EPPLER 340 AIRFOIL (e340-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 340 AIRFOIL (e340-il) Reynolds number: 200,000 Max Cl/Cd: 58.75 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e340-il-200000.txt Download as CSV file: xf-e340-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 340 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3963 0.09144 0.08863 -0.0070 1.0000 0.0469
-9.500 -0.4023 0.08658 0.08380 -0.0090 1.0000 0.0478
-9.250 -0.4127 0.08092 0.07817 -0.0121 1.0000 0.0486
-9.000 -0.4310 0.07417 0.07143 -0.0169 1.0000 0.0486
-8.750 -0.4525 0.06840 0.06563 -0.0195 1.0000 0.0486
-8.500 -0.5964 0.07236 0.06907 -0.0100 1.0000 0.0446
-8.250 -0.5905 0.06950 0.06625 -0.0091 1.0000 0.0453
-8.000 -0.5891 0.06654 0.06326 -0.0079 1.0000 0.0463
-7.750 -0.5882 0.06349 0.06013 -0.0064 1.0000 0.0476
-7.500 -0.5883 0.06037 0.05684 -0.0045 1.0000 0.0499
-7.250 -0.6041 0.05716 0.05309 0.0002 1.0000 0.0526
-7.000 -0.5796 0.05289 0.04895 -0.0018 0.9405 0.0538
-6.750 -0.5605 0.05020 0.04604 -0.0015 0.8640 0.0558
-6.500 -0.5526 0.04831 0.04377 0.0017 0.8212 0.0592
-6.250 -0.5501 0.04555 0.04043 0.0056 0.7932 0.0634
-6.000 -0.5344 0.04311 0.03790 0.0070 0.7672 0.0652
-5.750 -0.5191 0.04129 0.03582 0.0089 0.7454 0.0688
-5.500 -0.5081 0.03908 0.03313 0.0118 0.7273 0.0756
-5.250 -0.4890 0.03699 0.03093 0.0130 0.7094 0.0787
-5.000 -0.4604 0.02757 0.01956 0.0201 0.6999 0.0308
-4.750 -0.4324 0.02522 0.01706 0.0204 0.6839 0.0294
-4.500 -0.4031 0.02317 0.01469 0.0209 0.6689 0.0281
-4.250 -0.3719 0.02146 0.01265 0.0211 0.6544 0.0275
-4.000 -0.3414 0.02019 0.01118 0.0212 0.6406 0.0279
-3.750 -0.3120 0.01913 0.01000 0.0213 0.6266 0.0290
-3.500 -0.2844 0.01831 0.00904 0.0218 0.6137 0.0306
-3.250 -0.2600 0.01755 0.00830 0.0225 0.6025 0.0350
-3.000 -0.2370 0.01683 0.00756 0.0236 0.5918 0.0407
-2.750 -0.2150 0.01613 0.00685 0.0249 0.5807 0.0500
-2.500 -0.1986 0.01494 0.00599 0.0272 0.5722 0.1177
-2.250 -0.1642 0.01437 0.00856 0.0295 0.5611 0.8680
-2.000 -0.0769 0.01760 0.01143 0.0227 0.5468 0.9175
-1.750 -0.0162 0.01849 0.01203 0.0178 0.5356 0.9419
-1.500 0.0700 0.01853 0.01173 0.0075 0.5229 0.9667
-1.250 0.1241 0.01820 0.01126 0.0022 0.5122 0.9814
-1.000 0.1646 0.01788 0.01073 -0.0007 0.5048 0.9871
-0.750 0.2067 0.01741 0.01016 -0.0040 0.4961 0.9926
-0.500 0.2507 0.01694 0.00948 -0.0076 0.4889 0.9979
-0.250 0.2834 0.01664 0.00915 -0.0091 0.4814 1.0000
0.000 0.3079 0.01655 0.00896 -0.0089 0.4757 1.0000
0.250 0.3327 0.01652 0.00883 -0.0088 0.4705 1.0000
0.500 0.3576 0.01644 0.00873 -0.0087 0.4643 1.0000
0.750 0.3823 0.01641 0.00859 -0.0085 0.4590 1.0000
1.000 0.4072 0.01644 0.00854 -0.0083 0.4544 1.0000
1.250 0.4323 0.01642 0.00853 -0.0082 0.4490 1.0000
1.500 0.4572 0.01643 0.00849 -0.0081 0.4443 1.0000
1.750 0.4821 0.01649 0.00845 -0.0078 0.4401 1.0000
2.000 0.5073 0.01653 0.00852 -0.0078 0.4351 1.0000
2.250 0.5324 0.01657 0.00856 -0.0076 0.4302 1.0000
2.500 0.5573 0.01663 0.00856 -0.0074 0.4260 1.0000
2.750 0.5824 0.01677 0.00864 -0.0072 0.4220 1.0000
3.000 0.6076 0.01684 0.00879 -0.0071 0.4171 1.0000
3.250 0.6326 0.01694 0.00889 -0.0069 0.4129 1.0000
3.500 0.6575 0.01705 0.00897 -0.0066 0.4092 1.0000
3.750 0.6825 0.01726 0.00914 -0.0064 0.4055 1.0000
4.000 0.7075 0.01737 0.00937 -0.0063 0.4007 1.0000
4.250 0.7324 0.01750 0.00953 -0.0060 0.3963 1.0000
4.500 0.7572 0.01763 0.00962 -0.0057 0.3925 1.0000
4.750 0.7820 0.01787 0.00986 -0.0055 0.3887 1.0000
5.000 0.8066 0.01806 0.01018 -0.0053 0.3841 1.0000
5.250 0.8311 0.01822 0.01039 -0.0050 0.3799 1.0000
5.500 0.8558 0.01837 0.01051 -0.0047 0.3761 1.0000
5.750 0.8802 0.01866 0.01084 -0.0044 0.3721 1.0000
6.000 0.9042 0.01887 0.01121 -0.0041 0.3672 1.0000
6.250 0.9284 0.01902 0.01139 -0.0038 0.3627 1.0000
6.500 0.9530 0.01921 0.01151 -0.0034 0.3589 1.0000
6.750 0.9764 0.01951 0.01199 -0.0030 0.3540 1.0000
7.000 0.9998 0.01970 0.01229 -0.0026 0.3489 1.0000
7.250 1.0239 0.01982 0.01240 -0.0021 0.3447 1.0000
7.500 1.0474 0.02012 0.01276 -0.0017 0.3401 1.0000
7.750 1.0696 0.02032 0.01314 -0.0011 0.3341 1.0000
8.000 1.0932 0.02042 0.01324 -0.0006 0.3293 1.0000
8.250 1.1162 0.02069 0.01356 0.0000 0.3245 1.0000
8.500 1.1373 0.02091 0.01398 0.0007 0.3182 1.0000
8.750 1.1605 0.02095 0.01401 0.0014 0.3129 1.0000
9.000 1.1814 0.02122 0.01442 0.0022 0.3068 1.0000
9.250 1.2023 0.02134 0.01466 0.0030 0.3003 1.0000
9.500 1.2248 0.02146 0.01472 0.0037 0.2948 1.0000
9.750 1.2428 0.02169 0.01521 0.0050 0.2871 1.0000
10.000 1.2640 0.02174 0.01522 0.0059 0.2807 1.0000
10.250 1.2808 0.02203 0.01575 0.0073 0.2726 1.0000
10.500 1.3001 0.02213 0.01583 0.0084 0.2655 1.0000
10.750 1.3150 0.02246 0.01638 0.0101 0.2563 1.0000
11.000 1.3306 0.02273 0.01672 0.0117 0.2480 1.0000
11.250 1.3438 0.02308 0.01717 0.0136 0.2383 1.0000
11.500 1.3548 0.02357 0.01779 0.0158 0.2280 1.0000
11.750 1.3631 0.02413 0.01840 0.0183 0.2177 1.0000
12.000 1.3673 0.02481 0.01910 0.0213 0.2075 1.0000
12.250 1.3677 0.02561 0.02002 0.0248 0.1967 1.0000
12.500 1.3617 0.02654 0.02101 0.0291 0.1875 1.0000
12.750 1.3422 0.02748 0.02197 0.0355 0.1816 1.0000
13.000 1.3228 0.02872 0.02328 0.0408 0.1758 1.0000
13.250 1.3038 0.03037 0.02497 0.0451 0.1696 1.0000
13.500 1.2848 0.03237 0.02698 0.0486 0.1639 1.0000
13.750 1.2671 0.03460 0.02929 0.0514 0.1572 1.0000
14.000 1.2471 0.03715 0.03180 0.0539 0.1519 1.0000
14.250 1.2307 0.03982 0.03457 0.0557 0.1452 1.0000
14.500 1.2122 0.04284 0.03755 0.0571 0.1396 1.0000
14.750 1.1977 0.04605 0.04085 0.0576 0.1330 1.0000
15.000 1.1829 0.04958 0.04434 0.0576 0.1270 1.0000
15.250 1.1707 0.05321 0.04805 0.0571 0.1206 1.0000
15.500 1.1581 0.05699 0.05180 0.0563 0.1147 1.0000
15.750 1.1477 0.06086 0.05573 0.0553 0.1086 1.0000
16.000 1.1374 0.06482 0.05970 0.0541 0.1029 1.0000
16.250 1.1286 0.06873 0.06364 0.0529 0.0973 1.0000
16.500 1.1196 0.07282 0.06776 0.0515 0.0919 1.0000
16.750 1.1127 0.07658 0.07151 0.0503 0.0868 1.0000
17.000 1.1044 0.08085 0.07588 0.0487 0.0819 1.0000
17.250 1.1001 0.08422 0.07915 0.0477 0.0770 1.0000
17.500 1.0917 0.08871 0.08379 0.0459 0.0728 1.0000
17.750 1.0866 0.09251 0.08757 0.0444 0.0687 1.0000
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Polar data table (+)
Polar graphs
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