RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Reynolds number: 50,000 Max Cl/Cd: 34.6 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg15a213-il-50000-n5.txt Download as CSV file: xf-rg15a213-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 15A 2.5/13.0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4501 0.10144 0.09393 -0.0462 1.0000 0.0558
-10.750 -0.4589 0.09585 0.08842 -0.0483 1.0000 0.0556
-10.500 -0.4715 0.08945 0.08211 -0.0511 1.0000 0.0554
-10.250 -0.4893 0.08222 0.07494 -0.0547 1.0000 0.0550
-10.000 -0.5131 0.07539 0.06817 -0.0584 1.0000 0.0544
-9.750 -0.5423 0.06980 0.06261 -0.0604 1.0000 0.0539
-9.500 -0.5734 0.06581 0.05863 -0.0596 1.0000 0.0535
-9.250 -0.5995 0.06212 0.05486 -0.0579 1.0000 0.0532
-9.000 -0.6201 0.05842 0.05101 -0.0559 1.0000 0.0532
-8.750 -0.6348 0.05490 0.04726 -0.0537 1.0000 0.0535
-8.500 -0.6444 0.05147 0.04352 -0.0515 1.0000 0.0543
-8.250 -0.6497 0.04807 0.03969 -0.0493 1.0000 0.0556
-8.000 -0.6489 0.04500 0.03620 -0.0473 1.0000 0.0571
-7.750 -0.6391 0.04339 0.03458 -0.0456 1.0000 0.0592
-7.500 -0.6295 0.04138 0.03235 -0.0439 1.0000 0.0612
-7.250 -0.6183 0.03913 0.02979 -0.0422 1.0000 0.0635
-7.000 -0.6048 0.03694 0.02719 -0.0406 1.0000 0.0662
-6.750 -0.5902 0.03533 0.02545 -0.0392 1.0000 0.0698
-6.500 -0.5749 0.03408 0.02410 -0.0377 1.0000 0.0750
-6.250 -0.5577 0.03253 0.02227 -0.0363 1.0000 0.0808
-6.000 -0.5411 0.03137 0.02111 -0.0349 1.0000 0.0873
-5.750 -0.5237 0.03025 0.01989 -0.0335 1.0000 0.0971
-5.500 -0.5063 0.02931 0.01888 -0.0323 1.0000 0.1097
-5.250 -0.4891 0.02858 0.01817 -0.0312 1.0000 0.1253
-5.000 -0.4718 0.02798 0.01759 -0.0302 1.0000 0.1452
-4.750 -0.4374 0.02727 0.01685 -0.0322 0.9938 0.1702
-4.500 -0.4032 0.02657 0.01612 -0.0340 0.9866 0.1972
-4.250 -0.3691 0.02591 0.01553 -0.0359 0.9794 0.2285
-4.000 -0.3344 0.02526 0.01504 -0.0380 0.9721 0.2683
-3.750 -0.3031 0.02461 0.01458 -0.0394 0.9636 0.3180
-3.500 -0.2699 0.02402 0.01429 -0.0410 0.9561 0.3856
-3.250 -0.2411 0.02354 0.01420 -0.0413 0.9471 0.4646
-3.000 -0.2146 0.02342 0.01447 -0.0404 0.9378 0.5501
-2.750 -0.1841 0.02360 0.01478 -0.0400 0.9295 0.6322
-2.500 -0.1600 0.02378 0.01490 -0.0386 0.9187 0.6890
-2.250 -0.1335 0.02396 0.01503 -0.0373 0.9093 0.7325
-2.000 -0.1047 0.02408 0.01505 -0.0366 0.9002 0.7692
-1.750 -0.0814 0.02416 0.01505 -0.0349 0.8894 0.7997
-1.500 -0.0503 0.02420 0.01499 -0.0345 0.8812 0.8294
-1.250 -0.0226 0.02421 0.01491 -0.0337 0.8708 0.8568
-1.000 0.0097 0.02421 0.01482 -0.0338 0.8613 0.8836
-0.750 0.0559 0.02418 0.01466 -0.0365 0.8539 0.9085
-0.500 0.1038 0.02419 0.01455 -0.0400 0.8449 0.9306
-0.250 0.1665 0.02408 0.01431 -0.0463 0.8385 0.9482
0.000 0.2233 0.02400 0.01411 -0.0519 0.8292 0.9634
0.250 0.2855 0.02373 0.01373 -0.0584 0.8218 0.9752
0.500 0.3351 0.02356 0.01350 -0.0629 0.8101 0.9883
0.750 0.3835 0.02333 0.01321 -0.0671 0.7993 1.0000
1.000 0.4103 0.02310 0.01292 -0.0671 0.7876 1.0000
1.250 0.4306 0.02297 0.01275 -0.0659 0.7742 1.0000
1.500 0.4469 0.02294 0.01268 -0.0641 0.7599 1.0000
1.750 0.4636 0.02293 0.01263 -0.0623 0.7459 1.0000
2.000 0.4822 0.02293 0.01258 -0.0608 0.7320 1.0000
2.250 0.5038 0.02294 0.01254 -0.0597 0.7184 1.0000
2.500 0.5286 0.02294 0.01251 -0.0591 0.7051 1.0000
2.750 0.5558 0.02294 0.01245 -0.0588 0.6919 1.0000
3.000 0.5847 0.02293 0.01239 -0.0587 0.6787 1.0000
3.250 0.6092 0.02305 0.01251 -0.0581 0.6639 1.0000
3.500 0.6341 0.02320 0.01263 -0.0574 0.6489 1.0000
3.750 0.6593 0.02336 0.01277 -0.0568 0.6337 1.0000
4.000 0.6847 0.02354 0.01295 -0.0563 0.6183 1.0000
4.250 0.7101 0.02374 0.01314 -0.0557 0.6027 1.0000
4.500 0.7353 0.02396 0.01335 -0.0550 0.5869 1.0000
4.750 0.7603 0.02420 0.01360 -0.0544 0.5709 1.0000
5.000 0.7850 0.02446 0.01386 -0.0537 0.5547 1.0000
5.250 0.8096 0.02475 0.01414 -0.0530 0.5384 1.0000
5.500 0.8338 0.02506 0.01445 -0.0522 0.5219 1.0000
5.750 0.8567 0.02542 0.01484 -0.0513 0.5051 1.0000
6.000 0.8783 0.02585 0.01529 -0.0502 0.4879 1.0000
6.250 0.8997 0.02629 0.01576 -0.0491 0.4709 1.0000
6.500 0.9207 0.02676 0.01628 -0.0479 0.4536 1.0000
6.750 0.9413 0.02727 0.01681 -0.0468 0.4366 1.0000
7.000 0.9614 0.02779 0.01737 -0.0455 0.4195 1.0000
7.250 0.9810 0.02836 0.01795 -0.0442 0.4025 1.0000
7.500 0.9999 0.02895 0.01860 -0.0429 0.3857 1.0000
7.750 1.0181 0.02959 0.01926 -0.0415 0.3691 1.0000
8.000 1.0354 0.03027 0.01996 -0.0400 0.3527 1.0000
8.250 1.0517 0.03099 0.02071 -0.0384 0.3364 1.0000
8.500 1.0670 0.03177 0.02153 -0.0367 0.3205 1.0000
8.750 1.0811 0.03260 0.02240 -0.0349 0.3050 1.0000
9.000 1.0939 0.03350 0.02335 -0.0330 0.2899 1.0000
9.250 1.1047 0.03446 0.02436 -0.0309 0.2755 1.0000
9.750 1.1240 0.03663 0.02668 -0.0267 0.2484 1.0000
10.000 1.1335 0.03783 0.02794 -0.0248 0.2359 1.0000
10.250 1.1424 0.03908 0.02922 -0.0229 0.2240 1.0000
10.500 1.1525 0.04032 0.03045 -0.0212 0.2129 1.0000
10.750 1.1571 0.04194 0.03224 -0.0192 0.2017 1.0000
11.000 1.1621 0.04360 0.03401 -0.0175 0.1913 1.0000
11.250 1.1693 0.04515 0.03556 -0.0160 0.1818 1.0000
11.500 1.1712 0.04710 0.03765 -0.0144 0.1722 1.0000
11.750 1.1722 0.04921 0.03987 -0.0131 0.1633 1.0000
12.000 1.1764 0.05100 0.04163 -0.0119 0.1550 1.0000
12.250 1.1719 0.05382 0.04469 -0.0109 0.1471 1.0000
12.500 1.1747 0.05589 0.04670 -0.0101 0.1399 1.0000
12.750 1.1682 0.05923 0.05032 -0.0097 0.1332 1.0000
13.000 1.1726 0.06130 0.05234 -0.0092 0.1269 1.0000
13.250 1.1624 0.06545 0.05681 -0.0094 0.1216 1.0000
13.500 1.1595 0.06873 0.06020 -0.0096 0.1164 1.0000
13.750 1.1590 0.07185 0.06337 -0.0097 0.1117 1.0000
14.000 1.1442 0.07718 0.06901 -0.0111 0.1081 1.0000
14.250 1.1342 0.08199 0.07399 -0.0125 0.1045 1.0000
14.500 1.1459 0.08352 0.07541 -0.0121 0.1001 1.0000
14.750 1.1194 0.09132 0.08356 -0.0154 0.0984 1.0000
15.000 1.0854 0.10115 0.09369 -0.0203 0.0973 1.0000
15.250 1.0303 0.11649 0.10929 -0.0291 0.0969 1.0000
|
Polar data table (+)
Polar graphs
<< Back to RG 15A 2.5/13.0 AIRFOIL (rg15a213-il)