EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Reynolds number: 1,000,000 Max Cl/Cd: 146 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ste87391-il-1000000.txt Download as CSV file: xf-ste87391-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER STE 87(-3)-914 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.4228 0.08170 0.07933 -0.1294 0.9491 0.0096
-15.000 -0.4591 0.07106 0.06852 -0.1364 0.9479 0.0095
-14.750 -0.4846 0.06246 0.05977 -0.1428 0.9464 0.0094
-14.500 -0.5039 0.05511 0.05225 -0.1487 0.9448 0.0094
-14.250 -0.5180 0.04874 0.04571 -0.1541 0.9431 0.0095
-14.000 -0.5271 0.04345 0.04025 -0.1587 0.9414 0.0095
-13.750 -0.5329 0.03911 0.03573 -0.1624 0.9399 0.0096
-13.500 -0.5355 0.03566 0.03212 -0.1650 0.9384 0.0097
-13.250 -0.5348 0.03289 0.02917 -0.1670 0.9369 0.0099
-13.000 -0.5302 0.03070 0.02684 -0.1683 0.9350 0.0101
-12.750 -0.5227 0.02899 0.02499 -0.1692 0.9332 0.0102
-12.500 -0.5126 0.02771 0.02357 -0.1697 0.9316 0.0103
-12.250 -0.5125 0.02502 0.02071 -0.1694 0.9298 0.0107
-12.000 -0.4999 0.02376 0.01938 -0.1694 0.9285 0.0109
-11.750 -0.4866 0.02296 0.01852 -0.1691 0.9274 0.0111
-11.500 -0.4699 0.02226 0.01775 -0.1692 0.9263 0.0114
-11.250 -0.4513 0.02170 0.01713 -0.1693 0.9252 0.0117
-11.000 -0.4335 0.02114 0.01651 -0.1689 0.9238 0.0121
-10.750 -0.4154 0.02059 0.01587 -0.1684 0.9221 0.0125
-10.500 -0.3968 0.02007 0.01526 -0.1678 0.9207 0.0128
-10.250 -0.3770 0.01962 0.01471 -0.1672 0.9194 0.0130
-10.000 -0.3576 0.01892 0.01392 -0.1666 0.9183 0.0132
-9.750 -0.3407 0.01777 0.01274 -0.1659 0.9172 0.0136
-9.500 -0.3191 0.01717 0.01212 -0.1656 0.9164 0.0139
-9.250 -0.2955 0.01664 0.01155 -0.1656 0.9157 0.0143
-9.000 -0.2707 0.01614 0.01101 -0.1657 0.9150 0.0148
-8.750 -0.2460 0.01570 0.01052 -0.1657 0.9143 0.0152
-8.500 -0.2212 0.01542 0.01019 -0.1656 0.9136 0.0157
-8.250 -0.2336 0.01592 0.01068 -0.1581 0.9075 0.0158
-8.000 -0.2144 0.01537 0.01009 -0.1571 0.9060 0.0164
-7.750 -0.1892 0.01487 0.00957 -0.1572 0.9050 0.0170
-7.500 -0.1619 0.01446 0.00913 -0.1576 0.9043 0.0175
-7.250 -0.1344 0.01411 0.00874 -0.1579 0.9037 0.0180
-7.000 -0.1054 0.01378 0.00837 -0.1585 0.9032 0.0186
-6.750 -0.0754 0.01345 0.00800 -0.1593 0.9027 0.0191
-6.500 -0.0455 0.01297 0.00750 -0.1602 0.9023 0.0201
-6.250 -0.0670 0.01364 0.00816 -0.1505 0.8939 0.0203
-6.000 -0.0377 0.01338 0.00788 -0.1511 0.8929 0.0214
-5.750 -0.0055 0.01307 0.00755 -0.1522 0.8924 0.0229
-5.500 0.0273 0.01276 0.00724 -0.1535 0.8920 0.0250
-5.250 0.0612 0.01243 0.00692 -0.1550 0.8917 0.0296
-5.000 0.0969 0.01140 0.00640 -0.1577 0.8914 0.1378
-4.750 0.1305 0.01107 0.00621 -0.1592 0.8910 0.1740
-4.500 0.1643 0.01083 0.00602 -0.1606 0.8905 0.1908
-4.250 0.1982 0.01063 0.00583 -0.1620 0.8901 0.2030
-4.000 0.2322 0.01039 0.00564 -0.1634 0.8897 0.2171
-3.750 0.2670 0.01014 0.00543 -0.1651 0.8893 0.2309
-3.500 0.3029 0.00987 0.00518 -0.1668 0.8888 0.2433
-3.250 0.3397 0.00956 0.00490 -0.1688 0.8883 0.2574
-3.000 0.3776 0.00919 0.00459 -0.1710 0.8876 0.2782
-2.750 0.4091 0.00895 0.00442 -0.1720 0.8856 0.3021
-2.250 0.4621 0.00845 0.00411 -0.1717 0.8790 0.3594
-2.000 0.4989 0.00797 0.00374 -0.1737 0.8770 0.4020
-1.750 0.5390 0.00743 0.00333 -0.1764 0.8750 0.4561
-1.500 0.5776 0.00698 0.00305 -0.1789 0.8730 0.5238
-1.250 0.6026 0.00676 0.00304 -0.1786 0.8698 0.5930
-1.000 0.6287 0.00656 0.00307 -0.1784 0.8662 0.6667
-0.750 0.6585 0.00645 0.00303 -0.1788 0.8633 0.7038
-0.500 0.6904 0.00634 0.00294 -0.1796 0.8607 0.7208
-0.250 0.7233 0.00625 0.00284 -0.1806 0.8582 0.7321
0.000 0.7442 0.00631 0.00292 -0.1792 0.8536 0.7410
0.250 0.7696 0.00628 0.00288 -0.1787 0.8485 0.7476
0.500 0.7991 0.00618 0.00280 -0.1790 0.8443 0.7531
0.750 0.8200 0.00622 0.00287 -0.1775 0.8378 0.7582
1.000 0.8442 0.00620 0.00283 -0.1767 0.8300 0.7632
1.250 0.8625 0.00623 0.00285 -0.1747 0.8186 0.7672
1.500 0.8849 0.00619 0.00280 -0.1735 0.8032 0.7715
1.750 0.9081 0.00622 0.00273 -0.1724 0.7781 0.7748
2.000 0.9255 0.00649 0.00281 -0.1702 0.7418 0.7782
2.250 0.9370 0.00697 0.00308 -0.1668 0.7015 0.7819
2.500 0.9462 0.00752 0.00344 -0.1631 0.6628 0.7851
2.750 0.9564 0.00806 0.00380 -0.1597 0.6269 0.7882
3.000 0.9669 0.00858 0.00420 -0.1563 0.5929 0.7927
3.500 0.9909 0.00973 0.00507 -0.1503 0.5266 0.8059
3.750 1.0035 0.01023 0.00546 -0.1474 0.4953 0.8124
4.000 1.0191 0.01072 0.00583 -0.1452 0.4651 0.8168
4.250 1.0357 0.01120 0.00618 -0.1434 0.4372 0.8192
4.500 1.0541 0.01163 0.00649 -0.1419 0.4124 0.8209
4.750 1.0731 0.01204 0.00681 -0.1405 0.3891 0.8221
5.000 1.0925 0.01246 0.00712 -0.1393 0.3671 0.8232
5.250 1.1120 0.01286 0.00744 -0.1380 0.3465 0.8243
5.500 1.1318 0.01323 0.00773 -0.1369 0.3281 0.8259
5.750 1.1516 0.01361 0.00804 -0.1357 0.3122 0.8271
6.000 1.1710 0.01401 0.00838 -0.1345 0.2974 0.8282
6.250 1.1914 0.01437 0.00871 -0.1335 0.2846 0.8293
6.500 1.2116 0.01474 0.00904 -0.1324 0.2718 0.8304
6.750 1.2310 0.01515 0.00940 -0.1313 0.2590 0.8316
7.250 1.2701 0.01596 0.01013 -0.1290 0.2358 0.8345
7.500 1.2892 0.01639 0.01053 -0.1278 0.2249 0.8357
7.750 1.3075 0.01688 0.01095 -0.1265 0.2114 0.8369
8.000 1.3267 0.01732 0.01134 -0.1254 0.2002 0.8381
8.250 1.3463 0.01773 0.01174 -0.1244 0.1908 0.8393
8.500 1.3646 0.01822 0.01219 -0.1231 0.1808 0.8404
8.750 1.3823 0.01874 0.01267 -0.1218 0.1704 0.8414
9.000 1.3995 0.01929 0.01316 -0.1204 0.1578 0.8426
9.250 1.4158 0.01987 0.01370 -0.1190 0.1439 0.8442
9.500 1.4291 0.02064 0.01435 -0.1170 0.1230 0.8457
9.750 1.4348 0.02188 0.01537 -0.1140 0.0892 0.8472
10.000 1.4376 0.02334 0.01661 -0.1105 0.0571 0.8488
10.250 1.4402 0.02486 0.01794 -0.1071 0.0287 0.8503
10.500 1.4435 0.02635 0.01932 -0.1039 0.0112 0.8522
10.750 1.4552 0.02732 0.02030 -0.1020 0.0086 0.8541
11.000 1.4678 0.02823 0.02125 -0.1002 0.0076 0.8559
11.250 1.4792 0.02922 0.02231 -0.0982 0.0070 0.8575
11.500 1.4913 0.03019 0.02333 -0.0965 0.0066 0.8589
11.750 1.5026 0.03120 0.02441 -0.0947 0.0062 0.8612
12.000 1.5115 0.03240 0.02568 -0.0927 0.0058 0.8634
12.250 1.5171 0.03388 0.02726 -0.0903 0.0055 0.8656
12.500 1.5245 0.03525 0.02871 -0.0882 0.0053 0.8680
12.750 1.5325 0.03660 0.03014 -0.0863 0.0052 0.8705
13.000 1.5397 0.03806 0.03168 -0.0844 0.0050 0.8731
13.250 1.5462 0.03961 0.03331 -0.0826 0.0049 0.8757
13.500 1.5516 0.04126 0.03506 -0.0808 0.0048 0.8791
13.750 1.5559 0.04304 0.03694 -0.0789 0.0046 0.8828
14.000 1.5594 0.04498 0.03896 -0.0772 0.0045 0.8869
14.250 1.5622 0.04704 0.04112 -0.0756 0.0044 0.8914
14.500 1.5634 0.04929 0.04348 -0.0739 0.0043 0.8975
14.750 1.5632 0.05175 0.04606 -0.0724 0.0043 0.9053
15.000 1.5605 0.05442 0.04887 -0.0708 0.0042 0.9190
15.250 1.5547 0.05711 0.05173 -0.0689 0.0042 0.9981
15.500 1.5507 0.06040 0.05512 -0.0680 0.0041 0.9981
15.750 1.5445 0.06406 0.05889 -0.0672 0.0041 0.9981
16.000 1.5366 0.06803 0.06297 -0.0667 0.0041 0.9981
16.250 1.5280 0.07222 0.06727 -0.0665 0.0040 0.9981
16.500 1.5180 0.07674 0.07190 -0.0666 0.0040 0.9981
16.750 1.5070 0.08152 0.07680 -0.0669 0.0040 0.9981
17.000 1.4934 0.08681 0.08221 -0.0676 0.0040 0.9981
17.250 1.4803 0.09212 0.08765 -0.0685 0.0039 0.9981
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Polar data table (+)
Polar graphs
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