S3014-095-85 (s3014-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S3014-095-85 (s3014-il) Reynolds number: 100,000 Max Cl/Cd: 51.41 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3014-il-100000-n5.txt Download as CSV file: xf-s3014-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S3014-095-85
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4468 0.07940 0.07477 -0.0333 1.0000 0.0295
-8.250 -0.4503 0.07503 0.07047 -0.0360 1.0000 0.0291
-8.000 -0.4539 0.07047 0.06596 -0.0393 1.0000 0.0288
-7.750 -0.4561 0.06545 0.06093 -0.0426 1.0000 0.0284
-7.500 -0.4598 0.06034 0.05577 -0.0449 1.0000 0.0281
-7.250 -0.4653 0.05585 0.05119 -0.0455 1.0000 0.0278
-7.000 -0.4726 0.05214 0.04735 -0.0442 1.0000 0.0277
-6.750 -0.4800 0.04861 0.04361 -0.0422 1.0000 0.0280
-6.500 -0.4689 0.04364 0.03817 -0.0437 0.9941 0.0287
-6.250 -0.4451 0.03878 0.03264 -0.0465 0.9855 0.0293
-6.000 -0.4195 0.03480 0.02810 -0.0483 0.9783 0.0292
-5.750 -0.3908 0.03142 0.02416 -0.0499 0.9721 0.0292
-5.500 -0.3612 0.02870 0.02091 -0.0510 0.9660 0.0294
-5.250 -0.3301 0.02647 0.01821 -0.0521 0.9602 0.0297
-5.000 -0.2971 0.02438 0.01578 -0.0534 0.9556 0.0303
-4.750 -0.2690 0.02276 0.01401 -0.0537 0.9485 0.0314
-4.500 -0.2360 0.02173 0.01286 -0.0550 0.9434 0.0344
-4.250 -0.2075 0.02075 0.01173 -0.0551 0.9361 0.0368
-4.000 -0.1763 0.01972 0.01057 -0.0557 0.9302 0.0381
-3.750 -0.1489 0.01893 0.00964 -0.0555 0.9226 0.0397
-3.500 -0.1196 0.01810 0.00873 -0.0557 0.9162 0.0424
-3.250 -0.0930 0.01752 0.00804 -0.0554 0.9082 0.0471
-3.000 -0.0640 0.01688 0.00737 -0.0555 0.9016 0.0585
-2.750 -0.0397 0.01609 0.00692 -0.0549 0.8932 0.1209
-2.500 -0.0131 0.01528 0.00664 -0.0549 0.8867 0.2433
-2.250 0.0088 0.01456 0.00650 -0.0539 0.8777 0.3908
-2.000 0.0322 0.01372 0.00643 -0.0527 0.8710 0.5848
-1.750 0.0564 0.01316 0.00646 -0.0507 0.8628 0.7644
-1.500 0.1125 0.01287 0.00623 -0.0550 0.8590 0.8966
-1.250 0.1697 0.01277 0.00596 -0.0605 0.8527 0.9642
-1.000 0.2200 0.01267 0.00566 -0.0649 0.8460 1.0000
-0.750 0.2419 0.01270 0.00553 -0.0637 0.8353 1.0000
-0.500 0.2645 0.01273 0.00541 -0.0626 0.8253 1.0000
-0.250 0.2875 0.01274 0.00528 -0.0614 0.8155 1.0000
0.000 0.3100 0.01279 0.00522 -0.0602 0.8039 1.0000
0.250 0.3329 0.01283 0.00516 -0.0590 0.7923 1.0000
0.500 0.3560 0.01286 0.00509 -0.0578 0.7805 1.0000
0.750 0.3793 0.01288 0.00502 -0.0566 0.7684 1.0000
1.000 0.4028 0.01290 0.00495 -0.0555 0.7559 1.0000
1.250 0.4265 0.01293 0.00490 -0.0543 0.7427 1.0000
1.500 0.4503 0.01297 0.00487 -0.0533 0.7288 1.0000
1.750 0.4743 0.01301 0.00486 -0.0522 0.7141 1.0000
2.000 0.4984 0.01307 0.00487 -0.0512 0.6988 1.0000
2.250 0.5227 0.01314 0.00489 -0.0503 0.6829 1.0000
2.500 0.5470 0.01322 0.00492 -0.0493 0.6663 1.0000
2.750 0.5715 0.01331 0.00497 -0.0484 0.6490 1.0000
3.000 0.5960 0.01341 0.00501 -0.0474 0.6313 1.0000
3.250 0.6203 0.01355 0.00511 -0.0466 0.6113 1.0000
3.500 0.6446 0.01370 0.00520 -0.0456 0.5907 1.0000
3.750 0.6687 0.01389 0.00537 -0.0448 0.5686 1.0000
4.000 0.6927 0.01410 0.00551 -0.0438 0.5454 1.0000
4.250 0.7164 0.01435 0.00570 -0.0429 0.5204 1.0000
4.500 0.7399 0.01463 0.00592 -0.0420 0.4943 1.0000
4.750 0.7631 0.01496 0.00620 -0.0411 0.4674 1.0000
5.000 0.7860 0.01532 0.00649 -0.0401 0.4401 1.0000
5.250 0.8086 0.01573 0.00682 -0.0392 0.4129 1.0000
5.500 0.8308 0.01617 0.00719 -0.0383 0.3861 1.0000
5.750 0.8528 0.01665 0.00760 -0.0373 0.3608 1.0000
6.000 0.8746 0.01716 0.00809 -0.0364 0.3362 1.0000
6.250 0.8963 0.01769 0.00859 -0.0355 0.3138 1.0000
6.500 0.9174 0.01827 0.00912 -0.0345 0.2927 1.0000
6.750 0.9387 0.01884 0.00969 -0.0336 0.2731 1.0000
7.000 0.9596 0.01945 0.01030 -0.0326 0.2544 1.0000
7.250 0.9800 0.02009 0.01093 -0.0316 0.2372 1.0000
7.500 1.0000 0.02076 0.01164 -0.0306 0.2211 1.0000
7.750 1.0200 0.02142 0.01237 -0.0296 0.2052 1.0000
8.000 1.0395 0.02212 0.01312 -0.0285 0.1901 1.0000
8.250 1.0584 0.02285 0.01392 -0.0274 0.1757 1.0000
8.500 1.0767 0.02363 0.01476 -0.0262 0.1623 1.0000
8.750 1.0941 0.02445 0.01564 -0.0250 0.1495 1.0000
9.000 1.1105 0.02533 0.01661 -0.0237 0.1375 1.0000
9.250 1.1259 0.02623 0.01758 -0.0223 0.1249 1.0000
9.500 1.1407 0.02711 0.01854 -0.0209 0.1093 1.0000
9.750 1.1541 0.02806 0.01953 -0.0195 0.0923 1.0000
10.000 1.1644 0.02921 0.02058 -0.0179 0.0742 1.0000
10.250 1.1739 0.03037 0.02180 -0.0160 0.0601 1.0000
10.500 1.1801 0.03180 0.02328 -0.0138 0.0478 1.0000
10.750 1.1826 0.03357 0.02508 -0.0115 0.0374 1.0000
11.000 1.1813 0.03572 0.02725 -0.0094 0.0303 1.0000
11.250 1.1812 0.03786 0.02956 -0.0075 0.0255 1.0000
11.500 1.1773 0.04041 0.03217 -0.0060 0.0225 1.0000
11.750 1.1744 0.04300 0.03492 -0.0048 0.0206 1.0000
12.000 1.1720 0.04567 0.03778 -0.0040 0.0195 1.0000
12.250 1.1672 0.04876 0.04105 -0.0036 0.0182 1.0000
12.500 1.1615 0.05213 0.04459 -0.0036 0.0175 1.0000
12.750 1.1537 0.05598 0.04860 -0.0041 0.0168 1.0000
13.000 1.1458 0.06005 0.05284 -0.0050 0.0166 1.0000
13.250 1.1363 0.06460 0.05755 -0.0064 0.0163 1.0000
13.500 1.1254 0.06960 0.06271 -0.0082 0.0160 1.0000
13.750 1.1141 0.07490 0.06816 -0.0103 0.0158 1.0000
14.000 1.1038 0.08032 0.07372 -0.0126 0.0156 1.0000
14.250 1.0944 0.08585 0.07943 -0.0151 0.0155 1.0000
14.500 1.0850 0.09158 0.08532 -0.0177 0.0154 1.0000
14.750 1.0746 0.09773 0.09164 -0.0207 0.0153 1.0000
15.000 1.0643 0.10405 0.09813 -0.0238 0.0152 1.0000
15.250 1.0529 0.11084 0.10509 -0.0273 0.0151 1.0000
15.500 1.0426 0.11760 0.11198 -0.0308 0.0151 1.0000
15.750 1.0305 0.12502 0.11956 -0.0348 0.0151 1.0000
16.000 1.0190 0.13255 0.12722 -0.0389 0.0151 1.0000
16.250 1.0063 0.14074 0.13555 -0.0434 0.0151 1.0000
16.500 0.9937 0.14919 0.14412 -0.0481 0.0152 1.0000
16.750 0.9805 0.15828 0.15331 -0.0530 0.0153 1.0000
17.000 0.9662 0.16829 0.16338 -0.0584 0.0155 1.0000
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Polar data table (+)
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