EPPLER 715 AIRFOIL (e715-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 715 AIRFOIL (e715-il) Reynolds number: 100,000 Max Cl/Cd: 43.16 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e715-il-100000.txt Download as CSV file: xf-e715-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 715 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4262 0.13215 0.12781 -0.0071 1.0000 0.1146
-11.750 -0.4216 0.12853 0.12425 -0.0091 1.0000 0.1196
-11.500 -0.4516 0.12480 0.12067 -0.0169 1.0000 0.1235
-11.250 -0.5064 0.09329 0.08918 -0.0329 1.0000 0.0587
-11.000 -0.5087 0.08713 0.08305 -0.0361 1.0000 0.0574
-10.750 -0.5207 0.07982 0.07580 -0.0409 1.0000 0.0564
-10.500 -0.6197 0.06401 0.05954 -0.0588 1.0000 0.0479
-10.250 -0.6287 0.05904 0.05454 -0.0620 1.0000 0.0475
-10.000 -0.6288 0.05372 0.04892 -0.0674 0.9393 0.0472
-9.750 -0.6288 0.04941 0.04406 -0.0697 0.9019 0.0473
-9.500 -0.6307 0.04646 0.04058 -0.0688 0.8791 0.0476
-9.250 -0.6288 0.04285 0.03659 -0.0679 0.8628 0.0489
-9.000 -0.6156 0.04047 0.03407 -0.0673 0.8490 0.0506
-8.750 -0.6015 0.03815 0.03147 -0.0665 0.8373 0.0524
-8.500 -0.5867 0.03564 0.02852 -0.0656 0.8278 0.0542
-8.250 -0.5697 0.03357 0.02597 -0.0645 0.8188 0.0571
-8.000 -0.5501 0.03143 0.02375 -0.0640 0.8105 0.0621
-7.750 -0.5293 0.02992 0.02196 -0.0630 0.8028 0.0679
-7.500 -0.5073 0.02823 0.02027 -0.0626 0.7954 0.0760
-7.250 -0.4857 0.02673 0.01867 -0.0618 0.7887 0.0861
-7.000 -0.4643 0.02547 0.01740 -0.0610 0.7832 0.0998
-6.750 -0.4425 0.02432 0.01633 -0.0605 0.7770 0.1187
-6.500 -0.4227 0.02319 0.01530 -0.0595 0.7718 0.1442
-6.250 -0.4025 0.02211 0.01439 -0.0589 0.7665 0.1834
-6.000 -0.3831 0.02106 0.01370 -0.0582 0.7608 0.2369
-5.750 -0.3635 0.02036 0.01327 -0.0572 0.7563 0.3023
-5.500 -0.3407 0.02037 0.01352 -0.0563 0.7519 0.3635
-5.250 -0.3152 0.02098 0.01416 -0.0557 0.7470 0.4086
-5.000 -0.2896 0.02176 0.01485 -0.0546 0.7425 0.4406
-4.750 -0.2642 0.02255 0.01555 -0.0533 0.7389 0.4643
-4.500 -0.2376 0.02315 0.01608 -0.0530 0.7338 0.4873
-4.250 -0.2115 0.02366 0.01656 -0.0523 0.7297 0.5056
-4.000 -0.1861 0.02402 0.01682 -0.0513 0.7263 0.5231
-3.750 -0.1611 0.02428 0.01698 -0.0504 0.7232 0.5396
-3.500 -0.1353 0.02455 0.01724 -0.0503 0.7184 0.5552
-3.250 -0.1102 0.02471 0.01732 -0.0499 0.7143 0.5698
-3.000 -0.0851 0.02478 0.01731 -0.0493 0.7111 0.5837
-2.750 -0.0600 0.02484 0.01723 -0.0487 0.7085 0.5969
-2.500 -0.0348 0.02508 0.01743 -0.0491 0.7045 0.6099
-2.250 -0.0102 0.02527 0.01762 -0.0489 0.7002 0.6206
-2.000 0.0147 0.02535 0.01765 -0.0485 0.6968 0.6314
-1.750 0.0402 0.02542 0.01761 -0.0483 0.6941 0.6426
-1.500 0.0650 0.02564 0.01778 -0.0481 0.6913 0.6523
-1.250 0.0884 0.02606 0.01823 -0.0486 0.6866 0.6613
-1.000 0.1131 0.02634 0.01843 -0.0489 0.6828 0.6710
-0.750 0.1378 0.02651 0.01860 -0.0485 0.6800 0.6791
-0.500 0.1640 0.02666 0.01864 -0.0484 0.6776 0.6885
-0.250 0.1841 0.02742 0.01949 -0.0488 0.6728 0.6961
0.000 0.2059 0.02804 0.02008 -0.0492 0.6686 0.7047
0.250 0.2296 0.02841 0.02047 -0.0491 0.6655 0.7126
0.500 0.2565 0.02856 0.02057 -0.0489 0.6628 0.7210
0.750 0.2745 0.02953 0.02159 -0.0491 0.6582 0.7289
1.000 0.2906 0.03066 0.02277 -0.0495 0.6535 0.7370
1.250 0.3145 0.03110 0.02323 -0.0494 0.6498 0.7458
1.500 0.3433 0.03117 0.02329 -0.0491 0.6470 0.7550
1.750 0.3493 0.03303 0.02524 -0.0491 0.6413 0.7646
2.000 0.3644 0.03410 0.02638 -0.0489 0.6360 0.7748
2.250 0.3940 0.03429 0.02660 -0.0489 0.6327 0.7871
2.500 0.4294 0.03408 0.02643 -0.0488 0.6304 0.8016
2.750 0.4130 0.03727 0.02982 -0.0482 0.6211 0.8186
3.000 0.4471 0.03727 0.02996 -0.0486 0.6173 0.8459
3.250 0.5068 0.03652 0.02940 -0.0515 0.6149 0.8992
3.500 0.5125 0.03993 0.03291 -0.0557 0.6040 1.0000
3.750 0.5549 0.03967 0.03257 -0.0568 0.6007 1.0000
4.000 0.5388 0.04289 0.03573 -0.0557 0.5906 1.0000
4.250 0.5777 0.04284 0.03563 -0.0564 0.5861 1.0000
4.500 0.6206 0.04243 0.03519 -0.0566 0.5828 1.0000
4.750 0.6017 0.04555 0.03828 -0.0549 0.5712 1.0000
5.000 0.6020 0.04746 0.04016 -0.0533 0.5624 1.0000
5.250 0.6308 0.04780 0.04051 -0.0531 0.5559 1.0000
5.500 0.6683 0.04774 0.04048 -0.0532 0.5508 1.0000
5.750 0.6662 0.04964 0.04237 -0.0515 0.5403 1.0000
6.000 0.7083 0.04916 0.04194 -0.0516 0.5357 1.0000
6.250 0.7060 0.05109 0.04388 -0.0500 0.5245 1.0000
6.500 0.7542 0.05002 0.04289 -0.0500 0.5209 1.0000
6.750 0.7504 0.05203 0.04490 -0.0484 0.5088 1.0000
7.000 0.8097 0.04989 0.04289 -0.0485 0.5068 1.0000
7.250 0.7986 0.05242 0.04542 -0.0466 0.4932 1.0000
7.500 0.8572 0.04990 0.04304 -0.0464 0.4912 1.0000
7.750 0.8506 0.05213 0.04529 -0.0447 0.4779 1.0000
8.000 0.8494 0.05408 0.04729 -0.0434 0.4650 1.0000
8.250 0.8876 0.05267 0.04600 -0.0424 0.4595 1.0000
8.500 0.9812 0.04581 0.03941 -0.0415 0.4625 1.0000
8.750 1.0614 0.04002 0.03379 -0.0412 0.4621 1.0000
9.000 1.0645 0.04087 0.03475 -0.0391 0.4491 1.0000
9.250 1.1573 0.03394 0.02798 -0.0397 0.4472 1.0000
9.500 1.1770 0.03314 0.02732 -0.0379 0.4340 1.0000
9.750 1.2066 0.03146 0.02578 -0.0365 0.4201 1.0000
10.000 1.2415 0.02939 0.02376 -0.0353 0.4033 1.0000
10.250 1.2441 0.02983 0.02431 -0.0324 0.3828 1.0000
10.500 1.2604 0.02920 0.02360 -0.0300 0.3586 1.0000
10.750 1.2584 0.03015 0.02446 -0.0271 0.3336 1.0000
11.000 1.2551 0.03162 0.02578 -0.0248 0.3072 1.0000
11.250 1.2508 0.03352 0.02749 -0.0229 0.2811 1.0000
11.500 1.2460 0.03566 0.02937 -0.0212 0.2564 1.0000
11.750 1.2381 0.03833 0.03192 -0.0199 0.2338 1.0000
12.000 1.2335 0.04077 0.03411 -0.0187 0.2128 1.0000
12.250 1.2269 0.04360 0.03686 -0.0178 0.1934 1.0000
12.500 1.2226 0.04629 0.03942 -0.0170 0.1758 1.0000
12.750 1.2199 0.04890 0.04190 -0.0162 0.1599 1.0000
13.000 1.2185 0.05149 0.04437 -0.0156 0.1454 1.0000
13.250 1.2180 0.05408 0.04689 -0.0150 0.1322 1.0000
13.500 1.2186 0.05666 0.04943 -0.0144 0.1203 1.0000
13.750 1.2213 0.05910 0.05184 -0.0138 0.1098 1.0000
14.000 1.2270 0.06131 0.05396 -0.0131 0.1001 1.0000
14.250 1.2293 0.06393 0.05663 -0.0129 0.0922 1.0000
14.500 1.2333 0.06659 0.05935 -0.0125 0.0849 1.0000
14.750 1.2484 0.06820 0.06075 -0.0114 0.0769 1.0000
15.000 1.2426 0.07193 0.06481 -0.0118 0.0730 1.0000
15.250 1.2465 0.07457 0.06744 -0.0119 0.0679 1.0000
15.500 1.2514 0.07763 0.07062 -0.0116 0.0635 1.0000
15.750 1.2456 0.08165 0.07488 -0.0123 0.0605 1.0000
16.000 1.2478 0.08465 0.07792 -0.0126 0.0571 1.0000
16.250 1.2517 0.08816 0.08150 -0.0126 0.0539 1.0000
16.500 1.2369 0.09355 0.08720 -0.0144 0.0527 1.0000
16.750 1.2221 0.09920 0.09313 -0.0164 0.0514 1.0000
17.000 1.2077 0.10497 0.09914 -0.0188 0.0502 1.0000
17.250 1.1944 0.11079 0.10515 -0.0213 0.0490 1.0000
17.500 1.1758 0.11781 0.11241 -0.0248 0.0486 1.0000
17.750 1.1352 0.12952 0.12448 -0.0316 0.0504 1.0000
18.000 1.0962 0.14204 0.13726 -0.0392 0.0524 1.0000
18.250 1.0618 0.15478 0.15012 -0.0470 0.0539 1.0000
18.500 0.9348 0.20766 0.20279 -0.0763 0.0785 1.0000
18.750 0.9442 0.21176 0.20692 -0.0772 0.0778 1.0000
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Polar data table (+)
Polar graphs
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