EPPLER 339 AIRFOIL (e339-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 339 AIRFOIL (e339-il) Reynolds number: 500,000 Max Cl/Cd: 98.88 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e339-il-500000.txt Download as CSV file: xf-e339-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 339 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3021 0.11449 0.11223 -0.0289 1.0000 0.0130
-10.500 -0.3000 0.11088 0.10864 -0.0303 1.0000 0.0130
-10.250 -0.2988 0.10712 0.10490 -0.0319 1.0000 0.0130
-10.000 -0.2965 0.10370 0.10152 -0.0325 1.0000 0.0131
-9.750 -0.2894 0.10139 0.09924 -0.0312 1.0000 0.0132
-9.500 -0.2889 0.09796 0.09584 -0.0326 1.0000 0.0132
-9.250 -0.2854 0.09528 0.09319 -0.0326 1.0000 0.0133
-9.000 -0.2835 0.09244 0.09038 -0.0329 1.0000 0.0135
-8.750 -0.2768 0.08879 0.08676 -0.0355 0.9983 0.0137
-8.500 -0.2652 0.08432 0.08231 -0.0399 0.9565 0.0140
-8.250 -0.2063 0.07473 0.07259 -0.0614 0.9141 0.0148
-8.000 -0.1802 0.06733 0.06476 -0.0761 0.8272 0.0151
-7.750 -0.1902 0.06468 0.06189 -0.0754 0.7830 0.0150
-7.500 -0.2033 0.06149 0.05852 -0.0742 0.7553 0.0154
-7.250 -0.2132 0.05633 0.05310 -0.0738 0.7363 0.0158
-7.000 -0.2148 0.05229 0.04880 -0.0721 0.7196 0.0159
-6.750 -0.2124 0.04987 0.04629 -0.0707 0.7016 0.0161
-6.500 -0.2054 0.04749 0.04376 -0.0692 0.6862 0.0161
-6.250 -0.1964 0.04556 0.04171 -0.0679 0.6714 0.0163
-6.000 -0.1861 0.04346 0.03947 -0.0665 0.6582 0.0167
-5.750 -0.1747 0.04117 0.03701 -0.0650 0.6462 0.0172
-5.500 -0.1667 0.03602 0.03132 -0.0611 0.6371 0.0192
-5.250 -0.1522 0.03428 0.02949 -0.0599 0.6253 0.0194
-5.000 -0.1365 0.03291 0.02799 -0.0588 0.6140 0.0199
-4.750 -0.1194 0.03111 0.02601 -0.0572 0.6031 0.0209
-4.500 -0.1039 0.02805 0.02252 -0.0544 0.5943 0.0230
-4.250 -0.0842 0.02695 0.02134 -0.0535 0.5839 0.0245
-4.000 -0.0654 0.02471 0.01870 -0.0512 0.5755 0.0271
-3.750 -0.0437 0.02364 0.01752 -0.0504 0.5659 0.0282
-3.500 -0.0223 0.02206 0.01560 -0.0487 0.5577 0.0317
-3.000 0.0243 0.02015 0.01341 -0.0470 0.5403 0.0381
-2.750 0.0532 0.01655 0.00920 -0.0448 0.5331 0.0241
-2.500 0.0821 0.01425 0.00651 -0.0436 0.5261 0.0172
-2.250 0.1080 0.01337 0.00548 -0.0427 0.5187 0.0164
-2.000 0.1323 0.01284 0.00487 -0.0418 0.5116 0.0164
-1.750 0.1564 0.01240 0.00439 -0.0409 0.5049 0.0166
-1.500 0.1805 0.01203 0.00400 -0.0400 0.4980 0.0174
-1.250 0.2046 0.01179 0.00367 -0.0392 0.4915 0.0185
-1.000 0.2293 0.01148 0.00337 -0.0384 0.4854 0.0205
-0.750 0.2539 0.01124 0.00311 -0.0376 0.4796 0.0274
-0.500 0.2761 0.01082 0.00292 -0.0365 0.4743 0.1022
-0.250 0.2648 0.00837 0.00307 -0.0289 0.4709 0.8295
0.000 0.2815 0.00883 0.00355 -0.0254 0.4657 0.9004
0.250 0.3002 0.00937 0.00403 -0.0221 0.4607 0.9245
0.500 0.3489 0.01016 0.00471 -0.0249 0.4548 0.9471
0.750 0.4651 0.01085 0.00518 -0.0426 0.4465 0.9581
1.000 0.5148 0.01104 0.00522 -0.0471 0.4408 0.9648
1.250 0.5467 0.01101 0.00516 -0.0480 0.4363 0.9665
1.500 0.5760 0.01101 0.00512 -0.0485 0.4321 0.9685
1.750 0.6017 0.01106 0.00509 -0.0482 0.4281 0.9707
2.000 0.6205 0.01121 0.00516 -0.0464 0.4241 0.9737
2.250 0.6526 0.01114 0.00509 -0.0475 0.4202 0.9746
2.500 0.6841 0.01113 0.00505 -0.0485 0.4163 0.9756
2.750 0.7138 0.01116 0.00503 -0.0490 0.4125 0.9768
3.000 0.7421 0.01126 0.00506 -0.0494 0.4086 0.9780
3.250 0.7701 0.01129 0.00509 -0.0496 0.4051 0.9795
3.500 0.7961 0.01132 0.00513 -0.0494 0.4017 0.9808
3.750 0.8212 0.01138 0.00518 -0.0491 0.3983 0.9824
4.000 0.8431 0.01148 0.00526 -0.0480 0.3949 0.9840
4.250 0.8696 0.01162 0.00534 -0.0481 0.3911 0.9848
4.500 0.8998 0.01161 0.00537 -0.0488 0.3879 0.9857
4.750 0.9289 0.01164 0.00542 -0.0494 0.3845 0.9866
5.000 0.9559 0.01170 0.00549 -0.0494 0.3809 0.9874
5.250 0.9819 0.01182 0.00557 -0.0494 0.3775 0.9882
5.500 1.0086 0.01196 0.00571 -0.0495 0.3739 0.9892
5.750 1.0354 0.01201 0.00581 -0.0495 0.3706 0.9904
6.000 1.0602 0.01208 0.00593 -0.0492 0.3669 0.9913
6.250 1.0845 0.01219 0.00604 -0.0488 0.3636 0.9922
6.500 1.1080 0.01239 0.00620 -0.0483 0.3596 0.9930
6.750 1.1322 0.01248 0.00637 -0.0478 0.3562 0.9940
7.000 1.1607 0.01254 0.00649 -0.0484 0.3522 0.9949
7.250 1.1869 0.01264 0.00661 -0.0484 0.3482 0.9956
7.500 1.2119 0.01284 0.00678 -0.0483 0.3439 0.9964
7.750 1.2373 0.01292 0.00695 -0.0482 0.3396 0.9973
8.000 1.2626 0.01302 0.00712 -0.0480 0.3352 0.9982
8.250 1.2873 0.01317 0.00728 -0.0478 0.3307 0.9990
8.500 1.3118 0.01338 0.00752 -0.0476 0.3263 0.9998
8.750 1.3319 0.01349 0.00773 -0.0464 0.3218 1.0000
9.000 1.3487 0.01364 0.00792 -0.0446 0.3173 1.0000
9.500 1.3792 0.01399 0.00838 -0.0404 0.3076 1.0000
9.750 1.3926 0.01415 0.00858 -0.0380 0.3020 1.0000
10.000 1.4029 0.01440 0.00883 -0.0350 0.2967 1.0000
10.250 1.4146 0.01452 0.00906 -0.0322 0.2909 1.0000
10.500 1.4206 0.01472 0.00928 -0.0284 0.2853 1.0000
10.750 1.4237 0.01491 0.00951 -0.0240 0.2802 1.0000
11.000 1.4203 0.01499 0.00966 -0.0183 0.2749 1.0000
11.250 1.4214 0.01524 0.00990 -0.0138 0.2690 1.0000
11.500 1.4351 0.01553 0.01027 -0.0118 0.2612 1.0000
11.750 1.4462 0.01600 0.01073 -0.0096 0.2532 1.0000
12.000 1.4595 0.01647 0.01124 -0.0078 0.2433 1.0000
12.250 1.4706 0.01706 0.01185 -0.0059 0.2332 1.0000
12.500 1.4788 0.01781 0.01261 -0.0037 0.2234 1.0000
12.750 1.4846 0.01873 0.01353 -0.0015 0.2126 1.0000
13.000 1.4900 0.01976 0.01457 0.0005 0.2009 1.0000
13.250 1.4947 0.02092 0.01576 0.0024 0.1916 1.0000
13.500 1.4939 0.02252 0.01735 0.0044 0.1797 1.0000
13.750 1.4922 0.02435 0.01920 0.0061 0.1715 1.0000
14.000 1.4902 0.02639 0.02126 0.0074 0.1608 1.0000
14.250 1.4827 0.02904 0.02390 0.0085 0.1488 1.0000
14.500 1.4767 0.03175 0.02663 0.0093 0.1402 1.0000
14.750 1.4663 0.03501 0.02991 0.0098 0.1318 1.0000
15.000 1.4578 0.03823 0.03316 0.0101 0.1239 1.0000
15.250 1.4465 0.04183 0.03680 0.0102 0.1162 1.0000
15.500 1.4365 0.04541 0.04044 0.0101 0.1115 1.0000
15.750 1.4249 0.04928 0.04436 0.0099 0.1050 1.0000
16.000 1.4088 0.05382 0.04891 0.0093 0.0986 1.0000
16.250 1.4034 0.05726 0.05244 0.0088 0.0951 1.0000
16.500 1.3864 0.06218 0.05736 0.0078 0.0882 1.0000
16.750 1.3809 0.06582 0.06109 0.0070 0.0848 1.0000
17.000 1.3658 0.07076 0.06603 0.0057 0.0785 1.0000
17.250 1.3595 0.07467 0.07001 0.0047 0.0743 1.0000
17.500 1.3502 0.07906 0.07444 0.0034 0.0706 1.0000
17.750 1.3422 0.08335 0.07879 0.0021 0.0670 1.0000
18.000 1.3345 0.08768 0.08318 0.0006 0.0632 1.0000
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