EPPLER 664 AIRFOIL (e664-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 664 AIRFOIL (e664-il) Reynolds number: 200,000 Max Cl/Cd: 57.56 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e664-il-200000.txt Download as CSV file: xf-e664-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 664 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.1457 0.09890 0.09552 -0.0995 0.9479 0.0631
-12.000 -0.1326 0.09535 0.09195 -0.1017 0.9452 0.0649
-11.750 -0.3228 0.09446 0.09102 -0.1054 0.9616 0.0608
-11.500 -0.2780 0.09558 0.09217 -0.0969 0.9604 0.0625
-11.250 -0.2609 0.09220 0.08877 -0.0995 0.9561 0.0637
-11.000 -0.2494 0.08783 0.08438 -0.1035 0.9509 0.0658
-10.750 -0.2468 0.08086 0.07739 -0.1112 0.9465 0.0682
-10.500 -0.2864 0.06914 0.06548 -0.1253 0.9366 0.0709
-10.250 -0.3327 0.06504 0.06102 -0.1282 0.9241 0.0719
-10.000 -0.3679 0.06417 0.05982 -0.1245 0.9132 0.0724
-9.750 -0.3655 0.05740 0.05311 -0.1250 0.9080 0.0739
-9.500 -0.3515 0.05447 0.05018 -0.1249 0.9033 0.0752
-9.250 -0.3455 0.05216 0.04780 -0.1239 0.8985 0.0766
-9.000 -0.4110 0.04034 0.03461 -0.1124 0.8885 0.0401
-8.750 -0.4240 0.03651 0.02982 -0.1062 0.8833 0.0344
-8.500 -0.4038 0.03304 0.02616 -0.1060 0.8810 0.0336
-8.250 -0.3920 0.03129 0.02417 -0.1039 0.8771 0.0335
-8.000 -0.3811 0.03050 0.02302 -0.1013 0.8730 0.0343
-7.750 -0.3611 0.02896 0.02122 -0.1003 0.8698 0.0344
-7.500 -0.3338 0.02716 0.01920 -0.1004 0.8675 0.0344
-7.250 -0.2989 0.02507 0.01697 -0.1017 0.8659 0.0348
-7.000 -0.2628 0.02351 0.01540 -0.1033 0.8646 0.0359
-6.750 -0.2385 0.02276 0.01466 -0.1029 0.8620 0.0369
-6.500 -0.2175 0.02219 0.01409 -0.1019 0.8589 0.0386
-6.250 -0.1970 0.02171 0.01356 -0.1008 0.8558 0.0407
-6.000 -0.1785 0.02104 0.01290 -0.0995 0.8529 0.0436
-5.750 -0.1605 0.02060 0.01247 -0.0981 0.8505 0.0476
-5.500 -0.1450 0.02005 0.01191 -0.0962 0.8484 0.0529
-5.250 -0.1409 0.02004 0.01192 -0.0924 0.8442 0.0608
-5.000 -0.1435 0.01959 0.01175 -0.0875 0.8396 0.0944
-4.750 -0.1387 0.01898 0.01155 -0.0842 0.8363 0.1677
-4.500 -0.1316 0.01820 0.01128 -0.0813 0.8336 0.2735
-4.250 -0.1315 0.01734 0.01112 -0.0774 0.8306 0.4215
-4.000 -0.1516 0.01752 0.01195 -0.0695 0.8232 0.5338
-3.750 -0.1344 0.01942 0.01459 -0.0637 0.8207 0.7162
-3.500 -0.1093 0.02069 0.01572 -0.0618 0.8186 0.7573
-3.250 -0.0714 0.02237 0.01729 -0.0607 0.8174 0.7766
-3.000 -0.0347 0.02324 0.01803 -0.0608 0.8163 0.7898
-2.750 -0.0710 0.02438 0.01924 -0.0500 0.8067 0.7989
-2.500 -0.0367 0.02528 0.02004 -0.0494 0.8046 0.8092
-2.250 -0.0022 0.02581 0.02046 -0.0495 0.8030 0.8208
-2.000 0.0323 0.02616 0.02070 -0.0500 0.8015 0.8333
-1.750 0.1294 0.02688 0.02128 -0.0605 0.8029 0.8490
-1.500 0.2493 0.02653 0.02075 -0.0773 0.8052 0.8552
-1.250 0.2778 0.02651 0.02067 -0.0775 0.8029 0.8653
-1.000 0.3320 0.02624 0.02032 -0.0825 0.8018 0.8720
-0.750 0.3617 0.02606 0.02007 -0.0831 0.7999 0.8800
-0.500 0.4097 0.02572 0.01966 -0.0872 0.7987 0.8849
-0.250 0.3694 0.02692 0.02096 -0.0754 0.7884 0.8940
0.000 0.4203 0.02641 0.02040 -0.0801 0.7867 0.8973
0.250 0.4570 0.02602 0.01995 -0.0820 0.7847 0.9012
0.500 0.4778 0.02578 0.01967 -0.0808 0.7824 0.9051
0.750 0.4528 0.02666 0.02062 -0.0720 0.7716 0.9094
1.000 0.4979 0.02614 0.02007 -0.0755 0.7697 0.9118
1.250 0.5362 0.02566 0.01956 -0.0777 0.7679 0.9140
1.500 0.5695 0.02525 0.01911 -0.0789 0.7660 0.9162
1.750 0.5053 0.02641 0.02034 -0.0625 0.7531 0.9190
2.000 0.4325 0.02729 0.02126 -0.0445 0.7400 0.9222
2.250 0.4770 0.02673 0.02069 -0.0477 0.7381 0.9227
2.500 0.5241 0.02610 0.02005 -0.0514 0.7367 0.9231
2.750 0.5768 0.02542 0.01937 -0.0561 0.7356 0.9237
3.000 0.6290 0.02472 0.01866 -0.0607 0.7342 0.9245
3.250 0.5493 0.02550 0.01947 -0.0412 0.7204 0.9272
3.500 0.6046 0.02478 0.01876 -0.0463 0.7193 0.9274
3.750 0.6609 0.02402 0.01802 -0.0515 0.7181 0.9277
4.000 0.4914 0.02478 0.01875 -0.0156 0.6990 0.9338
4.250 0.5664 0.02397 0.01795 -0.0239 0.6997 0.9329
4.500 0.6561 0.02298 0.01700 -0.0350 0.7010 0.9318
4.750 0.5344 0.02418 0.01823 -0.0095 0.6786 0.9373
5.000 0.5764 0.02342 0.01750 -0.0117 0.6761 0.9375
5.250 0.6263 0.02253 0.01664 -0.0153 0.6744 0.9373
5.500 0.6832 0.02162 0.01578 -0.0202 0.6729 0.9370
5.750 0.7474 0.02072 0.01491 -0.0266 0.6711 0.9365
6.000 0.7264 0.02074 0.01501 -0.0182 0.6596 0.9387
6.250 0.7864 0.01977 0.01407 -0.0236 0.6567 0.9383
6.500 0.7827 0.01963 0.01400 -0.0183 0.6464 0.9402
6.750 0.8322 0.01872 0.01314 -0.0218 0.6413 0.9404
7.000 0.8346 0.01858 0.01307 -0.0175 0.6302 0.9428
7.250 0.8677 0.01795 0.01248 -0.0184 0.6218 0.9435
7.500 0.8908 0.01754 0.01213 -0.0177 0.6105 0.9445
7.750 0.9061 0.01738 0.01201 -0.0158 0.5964 0.9458
8.000 0.9288 0.01713 0.01179 -0.0152 0.5809 0.9469
8.250 0.9508 0.01702 0.01166 -0.0145 0.5626 0.9479
8.500 0.9671 0.01707 0.01172 -0.0129 0.5416 0.9493
8.750 0.9866 0.01714 0.01172 -0.0118 0.5195 0.9511
9.000 0.9990 0.01750 0.01203 -0.0099 0.4956 0.9531
9.250 1.0123 0.01795 0.01238 -0.0083 0.4705 0.9548
9.500 1.0206 0.01862 0.01302 -0.0062 0.4447 0.9568
9.750 1.0295 0.01939 0.01369 -0.0044 0.4198 0.9588
10.000 1.0367 0.02029 0.01452 -0.0025 0.3944 0.9608
10.250 1.0439 0.02127 0.01544 -0.0007 0.3696 0.9630
10.500 1.0501 0.02238 0.01647 0.0009 0.3453 0.9656
10.750 1.0569 0.02356 0.01762 0.0023 0.3206 0.9687
11.000 1.0620 0.02493 0.01889 0.0037 0.2958 0.9722
11.250 1.0686 0.02643 0.02032 0.0045 0.2695 0.9756
11.500 1.0758 0.02800 0.02182 0.0051 0.2439 0.9794
11.750 1.0816 0.02971 0.02342 0.0056 0.2199 0.9847
12.000 1.0868 0.03128 0.02494 0.0064 0.1963 1.0000
12.500 1.0989 0.03486 0.02839 0.0074 0.1564 1.0000
12.750 1.1060 0.03667 0.03017 0.0077 0.1395 1.0000
13.000 1.1127 0.03859 0.03205 0.0080 0.1241 1.0000
13.250 1.1191 0.04059 0.03403 0.0082 0.1100 1.0000
13.500 1.1248 0.04271 0.03613 0.0083 0.0964 1.0000
13.750 1.1290 0.04504 0.03843 0.0084 0.0830 1.0000
14.000 1.1299 0.04775 0.04109 0.0086 0.0689 1.0000
14.250 1.1298 0.05067 0.04399 0.0087 0.0551 1.0000
14.500 1.1265 0.05399 0.04728 0.0088 0.0448 1.0000
14.750 1.1228 0.05746 0.05075 0.0088 0.0397 1.0000
15.000 1.1243 0.06049 0.05385 0.0084 0.0360 1.0000
15.250 1.1207 0.06407 0.05744 0.0082 0.0337 1.0000
15.500 1.1252 0.06689 0.06039 0.0077 0.0317 1.0000
15.750 1.1293 0.06977 0.06334 0.0072 0.0302 1.0000
16.000 1.1332 0.07267 0.06630 0.0065 0.0290 1.0000
16.250 1.1379 0.07527 0.06886 0.0064 0.0278 1.0000
16.500 1.1456 0.07783 0.07157 0.0058 0.0270 1.0000
16.750 1.1516 0.08065 0.07454 0.0050 0.0258 1.0000
17.000 1.1581 0.08339 0.07737 0.0042 0.0249 1.0000
17.250 1.1648 0.08610 0.08015 0.0034 0.0241 1.0000
17.500 1.1732 0.08851 0.08261 0.0027 0.0235 1.0000
17.750 1.1869 0.09012 0.08424 0.0029 0.0229 1.0000
18.000 1.1926 0.09311 0.08739 0.0022 0.0225 1.0000
18.250 1.1936 0.09685 0.09134 0.0009 0.0223 1.0000
18.500 1.1924 0.10094 0.09566 -0.0007 0.0222 1.0000
18.750 1.1885 0.10550 0.10045 -0.0026 0.0220 1.0000
19.000 1.1831 0.11037 0.10554 -0.0047 0.0219 1.0000
19.250 1.1749 0.11580 0.11120 -0.0074 0.0219 1.0000
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