EPPLER 1200 AIRFOIL (e1200-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1200 AIRFOIL (e1200-il) Reynolds number: 500,000 Max Cl/Cd: 96.07 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1200-il-500000-n5.txt Download as CSV file: xf-e1200-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.5993 0.09179 0.08875 -0.0780 1.0000 0.0133
-15.750 -0.6479 0.07813 0.07484 -0.0865 0.9997 0.0132
-15.500 -0.6698 0.06874 0.06524 -0.0936 0.9919 0.0132
-15.250 -0.6831 0.06130 0.05760 -0.1001 0.9810 0.0132
-15.000 -0.6874 0.05464 0.05070 -0.1073 0.9578 0.0133
-14.750 -0.6752 0.04891 0.04472 -0.1162 0.9439 0.0134
-14.500 -0.6557 0.04388 0.03938 -0.1253 0.9302 0.0136
-14.250 -0.6314 0.04010 0.03533 -0.1329 0.9120 0.0136
-14.000 -0.6184 0.03739 0.03231 -0.1364 0.8875 0.0138
-13.750 -0.6142 0.03545 0.03014 -0.1368 0.8680 0.0139
-13.500 -0.6124 0.03359 0.02812 -0.1363 0.8538 0.0140
-13.000 -0.6031 0.03069 0.02498 -0.1347 0.8329 0.0144
-12.750 -0.5967 0.02943 0.02360 -0.1338 0.8246 0.0145
-12.500 -0.5885 0.02829 0.02237 -0.1329 0.8172 0.0146
-12.250 -0.5796 0.02728 0.02126 -0.1319 0.8107 0.0149
-12.000 -0.5702 0.02621 0.02009 -0.1308 0.8053 0.0150
-11.750 -0.5596 0.02526 0.01907 -0.1297 0.7999 0.0152
-11.500 -0.5487 0.02432 0.01803 -0.1285 0.7950 0.0153
-11.250 -0.5369 0.02348 0.01709 -0.1274 0.7909 0.0155
-11.000 -0.5246 0.02262 0.01615 -0.1262 0.7866 0.0156
-10.750 -0.5117 0.02185 0.01530 -0.1249 0.7824 0.0158
-10.500 -0.4987 0.02112 0.01448 -0.1236 0.7783 0.0160
-10.250 -0.4853 0.02044 0.01371 -0.1222 0.7748 0.0164
-10.000 -0.4720 0.01975 0.01297 -0.1207 0.7715 0.0166
-9.750 -0.4594 0.01915 0.01230 -0.1189 0.7681 0.0167
-9.500 -0.4469 0.01866 0.01173 -0.1171 0.7649 0.0169
-9.250 -0.4305 0.01820 0.01119 -0.1157 0.7621 0.0171
-9.000 -0.4152 0.01756 0.01049 -0.1143 0.7595 0.0174
-8.750 -0.3981 0.01698 0.00989 -0.1131 0.7568 0.0177
-8.500 -0.3791 0.01648 0.00937 -0.1121 0.7539 0.0181
-8.250 -0.3589 0.01603 0.00890 -0.1113 0.7512 0.0185
-8.000 -0.3373 0.01566 0.00848 -0.1106 0.7488 0.0191
-7.750 -0.3154 0.01527 0.00806 -0.1100 0.7466 0.0196
-7.500 -0.2928 0.01492 0.00765 -0.1094 0.7445 0.0202
-7.250 -0.2694 0.01461 0.00727 -0.1090 0.7424 0.0207
-7.000 -0.2464 0.01422 0.00687 -0.1085 0.7402 0.0212
-6.750 -0.2232 0.01383 0.00647 -0.1080 0.7378 0.0219
-6.500 -0.1990 0.01350 0.00612 -0.1077 0.7356 0.0227
-6.250 -0.1741 0.01322 0.00582 -0.1074 0.7335 0.0236
-6.000 -0.1487 0.01296 0.00553 -0.1072 0.7315 0.0246
-5.750 -0.1231 0.01271 0.00524 -0.1070 0.7296 0.0260
-5.500 -0.0974 0.01245 0.00497 -0.1069 0.7276 0.0282
-5.250 -0.0713 0.01222 0.00472 -0.1068 0.7257 0.0315
-5.000 -0.0455 0.01194 0.00450 -0.1067 0.7237 0.0384
-4.750 -0.0196 0.01164 0.00428 -0.1067 0.7218 0.0537
-4.500 0.0065 0.01136 0.00408 -0.1067 0.7198 0.0725
-4.250 0.0329 0.01108 0.00390 -0.1067 0.7177 0.0958
-4.000 0.0595 0.01081 0.00373 -0.1068 0.7156 0.1231
-3.750 0.0864 0.01055 0.00357 -0.1069 0.7136 0.1537
-3.500 0.1132 0.01024 0.00340 -0.1071 0.7119 0.1961
-3.250 0.1403 0.00989 0.00324 -0.1074 0.7102 0.2526
-3.000 0.1667 0.00943 0.00306 -0.1077 0.7083 0.3289
-2.750 0.1929 0.00886 0.00288 -0.1081 0.7062 0.4333
-2.500 0.2200 0.00847 0.00285 -0.1083 0.7041 0.5339
-2.250 0.2484 0.00840 0.00291 -0.1085 0.7020 0.5787
-2.000 0.2773 0.00841 0.00293 -0.1087 0.6999 0.6011
-1.750 0.3064 0.00844 0.00294 -0.1090 0.6978 0.6137
-1.500 0.3356 0.00847 0.00295 -0.1093 0.6959 0.6232
-1.250 0.3652 0.00853 0.00295 -0.1096 0.6938 0.6327
-1.000 0.3936 0.00856 0.00301 -0.1097 0.6913 0.6409
-0.750 0.4222 0.00860 0.00304 -0.1099 0.6882 0.6509
-0.500 0.4503 0.00863 0.00310 -0.1099 0.6844 0.6602
-0.250 0.4790 0.00867 0.00308 -0.1101 0.6803 0.6678
0.000 0.5071 0.00869 0.00310 -0.1101 0.6760 0.6726
0.250 0.5347 0.00869 0.00311 -0.1101 0.6701 0.6765
0.500 0.5627 0.00869 0.00307 -0.1101 0.6641 0.6797
0.750 0.5908 0.00871 0.00305 -0.1102 0.6585 0.6826
1.000 0.6186 0.00872 0.00306 -0.1103 0.6528 0.6850
1.250 0.6463 0.00873 0.00307 -0.1103 0.6477 0.6871
1.500 0.6740 0.00876 0.00310 -0.1103 0.6426 0.6896
1.750 0.7015 0.00879 0.00314 -0.1103 0.6366 0.6922
2.000 0.7288 0.00883 0.00315 -0.1103 0.6306 0.6947
2.250 0.7562 0.00887 0.00320 -0.1103 0.6235 0.6971
2.500 0.7829 0.00892 0.00322 -0.1101 0.6156 0.6997
2.750 0.8096 0.00897 0.00328 -0.1100 0.6068 0.7021
3.000 0.8351 0.00904 0.00333 -0.1096 0.5965 0.7043
3.250 0.8597 0.00913 0.00340 -0.1090 0.5835 0.7065
3.500 0.8835 0.00926 0.00349 -0.1083 0.5679 0.7088
3.750 0.9059 0.00943 0.00359 -0.1073 0.5485 0.7115
4.000 0.9252 0.00970 0.00375 -0.1058 0.5227 0.7144
4.250 0.9426 0.01004 0.00395 -0.1040 0.4951 0.7171
4.500 0.9573 0.01043 0.00421 -0.1016 0.4667 0.7194
4.750 0.9695 0.01086 0.00452 -0.0988 0.4385 0.7218
5.000 0.9793 0.01127 0.00484 -0.0956 0.4130 0.7245
5.250 0.9899 0.01172 0.00519 -0.0926 0.3915 0.7276
5.500 1.0016 0.01219 0.00557 -0.0899 0.3701 0.7308
5.750 1.0136 0.01269 0.00598 -0.0873 0.3502 0.7338
6.000 1.0260 0.01318 0.00642 -0.0849 0.3328 0.7365
6.250 1.0387 0.01368 0.00687 -0.0826 0.3171 0.7392
6.500 1.0509 0.01423 0.00737 -0.0803 0.3011 0.7424
6.750 1.0641 0.01477 0.00788 -0.0783 0.2881 0.7461
7.000 1.0776 0.01534 0.00841 -0.0763 0.2770 0.7496
7.250 1.0913 0.01591 0.00896 -0.0745 0.2655 0.7528
7.500 1.1052 0.01650 0.00954 -0.0728 0.2547 0.7561
7.750 1.1187 0.01713 0.01016 -0.0711 0.2456 0.7597
8.000 1.1336 0.01774 0.01077 -0.0696 0.2368 0.7636
8.250 1.1475 0.01842 0.01144 -0.0681 0.2283 0.7677
8.500 1.1619 0.01907 0.01210 -0.0667 0.2202 0.7719
8.750 1.1761 0.01975 0.01280 -0.0653 0.2138 0.7765
9.000 1.1912 0.02043 0.01349 -0.0640 0.2065 0.7812
9.250 1.2044 0.02121 0.01428 -0.0626 0.2000 0.7859
9.500 1.2197 0.02188 0.01499 -0.0614 0.1935 0.7909
9.750 1.2326 0.02271 0.01583 -0.0601 0.1869 0.7967
10.000 1.2476 0.02344 0.01660 -0.0590 0.1813 0.8029
10.250 1.2614 0.02423 0.01743 -0.0578 0.1754 0.8100
10.750 1.2887 0.02588 0.01916 -0.0555 0.1647 0.8264
11.000 1.3015 0.02677 0.02009 -0.0543 0.1590 0.8361
11.250 1.3139 0.02767 0.02105 -0.0530 0.1543 0.8482
11.500 1.3268 0.02849 0.02195 -0.0518 0.1495 0.8636
11.750 1.3364 0.02943 0.02297 -0.0502 0.1440 0.8897
12.250 1.3644 0.03130 0.02499 -0.0488 0.1344 1.0000
12.500 1.3759 0.03250 0.02619 -0.0479 0.1297 1.0000
12.750 1.3889 0.03361 0.02732 -0.0472 0.1249 1.0000
13.000 1.3998 0.03489 0.02859 -0.0464 0.1183 1.0000
13.250 1.4105 0.03622 0.02993 -0.0456 0.1136 1.0000
13.500 1.4219 0.03752 0.03124 -0.0449 0.1074 1.0000
13.750 1.4303 0.03909 0.03279 -0.0441 0.1019 1.0000
14.000 1.4419 0.04041 0.03415 -0.0435 0.0971 1.0000
14.250 1.4499 0.04206 0.03580 -0.0428 0.0917 1.0000
14.500 1.4601 0.04357 0.03734 -0.0422 0.0882 1.0000
14.750 1.4695 0.04516 0.03898 -0.0417 0.0842 1.0000
15.000 1.4772 0.04695 0.04077 -0.0411 0.0803 1.0000
15.250 1.4853 0.04872 0.04258 -0.0407 0.0767 1.0000
15.500 1.4931 0.05056 0.04447 -0.0403 0.0728 1.0000
15.750 1.4985 0.05269 0.04661 -0.0399 0.0689 1.0000
16.000 1.5054 0.05470 0.04866 -0.0396 0.0654 1.0000
16.250 1.5115 0.05683 0.05085 -0.0393 0.0623 1.0000
16.500 1.5150 0.05929 0.05333 -0.0392 0.0590 1.0000
16.750 1.5200 0.06164 0.05574 -0.0391 0.0563 1.0000
17.000 1.5245 0.06409 0.05825 -0.0391 0.0534 1.0000
17.250 1.5256 0.06699 0.06119 -0.0392 0.0504 1.0000
17.500 1.5279 0.06981 0.06407 -0.0394 0.0478 1.0000
17.750 1.5301 0.07269 0.06702 -0.0397 0.0454 1.0000
18.000 1.5297 0.07598 0.07037 -0.0402 0.0429 1.0000
18.250 1.5292 0.07934 0.07380 -0.0408 0.0410 1.0000
18.500 1.5291 0.08273 0.07728 -0.0415 0.0391 1.0000
18.750 1.5265 0.08651 0.08113 -0.0424 0.0369 1.0000
19.000 1.5219 0.09064 0.08533 -0.0435 0.0351 1.0000
19.250 1.5189 0.09462 0.08940 -0.0447 0.0331 1.0000
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