EPPLER 715 AIRFOIL (e715-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 715 AIRFOIL (e715-il) Reynolds number: 500,000 Max Cl/Cd: 113.28 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e715-il-500000.txt Download as CSV file: xf-e715-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.5984 0.12260 0.12040 -0.0031 1.0000 0.0096
-14.250 -0.6592 0.10230 0.09995 -0.0140 1.0000 0.0089
-14.000 -0.7131 0.08526 0.08265 -0.0248 1.0000 0.0086
-13.750 -0.7442 0.07488 0.07205 -0.0318 1.0000 0.0084
-13.500 -0.7851 0.06424 0.06109 -0.0389 1.0000 0.0081
-13.250 -0.7959 0.05922 0.05596 -0.0422 1.0000 0.0082
-13.000 -0.8191 0.05270 0.04919 -0.0459 1.0000 0.0080
-12.750 -0.8254 0.04882 0.04522 -0.0483 1.0000 0.0081
-12.500 -0.8378 0.04421 0.04041 -0.0505 1.0000 0.0079
-12.250 -0.8301 0.03986 0.03570 -0.0562 0.8783 0.0079
-12.000 -0.8370 0.03744 0.03284 -0.0559 0.7952 0.0080
-11.750 -0.8416 0.03476 0.02987 -0.0563 0.7616 0.0080
-11.250 -0.8459 0.03087 0.02558 -0.0550 0.7221 0.0083
-11.000 -0.8447 0.02936 0.02386 -0.0530 0.7089 0.0083
-10.750 -0.8358 0.02793 0.02225 -0.0519 0.6977 0.0085
-10.500 -0.8236 0.02664 0.02079 -0.0508 0.6882 0.0088
-10.250 -0.8096 0.02536 0.01933 -0.0498 0.6797 0.0091
-10.000 -0.7935 0.02418 0.01799 -0.0489 0.6722 0.0093
-9.750 -0.7753 0.02319 0.01682 -0.0481 0.6651 0.0096
-9.500 -0.7568 0.02214 0.01563 -0.0474 0.6590 0.0099
-9.250 -0.7415 0.02064 0.01404 -0.0464 0.6528 0.0104
-9.000 -0.7210 0.01979 0.01308 -0.0458 0.6475 0.0108
-8.750 -0.6989 0.01905 0.01226 -0.0453 0.6425 0.0114
-8.500 -0.6764 0.01829 0.01141 -0.0448 0.6376 0.0121
-8.250 -0.6532 0.01763 0.01062 -0.0443 0.6333 0.0128
-8.000 -0.6315 0.01675 0.00967 -0.0438 0.6294 0.0143
-7.750 -0.6062 0.01627 0.00911 -0.0435 0.6254 0.0161
-7.500 -0.5825 0.01555 0.00836 -0.0431 0.6216 0.0188
-7.250 -0.5581 0.01492 0.00767 -0.0428 0.6179 0.0227
-7.000 -0.5331 0.01440 0.00708 -0.0425 0.6144 0.0278
-6.750 -0.5073 0.01387 0.00656 -0.0423 0.6111 0.0344
-6.500 -0.4814 0.01340 0.00610 -0.0421 0.6079 0.0436
-6.250 -0.4552 0.01296 0.00568 -0.0419 0.6048 0.0562
-6.000 -0.4292 0.01252 0.00528 -0.0418 0.6020 0.0746
-5.750 -0.4032 0.01211 0.00493 -0.0417 0.5992 0.0998
-5.500 -0.3768 0.01164 0.00460 -0.0416 0.5966 0.1319
-5.250 -0.3501 0.01122 0.00430 -0.0416 0.5937 0.1674
-5.000 -0.3235 0.01079 0.00401 -0.0415 0.5909 0.2077
-4.750 -0.2968 0.01039 0.00374 -0.0415 0.5884 0.2530
-4.500 -0.2700 0.01004 0.00353 -0.0415 0.5861 0.3020
-4.250 -0.2430 0.00981 0.00341 -0.0414 0.5837 0.3487
-4.000 -0.2150 0.00966 0.00336 -0.0414 0.5816 0.3843
-3.750 -0.1865 0.00960 0.00334 -0.0414 0.5791 0.4112
-3.500 -0.1578 0.00962 0.00335 -0.0415 0.5765 0.4314
-3.250 -0.1289 0.00966 0.00336 -0.0415 0.5741 0.4460
-3.000 -0.0999 0.00973 0.00336 -0.0416 0.5720 0.4578
-2.750 -0.0710 0.00983 0.00338 -0.0416 0.5700 0.4676
-2.500 -0.0422 0.00995 0.00345 -0.0417 0.5678 0.4757
-2.250 -0.0131 0.01000 0.00346 -0.0418 0.5658 0.4838
-2.000 0.0158 0.01001 0.00347 -0.0419 0.5635 0.4904
-1.750 0.0448 0.01006 0.00349 -0.0420 0.5613 0.4969
-1.500 0.0738 0.01010 0.00348 -0.0421 0.5592 0.5027
-1.250 0.1027 0.01011 0.00349 -0.0422 0.5572 0.5078
-1.000 0.1316 0.01018 0.00350 -0.0423 0.5553 0.5134
-0.750 0.1605 0.01026 0.00352 -0.0424 0.5532 0.5186
-0.500 0.1893 0.01028 0.00358 -0.0426 0.5512 0.5233
-0.250 0.2183 0.01030 0.00360 -0.0427 0.5492 0.5281
0.000 0.2474 0.01036 0.00363 -0.0429 0.5472 0.5323
0.250 0.2761 0.01032 0.00362 -0.0430 0.5450 0.5363
0.500 0.3050 0.01034 0.00364 -0.0432 0.5428 0.5407
0.750 0.3340 0.01038 0.00366 -0.0433 0.5408 0.5453
1.000 0.3628 0.01044 0.00368 -0.0435 0.5390 0.5491
1.250 0.3915 0.01053 0.00378 -0.0436 0.5369 0.5528
1.500 0.4203 0.01052 0.00383 -0.0438 0.5349 0.5565
1.750 0.4492 0.01055 0.00388 -0.0440 0.5326 0.5604
2.000 0.4781 0.01058 0.00393 -0.0442 0.5303 0.5638
2.250 0.5067 0.01056 0.00395 -0.0443 0.5279 0.5674
2.500 0.5355 0.01058 0.00398 -0.0445 0.5257 0.5711
2.750 0.5643 0.01064 0.00404 -0.0446 0.5234 0.5749
3.000 0.5929 0.01076 0.00415 -0.0448 0.5210 0.5787
3.250 0.6213 0.01071 0.00421 -0.0449 0.5181 0.5827
3.500 0.6498 0.01070 0.00427 -0.0450 0.5150 0.5868
3.750 0.6784 0.01070 0.00429 -0.0452 0.5119 0.5913
4.000 0.7071 0.01070 0.00431 -0.0453 0.5091 0.5959
4.250 0.7353 0.01077 0.00441 -0.0454 0.5060 0.6009
4.500 0.7635 0.01074 0.00449 -0.0455 0.5024 0.6064
4.750 0.7917 0.01070 0.00453 -0.0456 0.4985 0.6122
5.000 0.8200 0.01066 0.00454 -0.0456 0.4949 0.6194
5.250 0.8482 0.01071 0.00460 -0.0457 0.4913 0.6277
5.500 0.8758 0.01064 0.00471 -0.0457 0.4871 0.6379
5.750 0.9035 0.01057 0.00475 -0.0457 0.4825 0.6517
6.000 0.9309 0.01048 0.00477 -0.0456 0.4780 0.6744
6.250 0.9564 0.01028 0.00488 -0.0452 0.4727 0.7350
6.500 0.9997 0.00975 0.00493 -0.0482 0.4658 1.0000
6.750 1.0270 0.00981 0.00499 -0.0482 0.4599 1.0000
7.000 1.0543 0.00984 0.00509 -0.0481 0.4523 1.0000
7.250 1.0812 0.00990 0.00517 -0.0480 0.4443 1.0000
7.500 1.1079 0.00997 0.00527 -0.0479 0.4342 1.0000
7.750 1.1344 0.01008 0.00542 -0.0477 0.4222 1.0000
8.000 1.1600 0.01024 0.00559 -0.0474 0.4063 1.0000
8.250 1.1846 0.01050 0.00581 -0.0471 0.3863 1.0000
8.500 1.2072 0.01093 0.00615 -0.0465 0.3590 1.0000
8.750 1.2271 0.01157 0.00664 -0.0456 0.3232 1.0000
9.000 1.2436 0.01247 0.00736 -0.0443 0.2848 1.0000
9.250 1.2590 0.01340 0.00813 -0.0430 0.2505 1.0000
9.500 1.2729 0.01437 0.00895 -0.0415 0.2203 1.0000
9.750 1.2849 0.01536 0.00982 -0.0398 0.1933 1.0000
10.000 1.2941 0.01641 0.01075 -0.0377 0.1705 1.0000
10.250 1.3009 0.01745 0.01171 -0.0354 0.1506 1.0000
10.500 1.3000 0.01857 0.01280 -0.0320 0.1362 1.0000
10.750 1.2975 0.02009 0.01430 -0.0294 0.1235 1.0000
11.000 1.2959 0.02202 0.01620 -0.0279 0.1110 1.0000
11.250 1.2956 0.02412 0.01828 -0.0269 0.1001 1.0000
11.500 1.2944 0.02641 0.02054 -0.0260 0.0894 1.0000
11.750 1.2956 0.02855 0.02268 -0.0252 0.0803 1.0000
12.000 1.2964 0.03076 0.02488 -0.0245 0.0718 1.0000
12.250 1.2952 0.03316 0.02727 -0.0238 0.0647 1.0000
12.500 1.2957 0.03544 0.02955 -0.0232 0.0579 1.0000
12.750 1.2965 0.03772 0.03184 -0.0226 0.0524 1.0000
13.000 1.2958 0.04016 0.03428 -0.0221 0.0472 1.0000
13.250 1.2968 0.04247 0.03663 -0.0217 0.0428 1.0000
13.500 1.2964 0.04495 0.03912 -0.0213 0.0389 1.0000
13.750 1.2956 0.04758 0.04179 -0.0211 0.0358 1.0000
14.000 1.2990 0.04987 0.04411 -0.0210 0.0326 1.0000
14.250 1.2963 0.05288 0.04713 -0.0210 0.0297 1.0000
14.500 1.2997 0.05531 0.04963 -0.0210 0.0277 1.0000
14.750 1.3018 0.05791 0.05227 -0.0211 0.0255 1.0000
15.000 1.2975 0.06137 0.05574 -0.0215 0.0233 1.0000
15.250 1.3014 0.06388 0.05834 -0.0217 0.0218 1.0000
15.500 1.3034 0.06670 0.06121 -0.0221 0.0201 1.0000
15.750 1.2993 0.07034 0.06490 -0.0227 0.0188 1.0000
16.000 1.2989 0.07358 0.06823 -0.0233 0.0178 1.0000
16.250 1.3010 0.07656 0.07129 -0.0239 0.0164 1.0000
16.500 1.2992 0.08011 0.07488 -0.0247 0.0153 1.0000
16.750 1.2935 0.08431 0.07914 -0.0258 0.0142 1.0000
17.000 1.2928 0.08786 0.08280 -0.0268 0.0135 1.0000
17.250 1.2934 0.09129 0.08629 -0.0278 0.0125 1.0000
17.500 1.2896 0.09545 0.09053 -0.0292 0.0120 1.0000
17.750 1.2814 0.10037 0.09552 -0.0309 0.0115 1.0000
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Polar data table (+)
Polar graphs
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