EPPLER 344 AIRFOIL (e344-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 344 AIRFOIL (e344-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.75 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e344-il-1000000.txt Download as CSV file: xf-e344-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 344 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1223 0.08723 0.08457 -0.0591 0.6834 0.0103
-10.250 -0.1198 0.08372 0.08100 -0.0602 0.6696 0.0103
-10.000 -0.1248 0.07857 0.07583 -0.0617 0.6597 0.0104
-9.750 -0.1217 0.07573 0.07294 -0.0622 0.6461 0.0106
-9.500 -0.1225 0.07166 0.06885 -0.0636 0.6372 0.0106
-9.250 -0.1202 0.06862 0.06578 -0.0644 0.6266 0.0107
-9.000 -0.1185 0.06549 0.06262 -0.0653 0.6159 0.0109
-8.750 -0.1235 0.06102 0.05814 -0.0672 0.6088 0.0109
-8.500 -0.2057 0.06325 0.06030 -0.0811 0.6363 0.0106
-8.250 -0.2214 0.05980 0.05677 -0.0798 0.6257 0.0106
-8.000 -0.2266 0.05823 0.05514 -0.0776 0.6147 0.0107
-7.750 -0.2332 0.05470 0.05151 -0.0763 0.6064 0.0107
-7.500 -0.2311 0.05254 0.04926 -0.0749 0.5963 0.0108
-7.250 -0.1967 0.03774 0.03460 -0.0704 0.5709 0.0113
-7.000 -0.1994 0.03423 0.03098 -0.0687 0.5639 0.0113
-6.750 -0.1973 0.03111 0.02773 -0.0671 0.5572 0.0118
-6.500 -0.1998 0.02427 0.02049 -0.0634 0.5541 0.0130
-6.250 -0.2038 0.02020 0.01625 -0.0605 0.5474 0.0133
-6.000 -0.1925 0.01832 0.01423 -0.0588 0.5402 0.0134
-5.750 -0.1785 0.01685 0.01265 -0.0574 0.5318 0.0136
-5.500 -0.1636 0.01534 0.01101 -0.0560 0.5242 0.0139
-5.250 -0.1481 0.01372 0.00924 -0.0544 0.5171 0.0142
-5.000 -0.1322 0.01202 0.00732 -0.0526 0.5101 0.0148
-4.750 -0.1217 0.00873 0.00345 -0.0489 0.5060 0.0165
-4.500 -0.1008 0.00797 0.00263 -0.0481 0.4989 0.0168
-4.250 -0.0794 0.00734 0.00190 -0.0473 0.4921 0.0172
-4.000 -0.0572 0.00666 0.00109 -0.0464 0.4859 0.0180
-3.500 -0.0080 0.01316 0.00624 -0.0444 0.4800 0.0106
-3.250 0.0182 0.01282 0.00582 -0.0439 0.4737 0.0104
-3.000 0.0440 0.01239 0.00533 -0.0433 0.4673 0.0104
-2.750 0.0685 0.01191 0.00477 -0.0425 0.4608 0.0103
-2.500 0.0930 0.01142 0.00425 -0.0418 0.4560 0.0103
-2.250 0.1168 0.01098 0.00376 -0.0408 0.4508 0.0104
-2.000 0.1402 0.01063 0.00334 -0.0399 0.4453 0.0106
-1.750 0.1649 0.01034 0.00303 -0.0391 0.4410 0.0111
-1.500 0.1905 0.01016 0.00284 -0.0386 0.4361 0.0117
-1.250 0.2159 0.01003 0.00265 -0.0380 0.4310 0.0132
-1.000 0.2414 0.00989 0.00250 -0.0374 0.4266 0.0155
-0.750 0.2671 0.00971 0.00234 -0.0369 0.4229 0.0248
-0.500 0.2921 0.00952 0.00227 -0.0363 0.4189 0.0587
-0.250 0.3164 0.00933 0.00223 -0.0357 0.4149 0.1186
0.000 0.3169 0.00743 0.00204 -0.0312 0.4117 0.6630
0.250 0.3301 0.00713 0.00240 -0.0275 0.4093 0.8752
0.500 0.3533 0.00742 0.00271 -0.0259 0.4059 0.8944
0.750 0.3753 0.00775 0.00302 -0.0241 0.4024 0.9081
1.000 0.3971 0.00801 0.00325 -0.0223 0.3991 0.9152
1.250 0.4213 0.00823 0.00340 -0.0213 0.3955 0.9216
1.500 0.4422 0.00838 0.00356 -0.0193 0.3934 0.9281
1.750 0.4647 0.00861 0.00378 -0.0177 0.3908 0.9363
2.000 0.4885 0.00863 0.00377 -0.0167 0.3879 0.9394
2.250 0.5148 0.00867 0.00376 -0.0164 0.3848 0.9403
2.500 0.5408 0.00873 0.00377 -0.0161 0.3816 0.9412
2.750 0.5672 0.00877 0.00378 -0.0159 0.3791 0.9423
3.000 0.5944 0.00878 0.00378 -0.0159 0.3770 0.9431
3.250 0.6214 0.00880 0.00378 -0.0159 0.3745 0.9438
3.500 0.6480 0.00883 0.00380 -0.0158 0.3718 0.9448
3.750 0.6744 0.00889 0.00382 -0.0156 0.3693 0.9458
4.000 0.7004 0.00897 0.00387 -0.0155 0.3662 0.9466
4.250 0.7270 0.00905 0.00392 -0.0154 0.3636 0.9474
4.500 0.7546 0.00907 0.00396 -0.0156 0.3617 0.9480
4.750 0.7820 0.00911 0.00400 -0.0157 0.3596 0.9487
5.000 0.8092 0.00916 0.00405 -0.0158 0.3570 0.9495
5.250 0.8360 0.00924 0.00411 -0.0158 0.3544 0.9502
5.500 0.8625 0.00936 0.00420 -0.0159 0.3515 0.9508
5.750 0.8878 0.00946 0.00429 -0.0156 0.3485 0.9515
6.000 0.9147 0.00947 0.00433 -0.0156 0.3467 0.9522
6.250 0.9412 0.00951 0.00439 -0.0156 0.3445 0.9529
6.500 0.9675 0.00957 0.00446 -0.0155 0.3420 0.9536
6.750 0.9932 0.00965 0.00455 -0.0154 0.3394 0.9543
7.000 1.0182 0.00977 0.00466 -0.0151 0.3364 0.9552
7.250 1.0428 0.00992 0.00480 -0.0148 0.3331 0.9561
7.500 1.0693 0.00997 0.00490 -0.0148 0.3311 0.9569
7.750 1.0951 0.01003 0.00499 -0.0147 0.3284 0.9580
8.000 1.1203 0.01012 0.00510 -0.0145 0.3254 0.9591
8.250 1.1449 0.01025 0.00523 -0.0143 0.3222 0.9601
8.500 1.1682 0.01044 0.00541 -0.0138 0.3184 0.9612
8.750 1.1945 0.01050 0.00553 -0.0139 0.3161 0.9621
9.000 1.2201 0.01058 0.00565 -0.0138 0.3129 0.9629
9.250 1.2442 0.01070 0.00579 -0.0135 0.3089 0.9639
9.500 1.2648 0.01088 0.00596 -0.0126 0.3044 0.9655
9.750 1.2882 0.01095 0.00609 -0.0120 0.3011 0.9669
10.000 1.3103 0.01105 0.00623 -0.0113 0.2968 0.9686
10.250 1.3303 0.01122 0.00641 -0.0103 0.2923 0.9706
10.500 1.3508 0.01141 0.00663 -0.0093 0.2881 0.9727
10.750 1.3728 0.01156 0.00682 -0.0087 0.2832 0.9748
11.000 1.3936 0.01180 0.00708 -0.0079 0.2777 0.9776
11.250 1.4164 0.01203 0.00735 -0.0077 0.2719 0.9802
11.500 1.4390 0.01233 0.00766 -0.0074 0.2645 0.9830
11.750 1.4626 0.01266 0.00801 -0.0075 0.2567 0.9858
12.000 1.4870 0.01314 0.00848 -0.0080 0.2478 0.9883
12.250 1.5124 0.01356 0.00892 -0.0086 0.2383 0.9912
12.500 1.5348 0.01412 0.00947 -0.0089 0.2279 0.9989
12.750 1.5454 0.01474 0.01007 -0.0070 0.2183 1.0000
13.000 1.5550 0.01547 0.01078 -0.0052 0.2079 1.0000
13.250 1.5652 0.01623 0.01155 -0.0035 0.1983 1.0000
13.500 1.5715 0.01723 0.01253 -0.0016 0.1880 1.0000
13.750 1.5744 0.01848 0.01376 0.0004 0.1775 1.0000
14.000 1.5747 0.01999 0.01525 0.0023 0.1674 1.0000
14.250 1.5768 0.02152 0.01680 0.0038 0.1584 1.0000
14.500 1.5754 0.02342 0.01871 0.0052 0.1500 1.0000
14.750 1.5719 0.02564 0.02094 0.0065 0.1424 1.0000
15.000 1.5677 0.02806 0.02338 0.0074 0.1343 1.0000
15.250 1.5596 0.03094 0.02629 0.0082 0.1275 1.0000
15.500 1.5533 0.03381 0.02920 0.0087 0.1213 1.0000
15.750 1.5420 0.03722 0.03264 0.0092 0.1157 1.0000
16.000 1.5291 0.04090 0.03635 0.0094 0.1089 1.0000
16.500 1.5056 0.04840 0.04396 0.0093 0.0998 1.0000
16.750 1.4875 0.05304 0.04863 0.0089 0.0946 1.0000
17.000 1.4761 0.05705 0.05270 0.0084 0.0899 1.0000
17.250 1.4643 0.06122 0.05692 0.0078 0.0863 1.0000
17.500 1.4497 0.06581 0.06156 0.0069 0.0816 1.0000
17.750 1.4347 0.07056 0.06632 0.0059 0.0761 1.0000
18.000 1.4263 0.07462 0.07045 0.0049 0.0742 1.0000
18.250 1.4167 0.07890 0.07478 0.0038 0.0704 1.0000
18.500 1.4075 0.08315 0.07907 0.0026 0.0667 1.0000
18.750 1.3958 0.08787 0.08382 0.0011 0.0630 1.0000
19.000 1.3899 0.09187 0.08789 -0.0002 0.0599 1.0000
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