E197 (13.49%) (e197-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E197 (13.49%) (e197-il) Reynolds number: 200,000 Max Cl/Cd: 77.59 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e197-il-200000.txt Download as CSV file: xf-e197-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E197 (13.49%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3896 0.10330 0.09979 -0.0410 1.0000 0.0660
-10.500 -0.4297 0.09402 0.09065 -0.0530 1.0000 0.0693
-10.250 -0.4338 0.08817 0.08487 -0.0536 1.0000 0.0703
-10.000 -0.4179 0.08703 0.08372 -0.0503 1.0000 0.0714
-9.750 -0.4017 0.08647 0.08315 -0.0478 1.0000 0.0742
-9.500 -0.4050 0.08262 0.07935 -0.0493 1.0000 0.0760
-9.250 -0.4173 0.07743 0.07424 -0.0523 1.0000 0.0780
-9.000 -0.4406 0.07065 0.06757 -0.0571 1.0000 0.0784
-8.750 -0.4813 0.06490 0.06192 -0.0599 1.0000 0.0772
-8.500 -0.5118 0.06129 0.05832 -0.0597 0.9951 0.0765
-8.250 -0.5597 0.03455 0.02890 -0.0706 0.9659 0.0366
-8.000 -0.5294 0.03069 0.02458 -0.0731 0.9579 0.0367
-7.750 -0.5000 0.02776 0.02126 -0.0744 0.9465 0.0367
-7.500 -0.4699 0.02471 0.01790 -0.0757 0.9359 0.0372
-7.250 -0.4375 0.02256 0.01558 -0.0770 0.9259 0.0382
-7.000 -0.4083 0.02125 0.01417 -0.0775 0.9131 0.0400
-6.750 -0.3814 0.02030 0.01308 -0.0773 0.8992 0.0424
-6.500 -0.3562 0.01926 0.01189 -0.0767 0.8855 0.0442
-6.250 -0.3319 0.01842 0.01089 -0.0758 0.8724 0.0458
-6.000 -0.3116 0.01714 0.00959 -0.0746 0.8602 0.0488
-5.750 -0.2891 0.01646 0.00883 -0.0736 0.8491 0.0533
-5.500 -0.2676 0.01570 0.00801 -0.0725 0.8383 0.0612
-5.250 -0.2467 0.01484 0.00718 -0.0713 0.8278 0.0836
-5.000 -0.2264 0.01388 0.00651 -0.0702 0.8191 0.1437
-4.750 -0.2038 0.01332 0.00613 -0.0696 0.8099 0.2008
-4.500 -0.1810 0.01283 0.00585 -0.0689 0.8018 0.2636
-4.250 -0.1584 0.01239 0.00567 -0.0682 0.7941 0.3398
-4.000 -0.1349 0.01218 0.00565 -0.0674 0.7865 0.4119
-3.750 -0.1100 0.01211 0.00560 -0.0667 0.7794 0.4611
-3.500 -0.0844 0.01208 0.00556 -0.0662 0.7729 0.4938
-3.250 -0.0586 0.01205 0.00551 -0.0657 0.7659 0.5216
-3.000 -0.0324 0.01205 0.00545 -0.0652 0.7604 0.5483
-2.750 -0.0067 0.01205 0.00544 -0.0647 0.7534 0.5734
-2.500 0.0197 0.01201 0.00539 -0.0642 0.7480 0.5947
-2.250 0.0458 0.01201 0.00537 -0.0638 0.7421 0.6155
-2.000 0.0721 0.01199 0.00534 -0.0634 0.7361 0.6362
-1.750 0.0989 0.01196 0.00530 -0.0630 0.7315 0.6560
-1.500 0.1245 0.01195 0.00533 -0.0625 0.7253 0.6770
-1.250 0.1508 0.01192 0.00532 -0.0620 0.7199 0.6986
-1.000 0.1775 0.01191 0.00530 -0.0616 0.7156 0.7206
-0.750 0.2026 0.01190 0.00538 -0.0610 0.7096 0.7446
-0.500 0.2282 0.01186 0.00540 -0.0603 0.7045 0.7711
-0.250 0.2542 0.01185 0.00542 -0.0596 0.7004 0.8002
0.000 0.2784 0.01185 0.00556 -0.0586 0.6945 0.8331
0.250 0.3054 0.01186 0.00563 -0.0580 0.6896 0.8681
0.500 0.3389 0.01194 0.00568 -0.0586 0.6857 0.9018
0.750 0.3777 0.01207 0.00586 -0.0608 0.6797 0.9314
1.000 0.4205 0.01217 0.00592 -0.0637 0.6747 0.9561
1.250 0.4694 0.01228 0.00592 -0.0680 0.6707 0.9717
1.500 0.5191 0.01238 0.00604 -0.0729 0.6644 0.9855
1.750 0.5702 0.01239 0.00601 -0.0780 0.6592 0.9976
2.000 0.5972 0.01249 0.00604 -0.0783 0.6551 1.0000
2.250 0.6155 0.01265 0.00624 -0.0769 0.6490 1.0000
2.500 0.6374 0.01278 0.00632 -0.0760 0.6441 1.0000
2.750 0.6609 0.01294 0.00643 -0.0752 0.6399 1.0000
3.000 0.6816 0.01314 0.00670 -0.0741 0.6336 1.0000
3.250 0.7056 0.01328 0.00680 -0.0734 0.6287 1.0000
3.500 0.7295 0.01346 0.00697 -0.0728 0.6237 1.0000
3.750 0.7518 0.01363 0.00721 -0.0718 0.6170 1.0000
4.000 0.7775 0.01372 0.00725 -0.0713 0.6120 1.0000
4.250 0.7995 0.01391 0.00750 -0.0703 0.6047 1.0000
4.500 0.8246 0.01397 0.00755 -0.0697 0.5984 1.0000
4.750 0.8482 0.01411 0.00774 -0.0689 0.5913 1.0000
5.000 0.8729 0.01416 0.00781 -0.0682 0.5841 1.0000
5.250 0.8970 0.01425 0.00795 -0.0674 0.5766 1.0000
5.500 0.9219 0.01427 0.00799 -0.0667 0.5686 1.0000
5.750 0.9453 0.01435 0.00814 -0.0659 0.5599 1.0000
6.000 0.9716 0.01431 0.00808 -0.0654 0.5519 1.0000
6.250 0.9936 0.01436 0.00825 -0.0642 0.5413 1.0000
6.500 1.0172 0.01437 0.00833 -0.0633 0.5310 1.0000
6.750 1.0415 0.01435 0.00833 -0.0625 0.5202 1.0000
7.000 1.0643 0.01435 0.00838 -0.0614 0.5077 1.0000
7.250 1.0859 0.01437 0.00847 -0.0601 0.4932 1.0000
7.500 1.1067 0.01445 0.00863 -0.0588 0.4767 1.0000
7.750 1.1263 0.01457 0.00883 -0.0573 0.4569 1.0000
8.000 1.1452 0.01476 0.00902 -0.0556 0.4350 1.0000
8.250 1.1618 0.01506 0.00932 -0.0536 0.4074 1.0000
8.500 1.1748 0.01553 0.00972 -0.0512 0.3701 1.0000
8.750 1.1804 0.01634 0.01028 -0.0476 0.3202 1.0000
9.000 1.1795 0.01748 0.01111 -0.0434 0.2684 1.0000
9.250 1.1739 0.01871 0.01208 -0.0385 0.2268 1.0000
9.500 1.1679 0.02007 0.01321 -0.0339 0.1912 1.0000
9.750 1.1641 0.02153 0.01450 -0.0302 0.1616 1.0000
10.000 1.1629 0.02303 0.01588 -0.0272 0.1370 1.0000
10.250 1.1618 0.02469 0.01745 -0.0245 0.1167 1.0000
10.500 1.1609 0.02649 0.01917 -0.0223 0.0976 1.0000
10.750 1.1590 0.02851 0.02109 -0.0203 0.0820 1.0000
11.000 1.1573 0.03066 0.02321 -0.0186 0.0680 1.0000
11.250 1.1548 0.03302 0.02553 -0.0170 0.0541 1.0000
11.500 1.1486 0.03580 0.02828 -0.0154 0.0442 1.0000
11.750 1.1425 0.03870 0.03115 -0.0141 0.0379 1.0000
12.000 1.1415 0.04123 0.03377 -0.0130 0.0331 1.0000
12.250 1.1410 0.04376 0.03633 -0.0122 0.0309 1.0000
12.500 1.1366 0.04666 0.03922 -0.0110 0.0292 1.0000
12.750 1.1421 0.04875 0.04145 -0.0103 0.0273 1.0000
13.000 1.1466 0.05095 0.04371 -0.0099 0.0252 1.0000
13.250 1.1508 0.05320 0.04600 -0.0093 0.0242 1.0000
13.500 1.1543 0.05558 0.04835 -0.0082 0.0227 1.0000
13.750 1.1634 0.05750 0.05041 -0.0074 0.0222 1.0000
14.000 1.1718 0.05959 0.05265 -0.0068 0.0215 1.0000
14.250 1.1800 0.06179 0.05499 -0.0061 0.0208 1.0000
14.500 1.1884 0.06406 0.05740 -0.0056 0.0204 1.0000
14.750 1.1949 0.06661 0.06011 -0.0051 0.0201 1.0000
15.000 1.1989 0.06950 0.06317 -0.0049 0.0196 1.0000
15.250 1.2009 0.07271 0.06656 -0.0049 0.0194 1.0000
15.500 1.1996 0.07642 0.07050 -0.0052 0.0194 1.0000
15.750 1.1953 0.08051 0.07479 -0.0058 0.0192 1.0000
16.000 1.1873 0.08522 0.07974 -0.0068 0.0192 1.0000
16.250 1.1764 0.09045 0.08520 -0.0084 0.0192 1.0000
16.500 1.1598 0.09676 0.09180 -0.0107 0.0194 1.0000
16.750 1.1414 0.10362 0.09893 -0.0137 0.0196 1.0000
17.000 1.1209 0.11120 0.10675 -0.0175 0.0197 1.0000
17.250 1.0971 0.11986 0.11566 -0.0222 0.0200 1.0000
17.500 1.0722 0.12933 0.12536 -0.0279 0.0204 1.0000
17.750 1.0455 0.13991 0.13615 -0.0345 0.0208 1.0000
18.000 1.0162 0.15216 0.14858 -0.0424 0.0212 1.0000
18.250 0.9835 0.16669 0.16322 -0.0516 0.0219 1.0000
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Polar data table (+)
Polar graphs
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