RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG-15 8.9% (rg15-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.52 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg15-il-1000000.txt Download as CSV file: xf-rg15-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RG-15 8.9%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5749 0.05818 0.05667 -0.0419 1.0000 0.0067
-8.250 -0.6022 0.04949 0.04782 -0.0438 1.0000 0.0064
-8.000 -0.6363 0.03823 0.03617 -0.0426 1.0000 0.0062
-7.750 -0.6499 0.02734 0.02447 -0.0420 0.9990 0.0061
-7.500 -0.6263 0.02183 0.01830 -0.0441 0.9967 0.0062
-7.250 -0.5966 0.01915 0.01524 -0.0457 0.9952 0.0063
-7.000 -0.5657 0.01709 0.01286 -0.0471 0.9939 0.0065
-6.750 -0.5368 0.01545 0.01099 -0.0479 0.9917 0.0066
-6.500 -0.5041 0.01508 0.01054 -0.0491 0.9896 0.0069
-6.250 -0.4755 0.01256 0.00767 -0.0499 0.9875 0.0074
-6.000 -0.4428 0.01159 0.00660 -0.0513 0.9859 0.0081
-5.750 -0.4082 0.01114 0.00612 -0.0529 0.9845 0.0091
-5.500 -0.3728 0.01074 0.00567 -0.0546 0.9834 0.0103
-5.250 -0.3416 0.01044 0.00534 -0.0553 0.9806 0.0110
-5.000 -0.3120 0.00947 0.00426 -0.0559 0.9768 0.0136
-4.750 -0.2779 0.00919 0.00397 -0.0573 0.9744 0.0159
-4.500 -0.2431 0.00877 0.00350 -0.0589 0.9725 0.0185
-4.250 -0.2074 0.00836 0.00308 -0.0607 0.9710 0.0213
-4.000 -0.1752 0.00807 0.00275 -0.0616 0.9676 0.0232
-3.750 -0.1453 0.00782 0.00247 -0.0620 0.9620 0.0251
-3.500 -0.1123 0.00737 0.00208 -0.0630 0.9580 0.0417
-3.250 -0.0830 0.00696 0.00183 -0.0635 0.9508 0.0844
-3.000 -0.0508 0.00661 0.00162 -0.0645 0.9442 0.1273
-2.750 -0.0211 0.00628 0.00145 -0.0650 0.9342 0.1779
-2.500 0.0084 0.00593 0.00128 -0.0654 0.9230 0.2425
-2.250 0.0367 0.00561 0.00115 -0.0656 0.9098 0.3156
-2.000 0.0637 0.00524 0.00103 -0.0656 0.8949 0.4103
-1.750 0.0889 0.00470 0.00095 -0.0653 0.8788 0.5683
-1.500 0.1153 0.00456 0.00093 -0.0649 0.8620 0.6369
-1.250 0.1422 0.00455 0.00090 -0.0645 0.8446 0.6638
-1.000 0.1689 0.00455 0.00089 -0.0641 0.8260 0.6920
-0.750 0.1955 0.00457 0.00088 -0.0637 0.8067 0.7141
-0.500 0.2222 0.00462 0.00088 -0.0633 0.7870 0.7296
-0.250 0.2488 0.00466 0.00088 -0.0629 0.7665 0.7437
0.000 0.2753 0.00473 0.00089 -0.0625 0.7459 0.7574
0.250 0.3019 0.00479 0.00090 -0.0621 0.7240 0.7706
0.500 0.3283 0.00486 0.00093 -0.0617 0.7023 0.7835
0.750 0.3546 0.00494 0.00096 -0.0613 0.6794 0.7959
1.000 0.3810 0.00503 0.00100 -0.0609 0.6561 0.8085
1.250 0.4071 0.00512 0.00104 -0.0605 0.6321 0.8216
1.500 0.4330 0.00523 0.00109 -0.0600 0.6066 0.8358
1.750 0.4588 0.00533 0.00115 -0.0595 0.5812 0.8507
2.000 0.4844 0.00543 0.00123 -0.0589 0.5558 0.8671
2.250 0.5094 0.00555 0.00130 -0.0583 0.5295 0.8860
2.500 0.5334 0.00565 0.00138 -0.0573 0.5033 0.9067
2.750 0.5566 0.00577 0.00147 -0.0562 0.4756 0.9301
3.000 0.5807 0.00591 0.00156 -0.0553 0.4456 0.9580
3.250 0.6145 0.00608 0.00165 -0.0567 0.4168 0.9848
3.500 0.6454 0.00632 0.00176 -0.0576 0.3851 1.0000
3.750 0.6715 0.00655 0.00189 -0.0573 0.3581 1.0000
4.000 0.6970 0.00684 0.00204 -0.0570 0.3248 1.0000
4.250 0.7224 0.00715 0.00222 -0.0566 0.2905 1.0000
4.500 0.7477 0.00746 0.00241 -0.0563 0.2591 1.0000
4.750 0.7727 0.00782 0.00262 -0.0559 0.2239 1.0000
5.000 0.7973 0.00823 0.00286 -0.0554 0.1877 1.0000
5.250 0.8218 0.00865 0.00312 -0.0550 0.1528 1.0000
5.500 0.8463 0.00906 0.00341 -0.0545 0.1242 1.0000
5.750 0.8712 0.00943 0.00369 -0.0541 0.1024 1.0000
6.000 0.8955 0.00987 0.00400 -0.0536 0.0794 1.0000
6.250 0.9199 0.01030 0.00434 -0.0531 0.0606 1.0000
6.500 0.9442 0.01073 0.00469 -0.0526 0.0453 1.0000
6.750 0.9686 0.01114 0.00506 -0.0521 0.0338 1.0000
7.000 0.9928 0.01157 0.00545 -0.0516 0.0238 1.0000
7.250 1.0146 0.01230 0.00606 -0.0507 0.0103 1.0000
7.500 1.0375 0.01290 0.00671 -0.0499 0.0077 1.0000
7.750 1.0614 0.01336 0.00723 -0.0492 0.0071 1.0000
8.000 1.0846 0.01390 0.00784 -0.0485 0.0065 1.0000
8.250 1.1071 0.01449 0.00850 -0.0476 0.0061 1.0000
8.500 1.1289 0.01515 0.00924 -0.0467 0.0055 1.0000
8.750 1.1484 0.01606 0.01026 -0.0454 0.0050 1.0000
9.000 1.1651 0.01725 0.01160 -0.0437 0.0047 1.0000
9.250 1.1787 0.01876 0.01328 -0.0415 0.0045 1.0000
9.500 1.1941 0.02001 0.01467 -0.0397 0.0044 1.0000
9.750 1.2113 0.02101 0.01578 -0.0383 0.0044 1.0000
10.000 1.2282 0.02199 0.01687 -0.0368 0.0043 1.0000
10.250 1.2445 0.02298 0.01797 -0.0352 0.0042 1.0000
10.500 1.2581 0.02418 0.01932 -0.0334 0.0041 1.0000
10.750 1.2704 0.02542 0.02070 -0.0314 0.0040 1.0000
11.000 1.2787 0.02682 0.02224 -0.0288 0.0039 1.0000
11.250 1.2828 0.02826 0.02383 -0.0256 0.0038 1.0000
11.500 1.2852 0.02978 0.02550 -0.0225 0.0037 1.0000
11.750 1.2844 0.03161 0.02750 -0.0193 0.0036 1.0000
12.000 1.2795 0.03387 0.02995 -0.0163 0.0036 1.0000
12.250 1.2781 0.03580 0.03202 -0.0140 0.0034 1.0000
12.500 1.2708 0.03849 0.03489 -0.0120 0.0034 1.0000
12.750 1.2591 0.04194 0.03854 -0.0106 0.0034 1.0000
13.000 1.2504 0.04528 0.04204 -0.0101 0.0033 1.0000
13.250 1.2350 0.04990 0.04686 -0.0106 0.0033 1.0000
13.500 1.2188 0.05518 0.05233 -0.0121 0.0034 1.0000
13.750 1.2033 0.06092 0.05823 -0.0147 0.0033 1.0000
14.000 1.1810 0.06849 0.06600 -0.0187 0.0034 1.0000
14.250 1.1649 0.07562 0.07328 -0.0231 0.0033 1.0000
14.500 1.1416 0.08479 0.08263 -0.0287 0.0035 1.0000
14.750 1.1219 0.09390 0.09188 -0.0345 0.0035 1.0000
15.000 1.0990 0.10432 0.10243 -0.0410 0.0035 1.0000
15.250 1.0749 0.11558 0.11382 -0.0478 0.0036 1.0000
15.500 1.0498 0.12775 0.12611 -0.0550 0.0037 1.0000
15.750 1.0177 0.14269 0.14117 -0.0634 0.0038 1.0000
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Polar data table (+)
Polar graphs
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