RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Reynolds number: 100,000 Max Cl/Cd: 49.45 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg15a111-il-100000-n5.txt Download as CSV file: xf-rg15a111-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 15A-1.8/11.0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5178 0.08836 0.08321 -0.0375 1.0000 0.0272
-10.250 -0.5343 0.08020 0.07513 -0.0419 1.0000 0.0268
-10.000 -0.5756 0.06607 0.06098 -0.0523 1.0000 0.0257
-9.750 -0.6151 0.05864 0.05343 -0.0564 1.0000 0.0251
-9.500 -0.6473 0.05438 0.04901 -0.0550 1.0000 0.0248
-9.250 -0.6666 0.05041 0.04480 -0.0533 1.0000 0.0247
-9.000 -0.6776 0.04681 0.04093 -0.0512 1.0000 0.0248
-8.750 -0.6814 0.04364 0.03747 -0.0491 1.0000 0.0252
-8.500 -0.6811 0.04063 0.03413 -0.0470 1.0000 0.0255
-8.250 -0.6766 0.03786 0.03102 -0.0449 1.0000 0.0262
-8.000 -0.6688 0.03534 0.02815 -0.0429 1.0000 0.0270
-7.750 -0.6579 0.03315 0.02558 -0.0410 1.0000 0.0285
-7.500 -0.6446 0.03119 0.02315 -0.0392 1.0000 0.0301
-7.250 -0.6305 0.02925 0.02109 -0.0377 1.0000 0.0314
-7.000 -0.6143 0.02777 0.01948 -0.0361 1.0000 0.0327
-6.500 -0.5793 0.02531 0.01666 -0.0332 1.0000 0.0368
-6.250 -0.5606 0.02427 0.01539 -0.0317 1.0000 0.0394
-6.000 -0.5433 0.02304 0.01416 -0.0304 1.0000 0.0418
-5.750 -0.5249 0.02212 0.01318 -0.0290 1.0000 0.0445
-5.500 -0.5059 0.02128 0.01222 -0.0277 1.0000 0.0484
-5.250 -0.4793 0.02043 0.01135 -0.0281 0.9975 0.0552
-5.000 -0.4452 0.01955 0.01042 -0.0298 0.9925 0.0660
-4.750 -0.4115 0.01876 0.00963 -0.0315 0.9868 0.0834
-4.500 -0.3768 0.01813 0.00908 -0.0334 0.9815 0.1097
-4.250 -0.3442 0.01753 0.00864 -0.0349 0.9748 0.1485
-4.000 -0.3096 0.01694 0.00824 -0.0369 0.9692 0.1946
-3.750 -0.2783 0.01638 0.00785 -0.0380 0.9615 0.2456
-3.500 -0.2437 0.01580 0.00753 -0.0398 0.9557 0.3121
-3.250 -0.2138 0.01524 0.00724 -0.0405 0.9475 0.3903
-3.000 -0.1811 0.01469 0.00712 -0.0416 0.9412 0.4900
-2.750 -0.1525 0.01440 0.00717 -0.0413 0.9327 0.5837
-2.500 -0.1199 0.01430 0.00714 -0.0418 0.9256 0.6497
-2.250 -0.0882 0.01424 0.00708 -0.0420 0.9175 0.6930
-2.000 -0.0564 0.01419 0.00702 -0.0422 0.9096 0.7263
-1.750 -0.0238 0.01413 0.00691 -0.0426 0.9018 0.7544
-1.500 0.0055 0.01408 0.00683 -0.0423 0.8921 0.7789
-1.250 0.0395 0.01399 0.00670 -0.0428 0.8850 0.8002
-1.000 0.0669 0.01393 0.00660 -0.0422 0.8738 0.8198
-0.750 0.0963 0.01385 0.00649 -0.0419 0.8633 0.8385
-0.500 0.1286 0.01374 0.00635 -0.0421 0.8540 0.8556
-0.250 0.1585 0.01366 0.00623 -0.0419 0.8425 0.8720
0.000 0.1886 0.01358 0.00613 -0.0418 0.8301 0.8880
0.250 0.2211 0.01351 0.00602 -0.0422 0.8177 0.9032
0.500 0.2559 0.01343 0.00590 -0.0431 0.8048 0.9170
0.750 0.2921 0.01336 0.00579 -0.0445 0.7909 0.9299
1.000 0.3293 0.01331 0.00570 -0.0461 0.7760 0.9422
1.250 0.3688 0.01327 0.00562 -0.0482 0.7600 0.9525
1.500 0.4080 0.01323 0.00554 -0.0504 0.7429 0.9624
1.750 0.4463 0.01322 0.00548 -0.0524 0.7251 0.9725
2.000 0.4842 0.01322 0.00544 -0.0544 0.7059 0.9830
2.250 0.5223 0.01325 0.00542 -0.0566 0.6850 0.9934
2.500 0.5503 0.01331 0.00543 -0.0568 0.6650 1.0000
2.750 0.5682 0.01342 0.00548 -0.0550 0.6449 1.0000
3.000 0.5877 0.01355 0.00555 -0.0534 0.6243 1.0000
3.250 0.6089 0.01372 0.00565 -0.0521 0.6033 1.0000
3.500 0.6307 0.01391 0.00578 -0.0510 0.5810 1.0000
3.750 0.6532 0.01413 0.00592 -0.0499 0.5587 1.0000
4.000 0.6759 0.01437 0.00610 -0.0489 0.5355 1.0000
4.250 0.6987 0.01464 0.00632 -0.0479 0.5118 1.0000
4.500 0.7214 0.01494 0.00654 -0.0469 0.4881 1.0000
4.750 0.7440 0.01525 0.00681 -0.0460 0.4634 1.0000
5.000 0.7664 0.01560 0.00710 -0.0450 0.4387 1.0000
5.250 0.7884 0.01599 0.00743 -0.0439 0.4138 1.0000
5.500 0.8103 0.01639 0.00778 -0.0429 0.3879 1.0000
5.750 0.8318 0.01682 0.00816 -0.0419 0.3617 1.0000
6.000 0.8531 0.01729 0.00858 -0.0408 0.3363 1.0000
6.250 0.8738 0.01781 0.00902 -0.0397 0.3114 1.0000
6.500 0.8947 0.01833 0.00955 -0.0386 0.2866 1.0000
6.750 0.9150 0.01890 0.01008 -0.0375 0.2627 1.0000
7.000 0.9346 0.01953 0.01066 -0.0363 0.2399 1.0000
7.250 0.9543 0.02017 0.01129 -0.0352 0.2168 1.0000
7.500 0.9727 0.02090 0.01196 -0.0339 0.1947 1.0000
7.750 0.9910 0.02165 0.01271 -0.0327 0.1732 1.0000
8.000 1.0081 0.02248 0.01348 -0.0313 0.1539 1.0000
8.250 1.0255 0.02331 0.01432 -0.0300 0.1366 1.0000
8.500 1.0420 0.02420 0.01522 -0.0285 0.1218 1.0000
8.750 1.0575 0.02515 0.01618 -0.0270 0.1088 1.0000
9.000 1.0717 0.02617 0.01723 -0.0253 0.0978 1.0000
9.250 1.0848 0.02723 0.01834 -0.0235 0.0887 1.0000
9.500 1.0977 0.02831 0.01952 -0.0217 0.0803 1.0000
9.750 1.1062 0.02953 0.02073 -0.0194 0.0738 1.0000
10.000 1.1171 0.03070 0.02205 -0.0173 0.0677 1.0000
10.250 1.1238 0.03209 0.02345 -0.0151 0.0632 1.0000
10.500 1.1333 0.03348 0.02499 -0.0131 0.0587 1.0000
10.750 1.1411 0.03488 0.02651 -0.0112 0.0544 1.0000
11.000 1.1457 0.03659 0.02827 -0.0093 0.0516 1.0000
11.250 1.1534 0.03831 0.03019 -0.0077 0.0486 1.0000
11.500 1.1594 0.04006 0.03211 -0.0062 0.0454 1.0000
11.750 1.1626 0.04190 0.03405 -0.0048 0.0427 1.0000
12.000 1.1641 0.04418 0.03634 -0.0036 0.0406 1.0000
12.250 1.1673 0.04645 0.03892 -0.0025 0.0382 1.0000
12.500 1.1679 0.04890 0.04157 -0.0018 0.0360 1.0000
12.750 1.1665 0.05147 0.04427 -0.0014 0.0340 1.0000
13.000 1.1635 0.05438 0.04724 -0.0013 0.0325 1.0000
13.250 1.1596 0.05780 0.05082 -0.0014 0.0311 1.0000
13.500 1.1536 0.06161 0.05493 -0.0020 0.0297 1.0000
13.750 1.1463 0.06575 0.05931 -0.0030 0.0285 1.0000
14.000 1.1372 0.07028 0.06404 -0.0046 0.0274 1.0000
14.250 1.1275 0.07516 0.06915 -0.0065 0.0268 1.0000
14.500 1.1165 0.08042 0.07457 -0.0089 0.0261 1.0000
14.750 1.1050 0.08603 0.08032 -0.0117 0.0255 1.0000
15.000 1.0927 0.09208 0.08652 -0.0149 0.0251 1.0000
15.250 1.0788 0.09873 0.09332 -0.0186 0.0248 1.0000
15.500 1.0630 0.10616 0.10091 -0.0230 0.0246 1.0000
15.750 1.0345 0.11719 0.11219 -0.0298 0.0250 1.0000
16.000 0.9259 0.15313 0.14848 -0.0511 0.0297 1.0000
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