EPPLER 1230 AIRFOIL (e1230-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 1230 AIRFOIL (e1230-il) Reynolds number: 500,000 Max Cl/Cd: 86.48 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1230-il-500000-n5.txt Download as CSV file: xf-e1230-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1230 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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.6964 0.10050 0.09711 -0.0504 1.0000 0.0095
-16.250 -0.7318 0.09013 0.08658 -0.0559 1.0000 0.0094
-16.000 -0.7625 0.08081 0.07710 -0.0609 1.0000 0.0094
-15.750 -0.7883 0.07256 0.06868 -0.0655 1.0000 0.0094
-15.500 -0.8100 0.06545 0.06142 -0.0695 1.0000 0.0094
-15.250 -0.8277 0.05946 0.05527 -0.0726 1.0000 0.0094
-15.000 -0.8426 0.05442 0.05009 -0.0749 1.0000 0.0094
-14.750 -0.8549 0.05015 0.04570 -0.0763 1.0000 0.0094
-14.500 -0.8651 0.04649 0.04192 -0.0771 1.0000 0.0094
-14.250 -0.8734 0.04333 0.03864 -0.0773 1.0000 0.0095
-14.000 -0.8802 0.04057 0.03577 -0.0770 1.0000 0.0095
-13.750 -0.8858 0.03811 0.03321 -0.0763 1.0000 0.0096
-13.500 -0.8903 0.03591 0.03091 -0.0753 1.0000 0.0096
-13.250 -0.8941 0.03392 0.02882 -0.0739 1.0000 0.0097
-13.000 -0.8979 0.03214 0.02694 -0.0722 1.0000 0.0098
-12.750 -0.9025 0.03060 0.02531 -0.0698 1.0000 0.0098
-12.500 -0.9086 0.02934 0.02396 -0.0665 1.0000 0.0099
-12.250 -0.8937 0.02799 0.02250 -0.0667 0.9977 0.0100
-12.000 -0.8712 0.02677 0.02117 -0.0679 0.9948 0.0101
-11.750 -0.8528 0.02541 0.01974 -0.0683 0.9908 0.0103
-11.500 -0.8264 0.02419 0.01845 -0.0697 0.9875 0.0105
-11.250 -0.8015 0.02318 0.01738 -0.0704 0.9832 0.0106
-11.000 -0.7734 0.02225 0.01640 -0.0715 0.9792 0.0109
-10.750 -0.7508 0.02145 0.01554 -0.0713 0.9730 0.0111
-10.500 -0.7289 0.02069 0.01473 -0.0708 0.9655 0.0113
-10.250 -0.7162 0.02005 0.01404 -0.0684 0.9503 0.0116
-10.000 -0.6947 0.01934 0.01327 -0.0676 0.9363 0.0118
-9.750 -0.6621 0.01856 0.01242 -0.0690 0.9238 0.0122
-9.500 -0.6142 0.01770 0.01146 -0.0735 0.9120 0.0126
-9.250 -0.5616 0.01670 0.01037 -0.0792 0.8912 0.0132
-9.000 -0.5237 0.01610 0.00960 -0.0815 0.8543 0.0138
-8.750 -0.4993 0.01576 0.00907 -0.0810 0.8184 0.0143
-8.500 -0.4772 0.01548 0.00861 -0.0800 0.7892 0.0149
-8.250 -0.4551 0.01521 0.00820 -0.0789 0.7639 0.0155
-8.000 -0.4335 0.01488 0.00777 -0.0778 0.7412 0.0163
-7.750 -0.4111 0.01462 0.00739 -0.0769 0.7205 0.0173
-7.500 -0.3882 0.01438 0.00703 -0.0759 0.7017 0.0184
-7.250 -0.3656 0.01409 0.00667 -0.0750 0.6843 0.0197
-7.000 -0.3425 0.01385 0.00634 -0.0741 0.6679 0.0213
-6.750 -0.3194 0.01361 0.00602 -0.0732 0.6525 0.0232
-6.250 -0.2720 0.01315 0.00544 -0.0716 0.6239 0.0297
-6.000 -0.2484 0.01292 0.00517 -0.0708 0.6112 0.0351
-5.750 -0.2247 0.01270 0.00494 -0.0700 0.5979 0.0425
-5.500 -0.2003 0.01250 0.00472 -0.0693 0.5855 0.0507
-5.250 -0.1758 0.01234 0.00453 -0.0687 0.5742 0.0589
-5.000 -0.1511 0.01218 0.00435 -0.0680 0.5623 0.0673
-4.750 -0.1263 0.01203 0.00418 -0.0674 0.5513 0.0758
-4.250 -0.0763 0.01175 0.00386 -0.0662 0.5307 0.0944
-4.000 -0.0516 0.01162 0.00372 -0.0656 0.5205 0.1066
-3.750 -0.0266 0.01145 0.00358 -0.0650 0.5108 0.1248
-3.500 -0.0023 0.01129 0.00344 -0.0644 0.5014 0.1464
-3.250 0.0228 0.01109 0.00331 -0.0638 0.4931 0.1716
-3.000 0.0472 0.01091 0.00319 -0.0632 0.4847 0.2023
-2.750 0.0716 0.01067 0.00306 -0.0626 0.4770 0.2439
-2.500 0.0953 0.01041 0.00294 -0.0618 0.4683 0.2960
-2.250 0.1186 0.01011 0.00282 -0.0611 0.4606 0.3613
-2.000 0.1415 0.00978 0.00271 -0.0602 0.4527 0.4375
-1.750 0.1645 0.00957 0.00270 -0.0592 0.4457 0.5093
-1.500 0.1903 0.00950 0.00273 -0.0587 0.4393 0.5509
-1.250 0.2165 0.00953 0.00277 -0.0583 0.4322 0.5771
-1.000 0.2430 0.00960 0.00282 -0.0579 0.4255 0.5958
-0.750 0.2703 0.00967 0.00286 -0.0576 0.4186 0.6098
-0.500 0.2970 0.00978 0.00292 -0.0573 0.4115 0.6219
-0.250 0.3241 0.00988 0.00299 -0.0570 0.4058 0.6323
0.000 0.3514 0.01000 0.00308 -0.0568 0.4000 0.6448
0.250 0.3783 0.01018 0.00316 -0.0564 0.3941 0.6572
0.500 0.4050 0.01028 0.00324 -0.0561 0.3888 0.6648
0.750 0.4324 0.01038 0.00328 -0.0560 0.3831 0.6709
1.000 0.4594 0.01045 0.00332 -0.0558 0.3772 0.6746
1.250 0.4863 0.01054 0.00336 -0.0555 0.3720 0.6775
1.500 0.5139 0.01060 0.00341 -0.0555 0.3675 0.6801
1.750 0.5411 0.01069 0.00346 -0.0553 0.3626 0.6829
2.000 0.5680 0.01080 0.00352 -0.0552 0.3579 0.6853
2.250 0.5950 0.01091 0.00358 -0.0550 0.3535 0.6876
2.500 0.6222 0.01097 0.00364 -0.0549 0.3489 0.6900
2.750 0.6490 0.01106 0.00372 -0.0547 0.3441 0.6923
3.000 0.6754 0.01118 0.00382 -0.0545 0.3398 0.6944
3.250 0.7020 0.01129 0.00391 -0.0543 0.3362 0.6968
3.500 0.7291 0.01139 0.00401 -0.0542 0.3326 0.6994
3.750 0.7557 0.01151 0.00411 -0.0540 0.3286 0.7017
4.000 0.7818 0.01165 0.00423 -0.0538 0.3245 0.7038
4.250 0.8073 0.01180 0.00436 -0.0534 0.3204 0.7059
4.500 0.8340 0.01189 0.00448 -0.0532 0.3173 0.7084
4.750 0.8603 0.01201 0.00462 -0.0530 0.3140 0.7112
5.000 0.8862 0.01215 0.00476 -0.0528 0.3107 0.7139
5.250 0.9116 0.01232 0.00492 -0.0524 0.3073 0.7163
5.500 0.9364 0.01252 0.00509 -0.0520 0.3038 0.7187
5.750 0.9624 0.01264 0.00525 -0.0518 0.3010 0.7211
6.000 0.9880 0.01277 0.00541 -0.0515 0.2979 0.7239
6.250 1.0131 0.01292 0.00560 -0.0511 0.2948 0.7274
6.500 1.0377 0.01310 0.00579 -0.0507 0.2919 0.7309
6.750 1.0617 0.01332 0.00599 -0.0502 0.2890 0.7342
7.000 1.0854 0.01352 0.00621 -0.0496 0.2863 0.7373
7.250 1.1098 0.01365 0.00641 -0.0492 0.2838 0.7410
7.500 1.1333 0.01380 0.00662 -0.0485 0.2809 0.7454
7.750 1.1561 0.01398 0.00685 -0.0478 0.2781 0.7507
8.000 1.1785 0.01417 0.00709 -0.0470 0.2755 0.7577
8.250 1.2003 0.01439 0.00737 -0.0462 0.2729 0.7670
8.500 1.2213 0.01461 0.00769 -0.0452 0.2704 0.7870
8.750 1.2405 0.01456 0.00800 -0.0435 0.2684 0.8780
9.000 1.2782 0.01478 0.00834 -0.0460 0.2654 1.0000
9.250 1.2991 0.01505 0.00864 -0.0451 0.2627 1.0000
9.500 1.3194 0.01535 0.00896 -0.0441 0.2603 1.0000
9.750 1.3389 0.01569 0.00930 -0.0430 0.2579 1.0000
10.000 1.3574 0.01607 0.00969 -0.0417 0.2552 1.0000
10.250 1.3778 0.01639 0.01005 -0.0408 0.2530 1.0000
10.500 1.3982 0.01670 0.01042 -0.0400 0.2506 1.0000
10.750 1.4177 0.01706 0.01082 -0.0390 0.2476 1.0000
11.000 1.4359 0.01747 0.01126 -0.0379 0.2443 1.0000
11.250 1.4523 0.01797 0.01176 -0.0366 0.2409 1.0000
11.500 1.4692 0.01846 0.01229 -0.0354 0.2380 1.0000
11.750 1.4880 0.01888 0.01278 -0.0345 0.2352 1.0000
12.000 1.5053 0.01938 0.01334 -0.0335 0.2320 1.0000
12.250 1.5209 0.01998 0.01397 -0.0323 0.2285 1.0000
12.500 1.5340 0.02073 0.01473 -0.0310 0.2248 1.0000
12.750 1.5497 0.02138 0.01544 -0.0300 0.2215 1.0000
13.000 1.5652 0.02207 0.01619 -0.0291 0.2178 1.0000
13.250 1.5783 0.02291 0.01709 -0.0280 0.2139 1.0000
13.500 1.5884 0.02399 0.01818 -0.0268 0.2100 1.0000
13.750 1.6015 0.02493 0.01919 -0.0260 0.2064 1.0000
14.000 1.6135 0.02598 0.02031 -0.0252 0.2019 1.0000
14.250 1.6215 0.02735 0.02172 -0.0242 0.1973 1.0000
14.500 1.6289 0.02884 0.02325 -0.0234 0.1932 1.0000
14.750 1.6383 0.03023 0.02471 -0.0227 0.1885 1.0000
15.000 1.6424 0.03211 0.02664 -0.0220 0.1833 1.0000
15.250 1.6453 0.03415 0.02873 -0.0214 0.1786 1.0000
15.500 1.6490 0.03620 0.03084 -0.0209 0.1731 1.0000
15.750 1.6453 0.03903 0.03370 -0.0205 0.1675 1.0000
16.000 1.6450 0.04157 0.03631 -0.0202 0.1618 1.0000
16.250 1.6374 0.04495 0.03973 -0.0200 0.1554 1.0000
16.500 1.6305 0.04835 0.04320 -0.0199 0.1496 1.0000
16.750 1.6189 0.05233 0.04722 -0.0200 0.1432 1.0000
17.000 1.6056 0.05663 0.05158 -0.0203 0.1376 1.0000
17.250 1.5906 0.06121 0.05621 -0.0207 0.1313 1.0000
17.500 1.5729 0.06620 0.06126 -0.0213 0.1261 1.0000
17.750 1.5558 0.07125 0.06637 -0.0221 0.1206 1.0000
18.000 1.5340 0.07698 0.07216 -0.0231 0.1159 1.0000
18.250 1.5182 0.08202 0.07727 -0.0241 0.1111 1.0000
18.500 1.4979 0.08775 0.08305 -0.0253 0.1065 1.0000
18.750 1.4806 0.09315 0.08852 -0.0266 0.1025 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 1230 AIRFOIL (e1230-il)