EPPLER 340 AIRFOIL (e340-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 340 AIRFOIL (e340-il) Reynolds number: 200,000 Max Cl/Cd: 57.05 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e340-il-200000-n5.txt Download as CSV file: xf-e340-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5350 0.09256 0.08949 -0.0023 1.0000 0.0264
-9.250 -0.5909 0.07206 0.06871 -0.0136 1.0000 0.0176
-8.750 -0.6233 0.06198 0.05835 -0.0097 1.0000 0.0141
-8.500 -0.6272 0.05939 0.05568 -0.0076 1.0000 0.0140
-8.250 -0.6244 0.05623 0.05232 -0.0066 0.8920 0.0138
-8.000 -0.6262 0.05333 0.04907 -0.0034 0.8252 0.0136
-7.750 -0.6257 0.05013 0.04554 -0.0004 0.7894 0.0133
-7.500 -0.6235 0.04655 0.04159 0.0027 0.7632 0.0129
-7.250 -0.6198 0.04249 0.03709 0.0060 0.7424 0.0125
-6.750 -0.6073 0.03171 0.02470 0.0143 0.7104 0.0112
-6.500 -0.5894 0.02952 0.02209 0.0161 0.6927 0.0112
-6.250 -0.5688 0.02751 0.01966 0.0176 0.6759 0.0112
-6.000 -0.5457 0.02574 0.01750 0.0187 0.6599 0.0112
-5.750 -0.5207 0.02419 0.01565 0.0194 0.6445 0.0113
-5.500 -0.4950 0.02287 0.01413 0.0199 0.6299 0.0115
-5.250 -0.4688 0.02178 0.01286 0.0203 0.6159 0.0117
-5.000 -0.4424 0.02081 0.01173 0.0207 0.6027 0.0121
-4.500 -0.3906 0.01913 0.00977 0.0217 0.5788 0.0130
-4.250 -0.3658 0.01840 0.00890 0.0224 0.5677 0.0137
-4.000 -0.3419 0.01776 0.00815 0.0232 0.5570 0.0145
-3.750 -0.3176 0.01725 0.00760 0.0239 0.5462 0.0159
-3.500 -0.2935 0.01682 0.00707 0.0247 0.5365 0.0183
-3.250 -0.2694 0.01642 0.00659 0.0255 0.5270 0.0213
-3.000 -0.2455 0.01598 0.00608 0.0263 0.5187 0.0253
-2.750 -0.2218 0.01556 0.00567 0.0272 0.5100 0.0349
-2.500 -0.1992 0.01508 0.00527 0.0282 0.5021 0.0609
-2.250 -0.1782 0.01451 0.00496 0.0293 0.4938 0.1254
-2.000 -0.1220 0.01335 0.00682 0.0259 0.4842 0.8255
-1.750 -0.1078 0.01382 0.00716 0.0294 0.4775 0.8622
-1.500 -0.0892 0.01439 0.00757 0.0321 0.4716 0.8838
-1.250 -0.0506 0.01515 0.00819 0.0310 0.4636 0.8992
-1.000 -0.0104 0.01588 0.00871 0.0295 0.4564 0.9135
-0.750 0.0390 0.01618 0.00886 0.0257 0.4481 0.9188
-0.500 0.0693 0.01620 0.00873 0.0252 0.4421 0.9222
-0.250 0.0913 0.01622 0.00864 0.0262 0.4372 0.9269
0.000 0.1208 0.01618 0.00851 0.0258 0.4313 0.9292
0.250 0.1532 0.01616 0.00837 0.0247 0.4256 0.9308
0.500 0.1844 0.01615 0.00825 0.0239 0.4204 0.9326
0.750 0.2142 0.01614 0.00817 0.0234 0.4149 0.9348
1.000 0.2416 0.01615 0.00810 0.0233 0.4103 0.9373
1.250 0.2643 0.01621 0.00805 0.0241 0.4063 0.9406
1.500 0.2919 0.01619 0.00802 0.0240 0.4013 0.9424
1.750 0.3233 0.01617 0.00795 0.0231 0.3964 0.9436
2.000 0.3537 0.01619 0.00789 0.0224 0.3923 0.9450
2.250 0.3828 0.01622 0.00787 0.0219 0.3886 0.9464
2.500 0.4111 0.01624 0.00789 0.0216 0.3843 0.9482
2.750 0.4377 0.01628 0.00791 0.0216 0.3801 0.9502
3.000 0.4618 0.01634 0.00792 0.0221 0.3763 0.9521
3.250 0.4864 0.01642 0.00797 0.0225 0.3728 0.9540
3.500 0.5169 0.01644 0.00802 0.0217 0.3684 0.9550
3.750 0.5460 0.01647 0.00806 0.0212 0.3643 0.9559
4.000 0.5745 0.01654 0.00811 0.0208 0.3607 0.9570
4.250 0.6026 0.01664 0.00817 0.0205 0.3577 0.9584
4.500 0.6295 0.01671 0.00830 0.0204 0.3538 0.9597
4.750 0.6549 0.01679 0.00842 0.0205 0.3498 0.9609
5.000 0.6790 0.01690 0.00855 0.0210 0.3461 0.9625
5.250 0.7029 0.01704 0.00866 0.0215 0.3429 0.9641
5.500 0.7312 0.01713 0.00882 0.0211 0.3390 0.9648
5.750 0.7588 0.01723 0.00900 0.0208 0.3350 0.9655
6.000 0.7860 0.01733 0.00915 0.0206 0.3312 0.9663
6.250 0.8133 0.01747 0.00928 0.0203 0.3276 0.9673
6.500 0.8399 0.01762 0.00951 0.0202 0.3237 0.9685
6.750 0.8648 0.01776 0.00976 0.0204 0.3193 0.9695
7.000 0.8887 0.01790 0.00996 0.0208 0.3150 0.9705
7.250 0.9116 0.01808 0.01014 0.0214 0.3113 0.9715
7.500 0.9340 0.01827 0.01045 0.0221 0.3068 0.9730
7.750 0.9612 0.01842 0.01071 0.0217 0.3018 0.9737
8.000 0.9866 0.01858 0.01091 0.0217 0.2971 0.9744
8.250 1.0113 0.01878 0.01121 0.0218 0.2920 0.9752
8.500 1.0355 0.01897 0.01152 0.0221 0.2862 0.9760
8.750 1.0587 0.01917 0.01177 0.0225 0.2812 0.9769
9.000 1.0817 0.01941 0.01215 0.0228 0.2753 0.9779
9.250 1.1039 0.01964 0.01247 0.0234 0.2686 0.9794
9.500 1.1235 0.01991 0.01283 0.0244 0.2623 0.9805
9.750 1.1449 0.02018 0.01322 0.0250 0.2549 0.9814
10.000 1.1669 0.02049 0.01360 0.0254 0.2475 0.9822
10.250 1.1877 0.02082 0.01404 0.0259 0.2387 0.9832
10.500 1.2072 0.02122 0.01454 0.0267 0.2298 0.9843
10.750 1.2240 0.02169 0.01506 0.0278 0.2210 0.9856
11.000 1.2403 0.02222 0.01569 0.0289 0.2106 0.9874
11.250 1.2565 0.02284 0.01638 0.0299 0.1997 0.9889
11.500 1.2707 0.02357 0.01717 0.0309 0.1886 0.9904
11.750 1.2808 0.02444 0.01809 0.0324 0.1775 0.9923
12.000 1.2861 0.02547 0.01916 0.0344 0.1666 0.9945
12.250 1.2891 0.02658 0.02034 0.0363 0.1559 0.9966
12.500 1.2878 0.02812 0.02195 0.0377 0.1465 0.9992
12.750 1.2724 0.03000 0.02387 0.0409 0.1405 1.0000
13.000 1.2551 0.03204 0.02599 0.0442 0.1356 1.0000
13.250 1.2378 0.03438 0.02839 0.0469 0.1304 1.0000
13.500 1.2177 0.03713 0.03118 0.0492 0.1261 1.0000
13.750 1.2018 0.03975 0.03387 0.0512 0.1212 1.0000
14.000 1.1838 0.04276 0.03693 0.0527 0.1166 1.0000
14.250 1.1647 0.04614 0.04034 0.0538 0.1126 1.0000
14.500 1.1516 0.04932 0.04359 0.0543 0.1075 1.0000
14.750 1.1366 0.05306 0.04736 0.0541 0.1029 1.0000
15.000 1.1235 0.05687 0.05122 0.0536 0.0985 1.0000
15.250 1.1128 0.06069 0.05511 0.0527 0.0935 1.0000
15.500 1.0996 0.06503 0.05946 0.0515 0.0893 1.0000
15.750 1.0922 0.06883 0.06335 0.0503 0.0846 1.0000
16.000 1.0824 0.07305 0.06761 0.0489 0.0802 1.0000
16.250 1.0731 0.07728 0.07189 0.0475 0.0764 1.0000
16.500 1.0666 0.08126 0.07594 0.0461 0.0722 1.0000
16.750 1.0574 0.08568 0.08039 0.0444 0.0686 1.0000
17.000 1.0506 0.08981 0.08458 0.0429 0.0651 1.0000
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