EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Reynolds number: 500,000 Max Cl/Cd: 92.54 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ste87391-il-500000-n5.txt Download as CSV file: xf-ste87391-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.4035 0.08102 0.07787 -0.1317 0.9440 0.0098
-14.750 -0.4350 0.07134 0.06802 -0.1379 0.9424 0.0098
-14.500 -0.4560 0.06382 0.06035 -0.1432 0.9407 0.0098
-14.250 -0.4713 0.05736 0.05373 -0.1480 0.9390 0.0098
-14.000 -0.4818 0.05172 0.04794 -0.1524 0.9372 0.0099
-13.750 -0.4889 0.04676 0.04282 -0.1565 0.9357 0.0099
-13.500 -0.4931 0.04251 0.03841 -0.1601 0.9343 0.0100
-13.250 -0.4945 0.03898 0.03473 -0.1630 0.9327 0.0102
-13.000 -0.4938 0.03611 0.03172 -0.1652 0.9308 0.0103
-12.750 -0.4915 0.03374 0.02920 -0.1665 0.9287 0.0105
-12.500 -0.4873 0.03175 0.02707 -0.1671 0.9268 0.0107
-12.250 -0.4811 0.03006 0.02524 -0.1673 0.9250 0.0109
-12.000 -0.4728 0.02860 0.02365 -0.1673 0.9234 0.0112
-11.750 -0.4627 0.02730 0.02220 -0.1671 0.9219 0.0114
-11.500 -0.4509 0.02615 0.02092 -0.1669 0.9206 0.0117
-11.250 -0.4416 0.02535 0.01999 -0.1658 0.9190 0.0119
-11.000 -0.4320 0.02473 0.01926 -0.1645 0.9166 0.0120
-10.750 -0.4228 0.02383 0.01826 -0.1630 0.9143 0.0122
-10.500 -0.4135 0.02271 0.01706 -0.1614 0.9123 0.0125
-10.250 -0.3990 0.02187 0.01615 -0.1603 0.9108 0.0127
-10.000 -0.3806 0.02111 0.01533 -0.1598 0.9096 0.0130
-9.750 -0.3606 0.02042 0.01458 -0.1594 0.9087 0.0133
-9.500 -0.3393 0.01978 0.01387 -0.1591 0.9079 0.0136
-9.250 -0.3167 0.01920 0.01321 -0.1590 0.9072 0.0141
-9.000 -0.2930 0.01864 0.01259 -0.1591 0.9066 0.0145
-8.750 -0.3035 0.01889 0.01283 -0.1521 0.9010 0.0148
-8.500 -0.2909 0.01860 0.01248 -0.1497 0.8986 0.0151
-8.250 -0.2694 0.01813 0.01194 -0.1491 0.8972 0.0155
-8.000 -0.2449 0.01763 0.01139 -0.1490 0.8962 0.0158
-7.750 -0.2197 0.01720 0.01088 -0.1491 0.8954 0.0160
-7.500 -0.1934 0.01668 0.01031 -0.1494 0.8948 0.0164
-7.250 -0.1659 0.01605 0.00962 -0.1500 0.8942 0.0170
-7.000 -0.1369 0.01557 0.00910 -0.1508 0.8937 0.0176
-6.750 -0.1549 0.01601 0.00952 -0.1419 0.8860 0.0177
-6.500 -0.1306 0.01573 0.00920 -0.1416 0.8843 0.0184
-6.250 -0.1028 0.01544 0.00887 -0.1420 0.8833 0.0194
-6.000 -0.0736 0.01516 0.00854 -0.1426 0.8825 0.0203
-5.750 -0.0435 0.01488 0.00822 -0.1433 0.8818 0.0210
-5.500 -0.0125 0.01457 0.00787 -0.1442 0.8813 0.0226
-5.250 0.0189 0.01428 0.00757 -0.1452 0.8808 0.0250
-5.000 0.0510 0.01396 0.00727 -0.1463 0.8804 0.0329
-4.750 0.0845 0.01323 0.00684 -0.1483 0.8800 0.1003
-4.500 0.1180 0.01278 0.00665 -0.1500 0.8797 0.1614
-4.250 0.1519 0.01253 0.00648 -0.1515 0.8793 0.1849
-4.000 0.1485 0.01303 0.00699 -0.1455 0.8709 0.1923
-3.750 0.1790 0.01285 0.00685 -0.1463 0.8696 0.2078
-3.500 0.2108 0.01265 0.00668 -0.1473 0.8687 0.2184
-3.250 0.2433 0.01245 0.00648 -0.1483 0.8679 0.2272
-3.000 0.2769 0.01218 0.00626 -0.1497 0.8673 0.2441
-2.750 0.3116 0.01188 0.00603 -0.1513 0.8666 0.2648
-2.500 0.3476 0.01156 0.00575 -0.1531 0.8660 0.2808
-2.250 0.3851 0.01121 0.00544 -0.1551 0.8654 0.2981
-2.000 0.3921 0.01148 0.00576 -0.1512 0.8576 0.3112
-1.750 0.4245 0.01116 0.00551 -0.1522 0.8553 0.3352
-1.500 0.4605 0.01071 0.00517 -0.1540 0.8536 0.3687
-1.250 0.4985 0.01021 0.00478 -0.1562 0.8519 0.4093
-1.000 0.5173 0.01022 0.00491 -0.1546 0.8448 0.4459
-0.750 0.5479 0.00985 0.00470 -0.1553 0.8394 0.4974
-0.500 0.5735 0.00968 0.00471 -0.1551 0.8324 0.5549
-0.250 0.5998 0.00951 0.00480 -0.1551 0.8250 0.6271
0.000 0.6193 0.00967 0.00516 -0.1534 0.8156 0.6873
0.250 0.6486 0.00950 0.00501 -0.1536 0.8085 0.7127
0.500 0.6746 0.00947 0.00498 -0.1532 0.7971 0.7259
0.750 0.7083 0.00918 0.00464 -0.1542 0.7847 0.7361
1.000 0.7474 0.00876 0.00413 -0.1562 0.7677 0.7434
1.250 0.7825 0.00859 0.00379 -0.1575 0.7413 0.7513
1.500 0.8079 0.00873 0.00376 -0.1569 0.7101 0.7565
1.750 0.8257 0.00910 0.00393 -0.1549 0.6744 0.7616
2.000 0.8401 0.00958 0.00420 -0.1524 0.6387 0.7669
2.250 0.8524 0.01009 0.00456 -0.1494 0.6047 0.7712
2.500 0.8656 0.01061 0.00494 -0.1466 0.5737 0.7784
2.750 0.8788 0.01114 0.00537 -0.1438 0.5444 0.7885
3.000 0.8925 0.01169 0.00579 -0.1412 0.5147 0.7993
3.250 0.9063 0.01221 0.00621 -0.1386 0.4861 0.8058
3.500 0.9227 0.01271 0.00657 -0.1367 0.4579 0.8091
3.750 0.9407 0.01318 0.00692 -0.1352 0.4325 0.8112
4.000 0.9600 0.01360 0.00724 -0.1339 0.4101 0.8127
4.250 0.9786 0.01402 0.00757 -0.1325 0.3895 0.8140
4.500 0.9979 0.01443 0.00790 -0.1312 0.3707 0.8154
4.750 1.0175 0.01483 0.00824 -0.1300 0.3524 0.8166
5.000 1.0373 0.01524 0.00858 -0.1289 0.3348 0.8179
5.250 1.0572 0.01565 0.00893 -0.1278 0.3187 0.8192
5.500 1.0773 0.01604 0.00928 -0.1267 0.3052 0.8207
5.750 1.0976 0.01644 0.00964 -0.1257 0.2937 0.8222
6.250 1.1389 0.01721 0.01037 -0.1239 0.2733 0.8247
6.500 1.1593 0.01762 0.01076 -0.1229 0.2646 0.8260
6.750 1.1798 0.01802 0.01115 -0.1220 0.2555 0.8272
7.000 1.1997 0.01843 0.01157 -0.1210 0.2478 0.8283
7.250 1.2187 0.01887 0.01201 -0.1198 0.2390 0.8295
7.500 1.2382 0.01930 0.01245 -0.1187 0.2305 0.8309
7.750 1.2564 0.01980 0.01293 -0.1175 0.2216 0.8323
8.000 1.2752 0.02029 0.01341 -0.1163 0.2105 0.8337
8.250 1.2932 0.02082 0.01391 -0.1151 0.1983 0.8350
8.500 1.3100 0.02141 0.01446 -0.1137 0.1846 0.8364
8.750 1.3264 0.02204 0.01504 -0.1123 0.1699 0.8379
9.000 1.3426 0.02270 0.01564 -0.1109 0.1553 0.8394
9.250 1.3588 0.02336 0.01626 -0.1095 0.1418 0.8409
9.750 1.3793 0.02544 0.01805 -0.1051 0.0901 0.8437
10.000 1.3854 0.02678 0.01923 -0.1024 0.0636 0.8452
10.250 1.3921 0.02810 0.02045 -0.0998 0.0432 0.8470
10.500 1.3991 0.02942 0.02170 -0.0974 0.0277 0.8489
10.750 1.4061 0.03077 0.02299 -0.0950 0.0158 0.8510
11.000 1.4140 0.03207 0.02430 -0.0928 0.0098 0.8530
11.250 1.4243 0.03323 0.02551 -0.0909 0.0079 0.8550
11.500 1.4347 0.03440 0.02674 -0.0892 0.0070 0.8570
11.750 1.4440 0.03562 0.02805 -0.0873 0.0065 0.8589
12.000 1.4534 0.03688 0.02939 -0.0855 0.0061 0.8610
12.250 1.4626 0.03817 0.03077 -0.0838 0.0058 0.8634
12.500 1.4712 0.03955 0.03225 -0.0822 0.0056 0.8661
12.750 1.4787 0.04105 0.03385 -0.0805 0.0054 0.8689
13.250 1.4908 0.04439 0.03740 -0.0771 0.0050 0.8749
13.500 1.4951 0.04627 0.03940 -0.0755 0.0049 0.8785
13.750 1.4980 0.04835 0.04159 -0.0739 0.0047 0.8826
14.250 1.4989 0.05319 0.04668 -0.0708 0.0045 0.8929
14.500 1.4957 0.05610 0.04972 -0.0694 0.0044 0.9002
14.750 1.4908 0.05920 0.05297 -0.0680 0.0043 0.9109
15.000 1.4863 0.06193 0.05587 -0.0664 0.0043 0.9482
15.250 1.4832 0.06503 0.05909 -0.0657 0.0042 0.9981
15.500 1.4790 0.06861 0.06280 -0.0653 0.0041 0.9981
15.750 1.4753 0.07223 0.06653 -0.0652 0.0041 0.9981
16.000 1.4687 0.07631 0.07074 -0.0652 0.0041 0.9981
16.250 1.4607 0.08072 0.07530 -0.0656 0.0040 0.9981
16.500 1.4532 0.08518 0.07988 -0.0662 0.0039 0.9981
16.750 1.4432 0.09011 0.08494 -0.0671 0.0039 0.9981
17.000 1.4337 0.09507 0.09002 -0.0682 0.0038 0.9981
17.250 1.4216 0.10049 0.09558 -0.0696 0.0038 0.9981
17.500 1.4106 0.10587 0.10108 -0.0712 0.0038 0.9981
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Polar data table (+)
Polar graphs
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