RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Reynolds number: 500,000 Max Cl/Cd: 79.68 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg15a111-il-500000-n5.txt Download as CSV file: xf-rg15a111-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7668 0.08309 0.08033 -0.0384 1.0000 0.0063
-13.750 -0.8106 0.07004 0.06715 -0.0461 1.0000 0.0062
-13.500 -0.8439 0.05862 0.05557 -0.0541 1.0000 0.0062
-13.250 -0.8699 0.04962 0.04636 -0.0611 1.0000 0.0061
-13.000 -0.8882 0.04365 0.04019 -0.0651 1.0000 0.0061
-12.750 -0.9006 0.03958 0.03595 -0.0668 1.0000 0.0062
-12.500 -0.9133 0.03622 0.03242 -0.0669 1.0000 0.0062
-12.250 -0.9218 0.03391 0.02994 -0.0656 1.0000 0.0063
-12.000 -0.9353 0.03201 0.02790 -0.0622 1.0000 0.0063
-11.750 -0.9411 0.03043 0.02615 -0.0588 1.0000 0.0063
-11.500 -0.9401 0.02886 0.02440 -0.0561 1.0000 0.0064
-11.250 -0.9391 0.02714 0.02253 -0.0533 1.0000 0.0066
-11.000 -0.9315 0.02588 0.02116 -0.0511 1.0000 0.0068
-10.750 -0.9207 0.02484 0.02001 -0.0491 1.0000 0.0069
-10.500 -0.9077 0.02396 0.01904 -0.0472 1.0000 0.0071
-10.250 -0.8943 0.02306 0.01803 -0.0454 1.0000 0.0073
-10.000 -0.8789 0.02236 0.01725 -0.0438 1.0000 0.0076
-9.750 -0.8557 0.02152 0.01629 -0.0437 0.9990 0.0080
-9.500 -0.8262 0.02063 0.01525 -0.0449 0.9970 0.0085
-9.250 -0.7963 0.01975 0.01422 -0.0461 0.9950 0.0090
-9.000 -0.7672 0.01885 0.01319 -0.0471 0.9929 0.0094
-8.750 -0.7397 0.01787 0.01213 -0.0478 0.9900 0.0100
-8.500 -0.7097 0.01719 0.01138 -0.0489 0.9873 0.0105
-8.250 -0.6786 0.01654 0.01065 -0.0500 0.9851 0.0112
-8.000 -0.6465 0.01591 0.00992 -0.0514 0.9833 0.0119
-7.750 -0.6195 0.01533 0.00926 -0.0515 0.9792 0.0126
-7.500 -0.5904 0.01470 0.00855 -0.0522 0.9754 0.0133
-7.250 -0.5594 0.01407 0.00790 -0.0533 0.9726 0.0145
-7.000 -0.5266 0.01356 0.00732 -0.0546 0.9704 0.0156
-6.750 -0.5009 0.01310 0.00680 -0.0543 0.9644 0.0164
-6.500 -0.4699 0.01269 0.00633 -0.0552 0.9605 0.0173
-6.250 -0.4376 0.01211 0.00571 -0.0563 0.9577 0.0190
-6.000 -0.4094 0.01170 0.00527 -0.0565 0.9516 0.0205
-5.750 -0.3776 0.01133 0.00484 -0.0575 0.9467 0.0220
-5.500 -0.3434 0.01093 0.00441 -0.0589 0.9429 0.0249
-5.250 -0.3141 0.01057 0.00407 -0.0593 0.9351 0.0295
-5.000 -0.2802 0.01019 0.00371 -0.0607 0.9293 0.0405
-4.750 -0.2497 0.00985 0.00341 -0.0613 0.9203 0.0545
-4.500 -0.2175 0.00956 0.00314 -0.0623 0.9117 0.0685
-4.250 -0.1872 0.00929 0.00290 -0.0629 0.9012 0.0854
-4.000 -0.1583 0.00902 0.00268 -0.0631 0.8894 0.1065
-3.750 -0.1299 0.00879 0.00248 -0.0633 0.8771 0.1286
-3.500 -0.1021 0.00858 0.00230 -0.0633 0.8641 0.1528
-3.250 -0.0750 0.00835 0.00214 -0.0632 0.8504 0.1853
-3.000 -0.0485 0.00811 0.00198 -0.0630 0.8364 0.2262
-2.750 -0.0223 0.00787 0.00185 -0.0627 0.8220 0.2724
-2.500 0.0039 0.00765 0.00173 -0.0624 0.8078 0.3195
-2.250 0.0300 0.00745 0.00162 -0.0621 0.7933 0.3663
-2.000 0.0556 0.00720 0.00152 -0.0617 0.7788 0.4293
-1.750 0.0810 0.00695 0.00145 -0.0613 0.7640 0.4983
-1.500 0.1065 0.00678 0.00142 -0.0608 0.7489 0.5603
-1.250 0.1326 0.00672 0.00142 -0.0603 0.7334 0.6050
-1.000 0.1591 0.00672 0.00142 -0.0599 0.7175 0.6342
-0.750 0.1856 0.00674 0.00143 -0.0595 0.7014 0.6567
-0.500 0.2123 0.00678 0.00143 -0.0591 0.6851 0.6750
-0.250 0.2389 0.00683 0.00144 -0.0587 0.6686 0.6904
0.000 0.2655 0.00689 0.00146 -0.0583 0.6518 0.7039
0.250 0.2919 0.00696 0.00148 -0.0579 0.6346 0.7163
0.500 0.3185 0.00703 0.00152 -0.0576 0.6169 0.7276
0.750 0.3450 0.00711 0.00155 -0.0572 0.5982 0.7384
1.000 0.3712 0.00721 0.00160 -0.0568 0.5788 0.7496
1.250 0.3973 0.00731 0.00165 -0.0563 0.5594 0.7603
1.500 0.4234 0.00741 0.00172 -0.0559 0.5389 0.7707
1.750 0.4492 0.00754 0.00179 -0.0554 0.5178 0.7815
2.000 0.4751 0.00767 0.00187 -0.0550 0.4969 0.7922
2.250 0.5007 0.00780 0.00197 -0.0545 0.4761 0.8024
2.500 0.5262 0.00795 0.00207 -0.0540 0.4551 0.8134
3.250 0.6024 0.00842 0.00243 -0.0524 0.3931 0.8438
3.750 0.6518 0.00880 0.00272 -0.0511 0.3484 0.8661
4.000 0.6757 0.00902 0.00288 -0.0503 0.3246 0.8791
4.250 0.6995 0.00921 0.00305 -0.0495 0.3034 0.8936
4.750 0.7468 0.00962 0.00341 -0.0478 0.2638 0.9330
5.000 0.7764 0.00985 0.00362 -0.0482 0.2453 0.9586
5.250 0.8103 0.01017 0.00386 -0.0498 0.2238 0.9959
5.500 0.8351 0.01049 0.00410 -0.0494 0.2034 1.0000
5.750 0.8588 0.01087 0.00438 -0.0488 0.1811 1.0000
6.000 0.8822 0.01128 0.00467 -0.0482 0.1572 1.0000
6.250 0.9058 0.01166 0.00499 -0.0476 0.1396 1.0000
6.500 0.9297 0.01202 0.00530 -0.0470 0.1255 1.0000
6.750 0.9532 0.01241 0.00563 -0.0464 0.1116 1.0000
7.000 0.9765 0.01281 0.00598 -0.0458 0.0983 1.0000
7.250 0.9995 0.01323 0.00636 -0.0451 0.0867 1.0000
7.500 1.0225 0.01363 0.00675 -0.0444 0.0771 1.0000
7.750 1.0453 0.01404 0.00715 -0.0437 0.0684 1.0000
8.000 1.0676 0.01449 0.00758 -0.0429 0.0602 1.0000
8.250 1.0895 0.01496 0.00803 -0.0420 0.0529 1.0000
8.500 1.1114 0.01540 0.00850 -0.0412 0.0468 1.0000
8.750 1.1320 0.01594 0.00901 -0.0402 0.0400 1.0000
9.000 1.1525 0.01646 0.00953 -0.0391 0.0344 1.0000
9.250 1.1725 0.01700 0.01008 -0.0381 0.0300 1.0000
9.500 1.1923 0.01753 0.01063 -0.0369 0.0269 1.0000
9.750 1.2107 0.01816 0.01127 -0.0356 0.0240 1.0000
10.000 1.2302 0.01864 0.01184 -0.0344 0.0226 1.0000
10.250 1.2483 0.01920 0.01244 -0.0331 0.0208 1.0000
10.500 1.2633 0.01984 0.01310 -0.0313 0.0187 1.0000
10.750 1.2782 0.02044 0.01376 -0.0294 0.0170 1.0000
11.000 1.2928 0.02104 0.01443 -0.0275 0.0156 1.0000
11.250 1.3056 0.02176 0.01517 -0.0255 0.0139 1.0000
11.500 1.3180 0.02250 0.01598 -0.0235 0.0126 1.0000
11.750 1.3300 0.02329 0.01684 -0.0216 0.0112 1.0000
12.000 1.3398 0.02422 0.01782 -0.0195 0.0100 1.0000
12.250 1.3496 0.02517 0.01885 -0.0175 0.0089 1.0000
12.500 1.3579 0.02624 0.01999 -0.0156 0.0079 1.0000
12.750 1.3644 0.02748 0.02131 -0.0136 0.0072 1.0000
13.000 1.3702 0.02884 0.02276 -0.0117 0.0067 1.0000
13.250 1.3755 0.03028 0.02430 -0.0101 0.0063 1.0000
13.500 1.3799 0.03187 0.02600 -0.0086 0.0059 1.0000
13.750 1.3830 0.03366 0.02790 -0.0073 0.0056 1.0000
14.000 1.3839 0.03576 0.03009 -0.0062 0.0053 1.0000
14.250 1.3843 0.03802 0.03248 -0.0054 0.0051 1.0000
14.500 1.3802 0.04090 0.03548 -0.0049 0.0048 1.0000
14.750 1.3784 0.04372 0.03843 -0.0047 0.0047 1.0000
15.000 1.3762 0.04673 0.04158 -0.0049 0.0046 1.0000
15.250 1.3708 0.05032 0.04531 -0.0055 0.0045 1.0000
15.500 1.3660 0.05404 0.04916 -0.0064 0.0044 1.0000
15.750 1.3591 0.05823 0.05349 -0.0078 0.0043 1.0000
16.000 1.3502 0.06296 0.05837 -0.0095 0.0041 1.0000
16.250 1.3391 0.06827 0.06382 -0.0118 0.0041 1.0000
16.500 1.3265 0.07407 0.06977 -0.0145 0.0041 1.0000
16.750 1.3125 0.08037 0.07622 -0.0176 0.0041 1.0000
17.000 1.2967 0.08724 0.08324 -0.0212 0.0040 1.0000
17.250 1.2775 0.09501 0.09117 -0.0253 0.0040 1.0000
17.500 1.2597 0.10273 0.09904 -0.0295 0.0039 1.0000
17.750 1.2393 0.11121 0.10766 -0.0342 0.0040 1.0000
18.000 1.2205 0.11960 0.11619 -0.0389 0.0040 1.0000
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