EPPLER 1200 AIRFOIL (e1200-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1200 AIRFOIL (e1200-il) Reynolds number: 1,000,000 Max Cl/Cd: 131.83 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1200-il-1000000.txt Download as CSV file: xf-e1200-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1200 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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.3407 0.16658 0.16478 -0.0470 1.0000 0.0151
-16.250 -0.3360 0.16348 0.16170 -0.0481 1.0000 0.0156
-16.000 -0.5820 0.09532 0.09323 -0.0754 1.0000 0.0146
-15.750 -0.5587 0.09682 0.09482 -0.0739 1.0000 0.0148
-15.500 -0.5354 0.09843 0.09651 -0.0724 1.0000 0.0150
-15.250 -0.5049 0.09881 0.09694 -0.0739 0.9992 0.0153
-15.000 -0.7354 0.05043 0.04729 -0.1075 0.9925 0.0142
-14.750 -0.7367 0.04612 0.04282 -0.1114 0.9796 0.0142
-14.500 -0.7248 0.04184 0.03838 -0.1175 0.9586 0.0144
-14.250 -0.6958 0.03785 0.03419 -0.1264 0.9467 0.0145
-14.000 -0.6576 0.03437 0.03050 -0.1359 0.9308 0.0147
-13.750 -0.6330 0.03205 0.02789 -0.1408 0.8958 0.0148
-13.500 -0.6299 0.03063 0.02624 -0.1399 0.8693 0.0149
-13.250 -0.6265 0.02938 0.02485 -0.1386 0.8528 0.0151
-13.000 -0.6221 0.02816 0.02348 -0.1373 0.8407 0.0152
-12.750 -0.6167 0.02687 0.02206 -0.1360 0.8311 0.0152
-12.500 -0.6093 0.02578 0.02085 -0.1347 0.8232 0.0153
-12.250 -0.6006 0.02480 0.01978 -0.1334 0.8163 0.0156
-12.000 -0.5913 0.02382 0.01868 -0.1320 0.8098 0.0156
-11.750 -0.5809 0.02283 0.01761 -0.1306 0.8045 0.0158
-11.500 -0.5693 0.02198 0.01667 -0.1293 0.7992 0.0159
-11.250 -0.5575 0.02117 0.01576 -0.1278 0.7944 0.0162
-11.000 -0.5445 0.02038 0.01489 -0.1264 0.7903 0.0163
-10.750 -0.5311 0.01978 0.01423 -0.1250 0.7865 0.0165
-10.500 -0.5179 0.01918 0.01355 -0.1234 0.7827 0.0167
-10.250 -0.5057 0.01872 0.01300 -0.1215 0.7789 0.0170
-10.000 -0.4923 0.01826 0.01246 -0.1196 0.7752 0.0171
-9.750 -0.4746 0.01779 0.01195 -0.1184 0.7724 0.0172
-9.500 -0.4620 0.01649 0.01058 -0.1167 0.7694 0.0176
-9.250 -0.4457 0.01579 0.00986 -0.1154 0.7665 0.0180
-9.000 -0.4272 0.01525 0.00928 -0.1143 0.7637 0.0182
-8.750 -0.4070 0.01482 0.00880 -0.1134 0.7609 0.0185
-8.500 -0.3858 0.01441 0.00836 -0.1127 0.7583 0.0189
-8.250 -0.3642 0.01398 0.00791 -0.1120 0.7562 0.0192
-8.000 -0.3415 0.01361 0.00751 -0.1114 0.7538 0.0197
-7.750 -0.3187 0.01322 0.00709 -0.1109 0.7515 0.0201
-7.500 -0.2950 0.01289 0.00672 -0.1104 0.7493 0.0205
-7.250 -0.2705 0.01260 0.00639 -0.1101 0.7471 0.0208
-7.000 -0.2478 0.01214 0.00587 -0.1095 0.7448 0.0214
-6.750 -0.2239 0.01176 0.00545 -0.1092 0.7423 0.0222
-6.500 -0.1987 0.01145 0.00514 -0.1090 0.7406 0.0230
-6.250 -0.1728 0.01119 0.00487 -0.1088 0.7387 0.0239
-6.000 -0.1464 0.01095 0.00463 -0.1088 0.7367 0.0248
-5.750 -0.1199 0.01070 0.00435 -0.1087 0.7348 0.0258
-5.500 -0.0937 0.01042 0.00406 -0.1086 0.7329 0.0276
-5.250 -0.0666 0.01022 0.00384 -0.1087 0.7310 0.0295
-5.000 -0.0396 0.01000 0.00362 -0.1087 0.7288 0.0335
-4.750 -0.0131 0.00970 0.00341 -0.1088 0.7264 0.0525
-4.500 0.0129 0.00929 0.00320 -0.1088 0.7249 0.0908
-4.250 0.0399 0.00899 0.00304 -0.1090 0.7234 0.1231
-4.000 0.0671 0.00870 0.00289 -0.1092 0.7215 0.1584
-3.750 0.0946 0.00840 0.00274 -0.1094 0.7195 0.1996
-3.500 0.1221 0.00806 0.00259 -0.1097 0.7176 0.2544
-3.250 0.1491 0.00756 0.00241 -0.1101 0.7157 0.3446
-3.000 0.1762 0.00700 0.00222 -0.1106 0.7139 0.4573
-2.750 0.2047 0.00671 0.00218 -0.1110 0.7117 0.5428
-2.500 0.2342 0.00669 0.00221 -0.1115 0.7095 0.5776
-2.250 0.2634 0.00666 0.00222 -0.1118 0.7080 0.5986
-2.000 0.2927 0.00665 0.00224 -0.1121 0.7060 0.6149
-1.750 0.3220 0.00667 0.00227 -0.1124 0.7036 0.6293
-1.500 0.3513 0.00668 0.00228 -0.1126 0.7009 0.6388
-1.250 0.3806 0.00670 0.00226 -0.1129 0.6978 0.6453
-1.000 0.4103 0.00678 0.00227 -0.1133 0.6939 0.6506
-0.750 0.4387 0.00674 0.00227 -0.1134 0.6906 0.6561
-0.500 0.4675 0.00674 0.00226 -0.1135 0.6863 0.6619
-0.250 0.4963 0.00676 0.00224 -0.1137 0.6820 0.6677
0.000 0.5251 0.00681 0.00228 -0.1139 0.6778 0.6740
0.250 0.5538 0.00683 0.00233 -0.1140 0.6746 0.6797
0.500 0.5828 0.00687 0.00235 -0.1143 0.6710 0.6840
0.750 0.6113 0.00684 0.00235 -0.1145 0.6674 0.6881
1.000 0.6399 0.00687 0.00236 -0.1146 0.6637 0.6910
1.250 0.6686 0.00690 0.00238 -0.1149 0.6600 0.6935
1.500 0.6973 0.00690 0.00240 -0.1151 0.6557 0.6961
1.750 0.7258 0.00692 0.00241 -0.1153 0.6513 0.6985
2.000 0.7540 0.00698 0.00242 -0.1154 0.6465 0.7004
2.250 0.7823 0.00696 0.00244 -0.1156 0.6415 0.7030
2.500 0.8103 0.00696 0.00246 -0.1157 0.6356 0.7055
2.750 0.8376 0.00701 0.00249 -0.1156 0.6295 0.7077
3.000 0.8654 0.00704 0.00254 -0.1157 0.6218 0.7100
3.250 0.8921 0.00710 0.00258 -0.1156 0.6137 0.7124
3.500 0.9192 0.00716 0.00263 -0.1155 0.6035 0.7149
3.750 0.9452 0.00726 0.00270 -0.1152 0.5909 0.7170
4.000 0.9699 0.00737 0.00277 -0.1147 0.5756 0.7195
4.250 0.9927 0.00753 0.00287 -0.1138 0.5552 0.7219
4.500 1.0135 0.00779 0.00304 -0.1126 0.5292 0.7243
4.750 1.0315 0.00814 0.00326 -0.1108 0.4979 0.7270
5.000 1.0475 0.00857 0.00353 -0.1087 0.4649 0.7298
5.250 1.0621 0.00902 0.00383 -0.1064 0.4331 0.7324
5.500 1.0763 0.00945 0.00412 -0.1040 0.4062 0.7346
5.750 1.0884 0.00979 0.00438 -0.1011 0.3829 0.7378
6.250 1.1115 0.01064 0.00506 -0.0954 0.3399 0.7438
6.500 1.1251 0.01106 0.00541 -0.0930 0.3222 0.7470
6.750 1.1384 0.01150 0.00578 -0.0907 0.3058 0.7500
7.000 1.1515 0.01195 0.00618 -0.0883 0.2902 0.7531
7.250 1.1647 0.01241 0.00660 -0.0861 0.2771 0.7565
7.500 1.1786 0.01287 0.00704 -0.0841 0.2655 0.7600
7.750 1.1933 0.01333 0.00749 -0.0822 0.2550 0.7638
8.000 1.2068 0.01388 0.00799 -0.0802 0.2448 0.7674
8.250 1.2207 0.01440 0.00851 -0.0784 0.2352 0.7715
8.500 1.2355 0.01492 0.00903 -0.0767 0.2271 0.7757
8.750 1.2487 0.01554 0.00963 -0.0749 0.2186 0.7801
9.000 1.2643 0.01608 0.01018 -0.0735 0.2117 0.7844
9.250 1.2781 0.01670 0.01081 -0.0719 0.2047 0.7895
9.500 1.2925 0.01732 0.01146 -0.0705 0.1982 0.7952
9.750 1.3074 0.01796 0.01210 -0.0691 0.1917 0.8009
10.000 1.3200 0.01870 0.01285 -0.0675 0.1850 0.8073
10.250 1.3359 0.01930 0.01349 -0.0664 0.1799 0.8145
10.500 1.3484 0.02009 0.01429 -0.0648 0.1733 0.8224
10.750 1.3625 0.02080 0.01503 -0.0636 0.1667 0.8319
11.000 1.3763 0.02152 0.01581 -0.0622 0.1621 0.8435
11.250 1.3874 0.02238 0.01670 -0.0607 0.1553 0.8593
11.500 1.4001 0.02308 0.01749 -0.0592 0.1497 0.8842
11.750 1.4113 0.02383 0.01839 -0.0577 0.1436 1.0000
12.000 1.4260 0.02467 0.01924 -0.0568 0.1385 1.0000
12.250 1.4382 0.02569 0.02023 -0.0558 0.1320 1.0000
12.500 1.4505 0.02671 0.02124 -0.0547 0.1257 1.0000
12.750 1.4633 0.02771 0.02224 -0.0538 0.1204 1.0000
13.000 1.4736 0.02891 0.02342 -0.0526 0.1148 1.0000
13.250 1.4874 0.02989 0.02441 -0.0518 0.1105 1.0000
13.500 1.4972 0.03117 0.02567 -0.0508 0.1048 1.0000
13.750 1.5089 0.03232 0.02684 -0.0499 0.1005 1.0000
14.000 1.5211 0.03347 0.02801 -0.0491 0.0969 1.0000
14.250 1.5299 0.03490 0.02942 -0.0482 0.0919 1.0000
14.500 1.5412 0.03615 0.03070 -0.0474 0.0878 1.0000
14.750 1.5511 0.03756 0.03212 -0.0466 0.0839 1.0000
15.000 1.5587 0.03916 0.03371 -0.0458 0.0789 1.0000
15.250 1.5695 0.04054 0.03513 -0.0452 0.0762 1.0000
15.500 1.5780 0.04214 0.03674 -0.0445 0.0724 1.0000
15.750 1.5844 0.04397 0.03857 -0.0438 0.0681 1.0000
16.000 1.5940 0.04553 0.04017 -0.0433 0.0657 1.0000
16.250 1.6014 0.04731 0.04198 -0.0427 0.0624 1.0000
16.500 1.6057 0.04945 0.04412 -0.0422 0.0586 1.0000
16.750 1.6138 0.05125 0.04597 -0.0418 0.0560 1.0000
17.000 1.6185 0.05344 0.04818 -0.0414 0.0529 1.0000
17.250 1.6215 0.05586 0.05062 -0.0411 0.0495 1.0000
17.500 1.6275 0.05799 0.05280 -0.0409 0.0471 1.0000
17.750 1.6300 0.06055 0.05539 -0.0408 0.0445 1.0000
18.000 1.6313 0.06332 0.05818 -0.0407 0.0413 1.0000
18.250 1.6343 0.06595 0.06087 -0.0408 0.0392 1.0000
18.500 1.6327 0.06919 0.06413 -0.0410 0.0363 1.0000
18.750 1.6328 0.07228 0.06727 -0.0413 0.0339 1.0000
19.000 1.6314 0.07563 0.07067 -0.0418 0.0315 1.0000
19.250 1.6271 0.07945 0.07455 -0.0424 0.0294 1.0000
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