S3010-103-84 (s3010-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3010-103-84 (s3010-il) Reynolds number: 200,000 Max Cl/Cd: 68.79 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3010-il-200000-n5.txt Download as CSV file: xf-s3010-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3524 0.10382 0.10045 -0.0143 1.0000 0.0213
-10.250 -0.4411 0.10681 0.10315 -0.0121 1.0000 0.0214
-10.000 -0.4359 0.10336 0.09972 -0.0133 1.0000 0.0207
-9.500 -0.4482 0.08976 0.08619 -0.0203 1.0000 0.0173
-9.250 -0.4471 0.08573 0.08219 -0.0223 1.0000 0.0172
-9.000 -0.4474 0.08151 0.07801 -0.0246 1.0000 0.0170
-8.750 -0.4515 0.07641 0.07297 -0.0276 1.0000 0.0169
-8.500 -0.4571 0.07129 0.06791 -0.0310 1.0000 0.0167
-8.250 -0.4692 0.06504 0.06175 -0.0359 1.0000 0.0165
-8.000 -0.4857 0.05300 0.04959 -0.0476 1.0000 0.0160
-7.750 -0.5017 0.04351 0.03971 -0.0525 1.0000 0.0157
-7.500 -0.5032 0.03723 0.03295 -0.0541 0.9957 0.0155
-7.250 -0.4804 0.03135 0.02636 -0.0582 0.9797 0.0156
-7.000 -0.4527 0.02784 0.02228 -0.0605 0.9678 0.0161
-6.750 -0.4233 0.02521 0.01911 -0.0622 0.9570 0.0169
-6.500 -0.3947 0.02320 0.01664 -0.0630 0.9455 0.0173
-6.250 -0.3670 0.02155 0.01467 -0.0633 0.9338 0.0174
-6.000 -0.3402 0.02009 0.01298 -0.0633 0.9224 0.0176
-5.750 -0.3144 0.01883 0.01158 -0.0631 0.9111 0.0180
-5.500 -0.2892 0.01786 0.01050 -0.0626 0.8994 0.0185
-5.250 -0.2643 0.01704 0.00958 -0.0620 0.8875 0.0189
-5.000 -0.2393 0.01630 0.00874 -0.0613 0.8760 0.0196
-4.750 -0.2143 0.01563 0.00796 -0.0606 0.8649 0.0204
-4.500 -0.1890 0.01505 0.00726 -0.0599 0.8535 0.0213
-4.250 -0.1634 0.01450 0.00662 -0.0594 0.8419 0.0229
-4.000 -0.1375 0.01406 0.00612 -0.0589 0.8308 0.0250
-3.750 -0.1113 0.01364 0.00556 -0.0583 0.8200 0.0271
-3.500 -0.0850 0.01318 0.00505 -0.0579 0.8084 0.0304
-3.250 -0.0583 0.01275 0.00459 -0.0574 0.7971 0.0389
-3.000 -0.0319 0.01229 0.00420 -0.0570 0.7861 0.0664
-2.750 -0.0056 0.01186 0.00391 -0.0567 0.7749 0.1115
-2.500 0.0209 0.01146 0.00371 -0.0565 0.7631 0.1685
-2.250 0.0471 0.01103 0.00354 -0.0563 0.7516 0.2453
-2.000 0.0735 0.01069 0.00338 -0.0560 0.7402 0.3161
-1.750 0.1000 0.01041 0.00325 -0.0557 0.7285 0.3810
-1.500 0.1263 0.01013 0.00317 -0.0553 0.7163 0.4559
-1.250 0.1523 0.00987 0.00310 -0.0547 0.7042 0.5296
-1.000 0.1780 0.00967 0.00305 -0.0540 0.6922 0.5990
-0.750 0.2031 0.00949 0.00301 -0.0531 0.6800 0.6665
-0.500 0.2275 0.00933 0.00299 -0.0519 0.6674 0.7329
-0.250 0.2514 0.00920 0.00297 -0.0505 0.6544 0.7968
0.000 0.2764 0.00911 0.00294 -0.0492 0.6415 0.8590
0.250 0.3080 0.00906 0.00287 -0.0494 0.6280 0.9217
0.500 0.3494 0.00905 0.00276 -0.0520 0.6135 0.9809
0.750 0.3805 0.00914 0.00271 -0.0526 0.5995 1.0000
1.000 0.4071 0.00926 0.00270 -0.0523 0.5860 1.0000
1.250 0.4339 0.00938 0.00271 -0.0520 0.5725 1.0000
1.500 0.4607 0.00952 0.00273 -0.0517 0.5585 1.0000
1.750 0.4876 0.00966 0.00277 -0.0515 0.5443 1.0000
2.000 0.5145 0.00981 0.00283 -0.0512 0.5299 1.0000
2.250 0.5414 0.00996 0.00290 -0.0510 0.5156 1.0000
2.500 0.5683 0.01013 0.00298 -0.0507 0.5016 1.0000
2.750 0.5952 0.01030 0.00308 -0.0505 0.4878 1.0000
3.000 0.6221 0.01048 0.00320 -0.0503 0.4738 1.0000
3.250 0.6489 0.01068 0.00333 -0.0501 0.4600 1.0000
3.500 0.6756 0.01088 0.00347 -0.0498 0.4458 1.0000
3.750 0.7022 0.01109 0.00363 -0.0496 0.4316 1.0000
4.000 0.7287 0.01132 0.00381 -0.0493 0.4171 1.0000
4.250 0.7551 0.01156 0.00399 -0.0491 0.4023 1.0000
4.500 0.7813 0.01180 0.00419 -0.0488 0.3872 1.0000
4.750 0.8075 0.01206 0.00443 -0.0486 0.3723 1.0000
5.000 0.8335 0.01234 0.00466 -0.0483 0.3571 1.0000
5.250 0.8593 0.01263 0.00491 -0.0480 0.3416 1.0000
5.500 0.8850 0.01293 0.00518 -0.0477 0.3261 1.0000
5.750 0.9104 0.01326 0.00549 -0.0474 0.3105 1.0000
6.000 0.9356 0.01360 0.00580 -0.0471 0.2947 1.0000
6.250 0.9606 0.01397 0.00614 -0.0467 0.2791 1.0000
6.500 0.9853 0.01436 0.00652 -0.0463 0.2636 1.0000
6.750 1.0097 0.01477 0.00690 -0.0459 0.2487 1.0000
7.000 1.0338 0.01520 0.00732 -0.0455 0.2341 1.0000
7.250 1.0577 0.01565 0.00776 -0.0450 0.2197 1.0000
7.500 1.0811 0.01613 0.00824 -0.0445 0.2054 1.0000
7.750 1.1042 0.01663 0.00873 -0.0440 0.1921 1.0000
8.000 1.1269 0.01717 0.00925 -0.0434 0.1789 1.0000
8.250 1.1492 0.01772 0.00982 -0.0428 0.1665 1.0000
8.500 1.1708 0.01831 0.01041 -0.0421 0.1543 1.0000
8.750 1.1918 0.01895 0.01104 -0.0414 0.1429 1.0000
9.000 1.2127 0.01956 0.01168 -0.0407 0.1321 1.0000
9.250 1.2330 0.02021 0.01237 -0.0399 0.1223 1.0000
9.500 1.2521 0.02093 0.01312 -0.0389 0.1135 1.0000
9.750 1.2702 0.02169 0.01390 -0.0379 0.1051 1.0000
10.000 1.2884 0.02242 0.01471 -0.0369 0.0979 1.0000
10.250 1.3035 0.02332 0.01561 -0.0355 0.0912 1.0000
10.500 1.3198 0.02409 0.01650 -0.0343 0.0845 1.0000
10.750 1.3313 0.02508 0.01751 -0.0326 0.0787 1.0000
11.000 1.3431 0.02594 0.01846 -0.0309 0.0727 1.0000
11.250 1.3503 0.02710 0.01963 -0.0289 0.0675 1.0000
11.500 1.3606 0.02813 0.02076 -0.0273 0.0617 1.0000
11.750 1.3663 0.02952 0.02216 -0.0257 0.0567 1.0000
12.000 1.3750 0.03079 0.02354 -0.0245 0.0518 1.0000
12.250 1.3794 0.03245 0.02526 -0.0232 0.0483 1.0000
12.500 1.3855 0.03408 0.02700 -0.0222 0.0451 1.0000
12.750 1.3902 0.03591 0.02893 -0.0214 0.0418 1.0000
13.000 1.3910 0.03821 0.03129 -0.0208 0.0391 1.0000
13.250 1.3951 0.04031 0.03353 -0.0204 0.0365 1.0000
13.500 1.3965 0.04278 0.03612 -0.0203 0.0339 1.0000
13.750 1.3942 0.04578 0.03920 -0.0204 0.0319 1.0000
14.000 1.3938 0.04871 0.04228 -0.0207 0.0299 1.0000
14.250 1.3915 0.05199 0.04570 -0.0213 0.0279 1.0000
14.500 1.3859 0.05583 0.04965 -0.0222 0.0261 1.0000
14.750 1.3785 0.06008 0.05402 -0.0235 0.0248 1.0000
15.000 1.3727 0.06427 0.05837 -0.0249 0.0234 1.0000
15.250 1.3643 0.06901 0.06326 -0.0267 0.0220 1.0000
15.500 1.3537 0.07430 0.06867 -0.0289 0.0210 1.0000
15.750 1.3412 0.08012 0.07461 -0.0316 0.0203 1.0000
16.000 1.3289 0.08611 0.08075 -0.0343 0.0195 1.0000
16.250 1.3172 0.09221 0.08700 -0.0373 0.0187 1.0000
16.500 1.3046 0.09862 0.09357 -0.0404 0.0181 1.0000
16.750 1.2911 0.10538 0.10047 -0.0439 0.0176 1.0000
17.000 1.2776 0.11233 0.10756 -0.0475 0.0172 1.0000
17.250 1.2635 0.11958 0.11495 -0.0515 0.0168 1.0000
17.500 1.2501 0.12679 0.12228 -0.0554 0.0166 1.0000
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Polar data table (+)
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