EPPLER 638 AIRFOIL (e638-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 638 AIRFOIL (e638-il) Reynolds number: 500,000 Max Cl/Cd: 99.38 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e638-il-500000.txt Download as CSV file: xf-e638-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 638 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3369 0.11770 0.11548 -0.0174 1.0000 0.0143
-10.750 -0.3327 0.11425 0.11205 -0.0189 1.0000 0.0143
-10.500 -0.3307 0.11033 0.10816 -0.0210 1.0000 0.0143
-10.250 -0.3286 0.10621 0.10407 -0.0219 1.0000 0.0144
-10.000 -0.3232 0.10309 0.10097 -0.0223 1.0000 0.0145
-9.750 -0.3135 0.10086 0.09876 -0.0213 1.0000 0.0149
-9.500 -0.3088 0.09799 0.09591 -0.0221 1.0000 0.0152
-9.250 -0.3062 0.09466 0.09262 -0.0233 1.0000 0.0153
-9.000 -0.3034 0.09152 0.08951 -0.0244 1.0000 0.0154
-8.750 -0.2581 0.08437 0.08227 -0.0388 0.9118 0.0165
-8.500 -0.2379 0.07966 0.07711 -0.0459 0.8101 0.0168
-8.250 -0.2432 0.07628 0.07356 -0.0473 0.7692 0.0174
-8.000 -0.2514 0.07278 0.06997 -0.0495 0.7411 0.0175
-7.750 -0.2641 0.06922 0.06631 -0.0507 0.7208 0.0178
-7.500 -0.2676 0.06501 0.06196 -0.0527 0.7037 0.0180
-7.250 -0.2669 0.06070 0.05747 -0.0536 0.6889 0.0181
-7.000 -0.2617 0.05717 0.05377 -0.0535 0.6747 0.0181
-6.750 -0.2552 0.05350 0.04991 -0.0529 0.6620 0.0182
-6.500 -0.2544 0.04913 0.04541 -0.0520 0.6503 0.0184
-6.250 -0.2443 0.04704 0.04324 -0.0513 0.6372 0.0188
-6.000 -0.2319 0.04454 0.04060 -0.0505 0.6255 0.0190
-5.750 -0.2181 0.04237 0.03830 -0.0496 0.6143 0.0195
-5.500 -0.2033 0.03991 0.03563 -0.0486 0.6039 0.0203
-5.250 -0.1869 0.03696 0.03245 -0.0472 0.5939 0.0216
-5.000 -0.1747 0.03185 0.02670 -0.0437 0.5867 0.0232
-4.750 -0.1567 0.03018 0.02499 -0.0431 0.5761 0.0239
-4.500 -0.1369 0.02886 0.02355 -0.0422 0.5664 0.0247
-4.000 -0.0974 0.02451 0.01848 -0.0385 0.5499 0.0297
-3.750 -0.0752 0.02349 0.01740 -0.0380 0.5412 0.0310
-3.500 -0.0517 0.02237 0.01611 -0.0370 0.5324 0.0333
-3.250 -0.0297 0.02071 0.01405 -0.0354 0.5249 0.0377
-3.000 -0.0031 0.01576 0.00832 -0.0326 0.5186 0.0239
-2.750 0.0228 0.01498 0.00742 -0.0320 0.5112 0.0247
-2.500 0.0494 0.01453 0.00692 -0.0316 0.5036 0.0267
-2.250 0.0758 0.01383 0.00607 -0.0310 0.4967 0.0274
-2.000 0.1024 0.01330 0.00545 -0.0304 0.4897 0.0283
-1.750 0.1267 0.01251 0.00457 -0.0295 0.4830 0.0297
-1.500 0.1517 0.01211 0.00417 -0.0289 0.4769 0.0318
-1.250 0.1768 0.01180 0.00381 -0.0282 0.4707 0.0333
-1.000 0.2018 0.01158 0.00351 -0.0274 0.4652 0.0349
-0.750 0.2272 0.01129 0.00320 -0.0268 0.4596 0.0370
-0.500 0.2523 0.01107 0.00295 -0.0261 0.4539 0.0404
-0.250 0.2782 0.01098 0.00279 -0.0256 0.4487 0.0441
0.000 0.3043 0.01081 0.00264 -0.0251 0.4437 0.0551
0.250 0.3068 0.00879 0.00250 -0.0207 0.4400 0.6464
0.500 0.3867 0.00878 0.00324 -0.0301 0.4332 0.9629
0.750 0.4637 0.00921 0.00353 -0.0400 0.4260 0.9799
1.000 0.5455 0.00946 0.00358 -0.0512 0.4197 0.9940
1.250 0.5945 0.00933 0.00340 -0.0557 0.4148 0.9986
1.500 0.6257 0.00932 0.00334 -0.0566 0.4106 1.0000
1.750 0.6488 0.00941 0.00334 -0.0558 0.4067 1.0000
2.000 0.6722 0.00949 0.00338 -0.0551 0.4031 1.0000
2.250 0.6958 0.00953 0.00342 -0.0543 0.3996 1.0000
2.500 0.7193 0.00959 0.00345 -0.0536 0.3961 1.0000
2.750 0.7425 0.00969 0.00350 -0.0528 0.3926 1.0000
3.000 0.7658 0.00982 0.00358 -0.0521 0.3891 1.0000
3.250 0.7895 0.00987 0.00365 -0.0513 0.3858 1.0000
3.500 0.8130 0.00994 0.00372 -0.0506 0.3825 1.0000
3.750 0.8364 0.01004 0.00380 -0.0498 0.3794 1.0000
4.000 0.8595 0.01020 0.00391 -0.0490 0.3760 1.0000
4.250 0.8829 0.01030 0.00402 -0.0483 0.3729 1.0000
4.500 0.9063 0.01038 0.00413 -0.0475 0.3697 1.0000
4.750 0.9296 0.01049 0.00425 -0.0468 0.3667 1.0000
5.000 0.9526 0.01063 0.00438 -0.0460 0.3635 1.0000
5.250 0.9753 0.01086 0.00456 -0.0451 0.3601 1.0000
5.500 0.9984 0.01095 0.00471 -0.0443 0.3573 1.0000
5.750 1.0214 0.01106 0.00488 -0.0435 0.3542 1.0000
6.000 1.0442 0.01119 0.00502 -0.0427 0.3508 1.0000
6.250 1.0666 0.01138 0.00518 -0.0418 0.3475 1.0000
6.500 1.0890 0.01159 0.00540 -0.0409 0.3442 1.0000
6.750 1.1116 0.01169 0.00559 -0.0400 0.3405 1.0000
7.000 1.1340 0.01182 0.00576 -0.0392 0.3369 1.0000
7.250 1.1560 0.01200 0.00593 -0.0382 0.3333 1.0000
7.500 1.1779 0.01223 0.00618 -0.0373 0.3295 1.0000
7.750 1.1999 0.01233 0.00637 -0.0363 0.3254 1.0000
8.000 1.2217 0.01247 0.00655 -0.0354 0.3212 1.0000
8.250 1.2428 0.01271 0.00678 -0.0343 0.3172 1.0000
8.500 1.2643 0.01287 0.00703 -0.0333 0.3132 1.0000
8.750 1.2858 0.01301 0.00724 -0.0323 0.3088 1.0000
9.000 1.3063 0.01321 0.00745 -0.0312 0.3041 1.0000
9.250 1.3268 0.01341 0.00772 -0.0301 0.2989 1.0000
9.500 1.3476 0.01356 0.00795 -0.0290 0.2936 1.0000
9.750 1.3666 0.01382 0.00821 -0.0277 0.2883 1.0000
10.000 1.3872 0.01401 0.00850 -0.0266 0.2828 1.0000
10.250 1.4061 0.01424 0.00878 -0.0253 0.2765 1.0000
10.500 1.4247 0.01451 0.00911 -0.0239 0.2703 1.0000
10.750 1.4427 0.01477 0.00943 -0.0225 0.2627 1.0000
11.000 1.4599 0.01508 0.00978 -0.0209 0.2543 1.0000
11.250 1.4742 0.01549 0.01020 -0.0190 0.2450 1.0000
11.500 1.4892 0.01587 0.01064 -0.0172 0.2347 1.0000
11.750 1.5013 0.01636 0.01114 -0.0149 0.2230 1.0000
12.000 1.5078 0.01695 0.01172 -0.0118 0.2103 1.0000
12.250 1.5095 0.01768 0.01243 -0.0080 0.1962 1.0000
12.500 1.5080 0.01870 0.01339 -0.0042 0.1801 1.0000
13.000 1.4988 0.02168 0.01630 0.0021 0.1500 1.0000
13.500 1.4857 0.02622 0.02082 0.0055 0.1260 1.0000
13.750 1.4785 0.02904 0.02366 0.0062 0.1155 1.0000
14.000 1.4713 0.03208 0.02675 0.0066 0.1073 1.0000
14.250 1.4596 0.03574 0.03043 0.0066 0.0998 1.0000
14.500 1.4495 0.03935 0.03409 0.0065 0.0927 1.0000
14.750 1.4372 0.04329 0.03808 0.0062 0.0879 1.0000
15.000 1.4257 0.04717 0.04203 0.0059 0.0820 1.0000
15.250 1.4132 0.05123 0.04615 0.0055 0.0787 1.0000
15.500 1.3991 0.05558 0.05055 0.0049 0.0732 1.0000
15.750 1.3859 0.05999 0.05501 0.0041 0.0691 1.0000
16.000 1.3725 0.06451 0.05957 0.0032 0.0652 1.0000
16.250 1.3640 0.06853 0.06367 0.0024 0.0616 1.0000
16.500 1.3523 0.07303 0.06823 0.0013 0.0584 1.0000
16.750 1.3405 0.07763 0.07287 0.0002 0.0547 1.0000
17.000 1.3326 0.08176 0.07707 -0.0009 0.0513 1.0000
17.250 1.3207 0.08654 0.08188 -0.0022 0.0479 1.0000
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Polar data table (+)
Polar graphs
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