EPPLER 715 AIRFOIL (e715-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 715 AIRFOIL (e715-il) Reynolds number: 200,000 Max Cl/Cd: 74.61 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e715-il-200000.txt Download as CSV file: xf-e715-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4882 0.10286 0.09991 -0.0208 1.0000 0.0338
-11.500 -0.6960 0.05649 0.05258 -0.0530 1.0000 0.0209
-11.250 -0.7143 0.05151 0.04742 -0.0571 1.0000 0.0208
-11.000 -0.7242 0.04742 0.04278 -0.0614 0.8584 0.0206
-10.750 -0.7373 0.04506 0.04003 -0.0595 0.8207 0.0205
-10.500 -0.7422 0.04228 0.03689 -0.0582 0.8003 0.0206
-10.250 -0.7373 0.03986 0.03429 -0.0574 0.7847 0.0213
-10.000 -0.7248 0.03841 0.03273 -0.0568 0.7712 0.0221
-9.750 -0.7136 0.03680 0.03088 -0.0560 0.7599 0.0231
-9.500 -0.7032 0.03465 0.02836 -0.0551 0.7510 0.0237
-9.250 -0.6899 0.03242 0.02574 -0.0541 0.7425 0.0244
-9.000 -0.6731 0.03040 0.02335 -0.0532 0.7353 0.0249
-8.750 -0.6540 0.02863 0.02125 -0.0524 0.7280 0.0256
-8.500 -0.6347 0.02647 0.01905 -0.0517 0.7220 0.0269
-8.250 -0.6133 0.02525 0.01777 -0.0512 0.7151 0.0286
-8.000 -0.5914 0.02416 0.01645 -0.0504 0.7096 0.0311
-7.750 -0.5714 0.02283 0.01515 -0.0498 0.7044 0.0347
-7.500 -0.5480 0.02205 0.01422 -0.0493 0.6991 0.0392
-7.250 -0.5279 0.02085 0.01303 -0.0485 0.6947 0.0452
-7.000 -0.5064 0.01985 0.01201 -0.0480 0.6906 0.0534
-6.750 -0.4838 0.01893 0.01109 -0.0475 0.6857 0.0646
-6.500 -0.4608 0.01810 0.01024 -0.0470 0.6813 0.0802
-6.250 -0.4385 0.01721 0.00940 -0.0465 0.6777 0.1029
-6.000 -0.4148 0.01640 0.00873 -0.0462 0.6738 0.1387
-5.750 -0.3912 0.01560 0.00817 -0.0461 0.6698 0.1872
-5.500 -0.3670 0.01497 0.00774 -0.0459 0.6663 0.2440
-5.250 -0.3426 0.01449 0.00745 -0.0455 0.6633 0.3024
-5.000 -0.3171 0.01429 0.00741 -0.0452 0.6601 0.3556
-4.750 -0.2899 0.01432 0.00750 -0.0450 0.6561 0.3967
-4.500 -0.2622 0.01452 0.00766 -0.0448 0.6525 0.4265
-4.250 -0.2344 0.01480 0.00787 -0.0445 0.6496 0.4485
-4.000 -0.2067 0.01510 0.00803 -0.0442 0.6470 0.4664
-3.750 -0.1787 0.01538 0.00823 -0.0440 0.6442 0.4808
-3.500 -0.1506 0.01557 0.00841 -0.0439 0.6407 0.4933
-3.250 -0.1227 0.01573 0.00849 -0.0438 0.6373 0.5052
-3.000 -0.0948 0.01588 0.00851 -0.0436 0.6345 0.5171
-2.750 -0.0670 0.01599 0.00860 -0.0434 0.6322 0.5261
-2.500 -0.0392 0.01611 0.00863 -0.0433 0.6300 0.5356
-2.250 -0.0111 0.01620 0.00872 -0.0434 0.6268 0.5447
-2.000 0.0169 0.01623 0.00875 -0.0434 0.6236 0.5524
-1.750 0.0450 0.01630 0.00875 -0.0434 0.6206 0.5610
-1.500 0.0728 0.01631 0.00874 -0.0434 0.6182 0.5681
-1.250 0.1009 0.01639 0.00874 -0.0434 0.6161 0.5760
-1.000 0.1288 0.01646 0.00878 -0.0434 0.6139 0.5823
-0.750 0.1568 0.01654 0.00891 -0.0436 0.6105 0.5889
-0.500 0.1849 0.01662 0.00895 -0.0438 0.6074 0.5954
-0.250 0.2128 0.01666 0.00902 -0.0439 0.6048 0.6012
0.000 0.2410 0.01675 0.00905 -0.0440 0.6025 0.6079
0.250 0.2691 0.01678 0.00906 -0.0440 0.6004 0.6134
0.500 0.2968 0.01692 0.00922 -0.0441 0.5978 0.6191
0.750 0.3246 0.01713 0.00945 -0.0445 0.5944 0.6251
1.000 0.3522 0.01723 0.00963 -0.0447 0.5914 0.6299
1.250 0.3802 0.01732 0.00973 -0.0448 0.5887 0.6357
1.500 0.4085 0.01740 0.00977 -0.0449 0.5863 0.6414
1.750 0.4365 0.01748 0.00986 -0.0449 0.5842 0.6466
2.000 0.4634 0.01777 0.01024 -0.0451 0.5810 0.6527
2.250 0.4903 0.01801 0.01057 -0.0453 0.5771 0.6585
2.500 0.5178 0.01812 0.01075 -0.0454 0.5740 0.6648
3.000 0.5740 0.01823 0.01090 -0.0454 0.5691 0.6786
3.250 0.6002 0.01856 0.01134 -0.0455 0.5655 0.6871
3.500 0.6258 0.01881 0.01176 -0.0455 0.5609 0.6958
3.750 0.6534 0.01885 0.01188 -0.0455 0.5576 0.7062
4.000 0.6815 0.01879 0.01188 -0.0454 0.5549 0.7191
4.250 0.7097 0.01873 0.01190 -0.0452 0.5525 0.7364
4.500 0.7318 0.01909 0.01261 -0.0448 0.5463 0.7639
4.750 0.7608 0.01877 0.01266 -0.0447 0.5424 0.8501
5.000 0.8131 0.01851 0.01247 -0.0494 0.5389 1.0000
5.250 0.8395 0.01880 0.01278 -0.0494 0.5342 1.0000
5.500 0.8657 0.01899 0.01301 -0.0494 0.5285 1.0000
5.750 0.8948 0.01882 0.01281 -0.0493 0.5246 1.0000
6.000 0.9241 0.01870 0.01264 -0.0492 0.5210 1.0000
6.250 0.9475 0.01899 0.01308 -0.0488 0.5137 1.0000
6.500 0.9769 0.01871 0.01277 -0.0486 0.5093 1.0000
6.750 1.0042 0.01863 0.01273 -0.0484 0.5039 1.0000
7.000 1.0300 0.01855 0.01273 -0.0480 0.4966 1.0000
7.250 1.0610 0.01805 0.01217 -0.0479 0.4919 1.0000
7.500 1.0842 0.01812 0.01241 -0.0473 0.4829 1.0000
7.750 1.1145 0.01761 0.01185 -0.0471 0.4771 1.0000
8.000 1.1378 0.01757 0.01198 -0.0464 0.4670 1.0000
8.250 1.1642 0.01728 0.01176 -0.0459 0.4578 1.0000
8.500 1.1910 0.01692 0.01142 -0.0454 0.4474 1.0000
8.750 1.2145 0.01681 0.01143 -0.0446 0.4336 1.0000
9.000 1.2375 0.01676 0.01145 -0.0438 0.4172 1.0000
9.250 1.2586 0.01687 0.01165 -0.0428 0.3956 1.0000
9.500 1.2776 0.01713 0.01187 -0.0416 0.3693 1.0000
9.750 1.2918 0.01772 0.01234 -0.0399 0.3365 1.0000
10.000 1.2991 0.01872 0.01315 -0.0375 0.3022 1.0000
10.250 1.3004 0.02002 0.01429 -0.0346 0.2714 1.0000
10.500 1.2945 0.02146 0.01561 -0.0309 0.2466 1.0000
10.750 1.2842 0.02334 0.01742 -0.0277 0.2271 1.0000
11.000 1.2757 0.02566 0.01968 -0.0258 0.2070 1.0000
11.250 1.2676 0.02829 0.02223 -0.0245 0.1891 1.0000
11.500 1.2596 0.03110 0.02496 -0.0235 0.1724 1.0000
11.750 1.2524 0.03395 0.02773 -0.0226 0.1572 1.0000
12.000 1.2460 0.03679 0.03052 -0.0219 0.1431 1.0000
12.250 1.2403 0.03966 0.03333 -0.0213 0.1298 1.0000
12.500 1.2359 0.04245 0.03609 -0.0208 0.1176 1.0000
12.750 1.2323 0.04523 0.03885 -0.0203 0.1067 1.0000
13.000 1.2284 0.04807 0.04167 -0.0200 0.0973 1.0000
13.250 1.2226 0.05117 0.04468 -0.0197 0.0892 1.0000
13.500 1.2226 0.05389 0.04745 -0.0196 0.0807 1.0000
13.750 1.2208 0.05682 0.05037 -0.0195 0.0739 1.0000
14.000 1.2196 0.05980 0.05336 -0.0196 0.0677 1.0000
14.250 1.2197 0.06265 0.05624 -0.0196 0.0621 1.0000
14.500 1.2199 0.06561 0.05922 -0.0199 0.0573 1.0000
14.750 1.2198 0.06853 0.06215 -0.0199 0.0530 1.0000
15.000 1.2214 0.07149 0.06519 -0.0204 0.0488 1.0000
15.250 1.2208 0.07443 0.06803 -0.0203 0.0450 1.0000
15.500 1.2231 0.07751 0.07130 -0.0210 0.0420 1.0000
15.750 1.2242 0.08064 0.07448 -0.0216 0.0393 1.0000
16.000 1.2265 0.08327 0.07703 -0.0215 0.0364 1.0000
16.250 1.2267 0.08681 0.08076 -0.0225 0.0342 1.0000
16.500 1.2270 0.09027 0.08430 -0.0234 0.0320 1.0000
16.750 1.2286 0.09324 0.08724 -0.0240 0.0299 1.0000
17.000 1.2296 0.09658 0.09072 -0.0246 0.0282 1.0000
17.250 1.2291 0.10033 0.09462 -0.0257 0.0266 1.0000
17.500 1.2296 0.10387 0.09823 -0.0269 0.0253 1.0000
17.750 1.2328 0.10677 0.10111 -0.0276 0.0240 1.0000
18.000 1.2310 0.11066 0.10515 -0.0287 0.0228 1.0000
18.250 1.2268 0.11530 0.10998 -0.0306 0.0219 1.0000
18.500 1.2220 0.12009 0.11492 -0.0329 0.0208 1.0000
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Polar data table (+)
Polar graphs
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