 0.00997 0.00405 -0.0501 0.2924 1.0000
6.250 0.9794 0.01027 0.00430 -0.0499 0.2760 1.0000
6.500 1.0052 0.01059 0.00458 -0.0497 0.2600 1.0000
6.750 1.0307 0.01094 0.00487 -0.0494 0.2441 1.0000
7.000 1.0560 0.01130 0.00518 -0.0491 0.2283 1.0000
7.250 1.0811 0.01168 0.00552 -0.0488 0.2130 1.0000
7.500 1.1059 0.01208 0.00587 -0.0485 0.1980 1.0000
7.750 1.1305 0.01249 0.00624 -0.0481 0.1840 1.0000
8.000 1.1549 0.01290 0.00662 -0.0477 0.1708 1.0000
8.250 1.1790 0.01334 0.00704 -0.0473 0.1577 1.0000
8.500 1.2028 0.01379 0.00747 -0.0468 0.1457 1.0000
8.750 1.2262 0.01426 0.00793 -0.0463 0.1345 1.0000
9.000 1.2489 0.01478 0.00843 -0.0458 0.1231 1.0000
9.250 1.2710 0.01534 0.00895 -0.0452 0.1121 1.0000
9.500 1.2923 0.01595 0.00952 -0.0444 0.1011 1.0000
9.750 1.3141 0.01649 0.01005 -0.0438 0.0917 1.0000
10.000 1.3351 0.01706 0.01064 -0.0430 0.0831 1.0000
10.250 1.3548 0.01772 0.01127 -0.0421 0.0748 1.0000
10.500 1.3740 0.01839 0.01194 -0.0412 0.0679 1.0000
10.750 1.3930 0.01902 0.01261 -0.0402 0.0624 1.0000
11.000 1.4097 0.01979 0.01337 -0.0390 0.0569 1.0000
11.250 1.4268 0.02046 0.01411 -0.0377 0.0525 1.0000
11.500 1.4411 0.02125 0.01491 -0.0362 0.0480 1.0000
11.750 1.4524 0.02203 0.01574 -0.0342 0.0444 1.0000
12.000 1.4631 0.02282 0.01658 -0.0322 0.0409 1.0000
12.250 1.4688 0.02397 0.01774 -0.0299 0.0374 1.0000
12.500 1.4797 0.02485 0.01870 -0.0283 0.0342 1.0000
12.750 1.4830 0.02633 0.02020 -0.0264 0.0304 1.0000
13.000 1.4907 0.02761 0.02155 -0.0250 0.0266 1.0000
13.250 1.4922 0.02946 0.02345 -0.0235 0.0231 1.0000
13.500 1.4919 0.03162 0.02565 -0.0223 0.0201 1.0000
13.750 1.4913 0.03397 0.02810 -0.0214 0.0176 1.0000
14.000 1.4904 0.03649 0.03070 -0.0209 0.0166 1.0000
14.250 1.4824 0.03997 0.03426 -0.0207 0.0152 1.0000
14.500 1.4810 0.04288 0.03730 -0.0207 0.0147 1.0000
14.750 1.4769 0.04626 0.04081 -0.0211 0.0140 1.0000
15.000 1.4725 0.04985 0.04451 -0.0218 0.0135 1.0000
15.250 1.4645 0.05407 0.04884 -0.0230 0.0130 1.0000
15.500 1.4550 0.05866 0.05354 -0.0244 0.0127 1.0000
15.750 1.4449 0.06356 0.05857 -0.0262 0.0125 1.0000
16.000 1.4290 0.06959 0.06473 -0.0286 0.0123 1.0000
16.250 1.4127 0.07590 0.07117 -0.0313 0.0120 1.0000
16.500 1.4017 0.08162 0.07702 -0.0339 0.0118 1.0000
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Polar data table (+)
Polar graphs
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