EPPLER 715 AIRFOIL (e715-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 715 AIRFOIL (e715-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.36 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e715-il-1000000-n5.txt Download as CSV file: xf-e715-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.8912 0.10000 0.09735 -0.0143 1.0000 0.0025
-16.500 -0.9157 0.09112 0.08834 -0.0194 1.0000 0.0024
-16.250 -0.9489 0.08093 0.07799 -0.0255 1.0000 0.0025
-16.000 -0.9592 0.07514 0.07209 -0.0289 1.0000 0.0024
-15.500 -0.9828 0.06132 0.05757 -0.0403 0.8102 0.0024
-15.250 -1.0067 0.05509 0.05108 -0.0436 0.7745 0.0024
-15.000 -1.0152 0.05112 0.04693 -0.0454 0.7466 0.0024
-14.750 -1.0335 0.04612 0.04175 -0.0477 0.7280 0.0025
-14.500 -1.0424 0.04241 0.03789 -0.0492 0.7115 0.0026
-14.250 -1.0472 0.03924 0.03458 -0.0503 0.6972 0.0025
-14.000 -1.0554 0.03574 0.03095 -0.0516 0.6852 0.0025
-13.750 -1.0573 0.03290 0.02799 -0.0526 0.6739 0.0026
-13.500 -1.0606 0.02993 0.02488 -0.0539 0.6636 0.0025
-13.250 -1.0643 0.02743 0.02225 -0.0545 0.6547 0.0026
-12.750 -1.0636 0.02474 0.01933 -0.0507 0.6380 0.0027
-12.250 -1.0382 0.02273 0.01710 -0.0486 0.6235 0.0027
-12.000 -1.0215 0.02188 0.01615 -0.0478 0.6167 0.0028
-11.750 -1.0035 0.02107 0.01524 -0.0470 0.6114 0.0028
-11.500 -0.9842 0.02032 0.01440 -0.0463 0.6060 0.0029
-11.250 -0.9638 0.01962 0.01362 -0.0457 0.6008 0.0031
-11.000 -0.9426 0.01895 0.01286 -0.0452 0.5965 0.0031
-10.750 -0.9206 0.01832 0.01215 -0.0447 0.5922 0.0032
-10.500 -0.8977 0.01775 0.01150 -0.0443 0.5877 0.0033
-10.000 -0.8506 0.01669 0.01028 -0.0435 0.5799 0.0035
-9.750 -0.8263 0.01620 0.00972 -0.0431 0.5759 0.0036
-9.500 -0.8024 0.01564 0.00909 -0.0428 0.5722 0.0039
-9.250 -0.7777 0.01516 0.00855 -0.0425 0.5689 0.0041
-9.000 -0.7524 0.01474 0.00807 -0.0422 0.5662 0.0043
-8.750 -0.7268 0.01433 0.00762 -0.0420 0.5635 0.0046
-8.500 -0.7008 0.01396 0.00719 -0.0418 0.5606 0.0049
-8.250 -0.6746 0.01362 0.00679 -0.0416 0.5578 0.0053
-8.000 -0.6485 0.01325 0.00638 -0.0414 0.5550 0.0060
-7.750 -0.6220 0.01292 0.00601 -0.0413 0.5523 0.0068
-7.500 -0.5952 0.01261 0.00567 -0.0411 0.5501 0.0077
-7.250 -0.5683 0.01230 0.00534 -0.0410 0.5476 0.0091
-7.000 -0.5413 0.01201 0.00503 -0.0409 0.5452 0.0107
-6.500 -0.4868 0.01147 0.00445 -0.0408 0.5407 0.0156
-6.250 -0.4596 0.01121 0.00418 -0.0407 0.5385 0.0197
-6.000 -0.4321 0.01095 0.00392 -0.0407 0.5366 0.0248
-5.750 -0.4045 0.01069 0.00368 -0.0407 0.5348 0.0306
-5.250 -0.3496 0.01011 0.00319 -0.0406 0.5306 0.0535
-5.000 -0.3220 0.00985 0.00297 -0.0406 0.5286 0.0687
-4.750 -0.2942 0.00960 0.00277 -0.0406 0.5268 0.0851
-4.500 -0.2665 0.00935 0.00258 -0.0407 0.5249 0.1044
-4.250 -0.2387 0.00911 0.00240 -0.0407 0.5230 0.1274
-4.000 -0.2110 0.00884 0.00222 -0.0407 0.5212 0.1574
-3.750 -0.1829 0.00859 0.00207 -0.0408 0.5196 0.1847
-3.500 -0.1547 0.00838 0.00193 -0.0409 0.5179 0.2110
-3.250 -0.1267 0.00814 0.00180 -0.0409 0.5162 0.2439
-3.000 -0.0987 0.00788 0.00166 -0.0410 0.5145 0.2830
-2.750 -0.0705 0.00768 0.00156 -0.0411 0.5127 0.3183
-2.500 -0.0422 0.00751 0.00148 -0.0412 0.5109 0.3504
-2.250 -0.0137 0.00741 0.00143 -0.0413 0.5090 0.3750
-2.000 0.0151 0.00736 0.00140 -0.0414 0.5070 0.3959
-1.750 0.0440 0.00731 0.00138 -0.0415 0.5057 0.4115
-1.500 0.0732 0.00728 0.00137 -0.0417 0.5043 0.4241
-1.250 0.1023 0.00726 0.00137 -0.0418 0.5027 0.4341
-1.000 0.1316 0.00726 0.00136 -0.0420 0.5009 0.4415
-0.750 0.1607 0.00726 0.00137 -0.0421 0.4990 0.4484
-0.500 0.1900 0.00727 0.00136 -0.0423 0.4972 0.4540
-0.250 0.2191 0.00728 0.00137 -0.0425 0.4955 0.4597
0.000 0.2482 0.00730 0.00138 -0.0426 0.4937 0.4653
0.250 0.2773 0.00735 0.00140 -0.0428 0.4917 0.4695
0.500 0.3065 0.00735 0.00141 -0.0430 0.4902 0.4731
0.750 0.3356 0.00735 0.00144 -0.0431 0.4887 0.4767
1.000 0.3648 0.00737 0.00146 -0.0433 0.4869 0.4809
1.250 0.3940 0.00739 0.00149 -0.0435 0.4849 0.4846
1.500 0.4231 0.00741 0.00151 -0.0437 0.4828 0.4878
1.750 0.4521 0.00743 0.00154 -0.0439 0.4807 0.4908
2.000 0.4810 0.00746 0.00158 -0.0440 0.4784 0.4937
2.250 0.5100 0.00750 0.00162 -0.0442 0.4761 0.4963
2.500 0.5391 0.00752 0.00166 -0.0444 0.4736 0.4988
2.750 0.5682 0.00755 0.00170 -0.0446 0.4705 0.5010
3.000 0.5971 0.00757 0.00174 -0.0448 0.4670 0.5035
3.250 0.6258 0.00760 0.00178 -0.0449 0.4634 0.5060
3.500 0.6546 0.00764 0.00185 -0.0451 0.4601 0.5088
3.750 0.6836 0.00767 0.00190 -0.0453 0.4561 0.5113
4.000 0.7123 0.00771 0.00196 -0.0455 0.4514 0.5137
4.250 0.7408 0.00778 0.00203 -0.0456 0.4467 0.5161
4.500 0.7696 0.00781 0.00210 -0.0458 0.4417 0.5187
4.750 0.7980 0.00787 0.00218 -0.0459 0.4356 0.5214
5.000 0.8264 0.00794 0.00227 -0.0461 0.4297 0.5242
5.250 0.8547 0.00802 0.00237 -0.0462 0.4214 0.5273
5.500 0.8828 0.00812 0.00248 -0.0463 0.4115 0.5303
5.750 0.9104 0.00826 0.00260 -0.0464 0.3996 0.5332
6.000 0.9377 0.00843 0.00276 -0.0464 0.3854 0.5365
6.250 0.9644 0.00866 0.00295 -0.0463 0.3663 0.5400
6.500 0.9901 0.00898 0.00320 -0.0462 0.3430 0.5437
6.750 1.0147 0.00943 0.00353 -0.0459 0.3131 0.5476
7.000 1.0381 0.00995 0.00393 -0.0455 0.2796 0.5523
7.250 1.0617 0.01044 0.00433 -0.0451 0.2533 0.5574
7.500 1.0840 0.01101 0.00478 -0.0446 0.2233 0.5624
7.750 1.1061 0.01156 0.00524 -0.0441 0.1976 0.5685
8.000 1.1282 0.01208 0.00568 -0.0435 0.1752 0.5758
8.250 1.1491 0.01264 0.00618 -0.0428 0.1537 0.5854
8.500 1.1691 0.01320 0.00669 -0.0420 0.1330 0.5983
8.750 1.1879 0.01379 0.00724 -0.0410 0.1146 0.6170
9.000 1.2066 0.01430 0.00777 -0.0400 0.1005 0.6483
9.250 1.2209 0.01452 0.00835 -0.0381 0.0886 0.7994
9.500 1.2494 0.01492 0.00904 -0.0393 0.0753 1.0000
9.750 1.2644 0.01561 0.00968 -0.0379 0.0656 1.0000
10.000 1.2776 0.01631 0.01036 -0.0362 0.0572 1.0000
10.250 1.2860 0.01699 0.01104 -0.0336 0.0516 1.0000
10.750 1.2916 0.01923 0.01329 -0.0288 0.0403 1.0000
11.000 1.2960 0.02074 0.01481 -0.0276 0.0357 1.0000
11.250 1.3026 0.02228 0.01637 -0.0267 0.0319 1.0000
11.500 1.3088 0.02394 0.01805 -0.0260 0.0286 1.0000
11.750 1.3156 0.02560 0.01973 -0.0254 0.0258 1.0000
12.000 1.3202 0.02747 0.02161 -0.0248 0.0225 1.0000
12.250 1.3259 0.02927 0.02343 -0.0242 0.0202 1.0000
12.500 1.3306 0.03116 0.02534 -0.0237 0.0182 1.0000
12.750 1.3355 0.03304 0.02726 -0.0231 0.0161 1.0000
13.000 1.3405 0.03494 0.02919 -0.0227 0.0151 1.0000
13.250 1.3451 0.03687 0.03116 -0.0222 0.0139 1.0000
13.500 1.3489 0.03888 0.03320 -0.0218 0.0124 1.0000
13.750 1.3532 0.04089 0.03525 -0.0214 0.0117 1.0000
14.000 1.3556 0.04308 0.03747 -0.0211 0.0102 1.0000
14.250 1.3597 0.04517 0.03961 -0.0208 0.0095 1.0000
14.500 1.3625 0.04748 0.04195 -0.0207 0.0087 1.0000
14.750 1.3672 0.04963 0.04415 -0.0206 0.0080 1.0000
15.000 1.3713 0.05192 0.04650 -0.0206 0.0075 1.0000
15.250 1.3749 0.05427 0.04890 -0.0206 0.0070 1.0000
15.500 1.3770 0.05685 0.05152 -0.0207 0.0063 1.0000
15.750 1.3808 0.05927 0.05400 -0.0209 0.0059 1.0000
16.000 1.3842 0.06179 0.05657 -0.0211 0.0057 1.0000
16.250 1.3859 0.06454 0.05937 -0.0214 0.0050 1.0000
16.500 1.3872 0.06740 0.06228 -0.0218 0.0046 1.0000
16.750 1.3890 0.07026 0.06521 -0.0223 0.0043 1.0000
17.000 1.3910 0.07311 0.06812 -0.0228 0.0041 1.0000
17.250 1.3911 0.07627 0.07134 -0.0235 0.0038 1.0000
17.500 1.3921 0.07935 0.07449 -0.0242 0.0036 1.0000
17.750 1.3917 0.08272 0.07793 -0.0250 0.0035 1.0000
18.000 1.3904 0.08623 0.08150 -0.0260 0.0033 1.0000
18.250 1.3889 0.08984 0.08519 -0.0270 0.0031 1.0000
18.500 1.3871 0.09358 0.08901 -0.0282 0.0030 1.0000
18.750 1.3860 0.09725 0.09276 -0.0294 0.0028 1.0000
19.000 1.3827 0.10134 0.09692 -0.0309 0.0026 1.0000
19.250 1.3790 0.10553 0.10120 -0.0325 0.0025 1.0000
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