RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG-15 8.9% (rg15-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.69 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg15-il-1000000-n5.txt Download as CSV file: xf-rg15-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.8583 0.03412 0.03188 -0.0532 1.0000 0.0028
-10.500 -0.8622 0.03065 0.02812 -0.0514 1.0000 0.0028
-10.250 -0.8610 0.02756 0.02474 -0.0495 1.0000 0.0028
-10.000 -0.8528 0.02530 0.02222 -0.0478 1.0000 0.0029
-9.750 -0.8373 0.02345 0.02013 -0.0470 0.9997 0.0030
-9.500 -0.8121 0.02139 0.01778 -0.0482 0.9983 0.0031
-9.250 -0.7855 0.01965 0.01579 -0.0493 0.9968 0.0032
-9.000 -0.7572 0.01838 0.01433 -0.0504 0.9955 0.0033
-8.750 -0.7281 0.01706 0.01281 -0.0516 0.9943 0.0034
-8.500 -0.7011 0.01604 0.01162 -0.0521 0.9926 0.0035
-8.250 -0.6732 0.01510 0.01054 -0.0526 0.9906 0.0036
-8.000 -0.6443 0.01424 0.00954 -0.0533 0.9886 0.0037
-7.750 -0.6143 0.01354 0.00871 -0.0542 0.9869 0.0038
-7.500 -0.5834 0.01291 0.00798 -0.0552 0.9853 0.0040
-7.250 -0.5514 0.01244 0.00743 -0.0564 0.9840 0.0041
-7.000 -0.5198 0.01148 0.00633 -0.0576 0.9827 0.0047
-6.750 -0.4950 0.01098 0.00578 -0.0571 0.9783 0.0051
-6.500 -0.4651 0.01057 0.00532 -0.0577 0.9752 0.0055
-6.250 -0.4337 0.01018 0.00489 -0.0586 0.9728 0.0061
-6.000 -0.4013 0.00982 0.00448 -0.0597 0.9708 0.0067
-5.750 -0.3732 0.00944 0.00407 -0.0598 0.9663 0.0077
-5.500 -0.3439 0.00915 0.00379 -0.0602 0.9610 0.0090
-5.250 -0.3110 0.00889 0.00350 -0.0614 0.9571 0.0103
-5.000 -0.2808 0.00871 0.00327 -0.0619 0.9503 0.0110
-4.750 -0.2479 0.00836 0.00291 -0.0631 0.9438 0.0134
-4.500 -0.2167 0.00813 0.00266 -0.0639 0.9345 0.0150
-4.250 -0.1857 0.00793 0.00240 -0.0645 0.9235 0.0161
-4.000 -0.1561 0.00777 0.00219 -0.0649 0.9102 0.0171
-3.750 -0.1281 0.00757 0.00192 -0.0648 0.8949 0.0211
-3.500 -0.1007 0.00744 0.00173 -0.0647 0.8782 0.0252
-3.250 -0.0740 0.00726 0.00156 -0.0644 0.8608 0.0400
-3.000 -0.0475 0.00713 0.00142 -0.0641 0.8429 0.0572
-2.750 -0.0210 0.00701 0.00129 -0.0638 0.8239 0.0761
-2.500 0.0052 0.00689 0.00117 -0.0635 0.8047 0.1017
-2.250 0.0316 0.00677 0.00107 -0.0632 0.7853 0.1304
-2.000 0.0578 0.00663 0.00098 -0.0629 0.7655 0.1697
-1.750 0.0835 0.00635 0.00090 -0.0627 0.7460 0.2508
-1.500 0.1096 0.00614 0.00082 -0.0625 0.7258 0.3207
-1.000 0.1620 0.00583 0.00073 -0.0620 0.6844 0.4468
-0.750 0.1876 0.00557 0.00070 -0.0617 0.6634 0.5480
-0.500 0.2140 0.00550 0.00072 -0.0614 0.6416 0.6065
-0.250 0.2407 0.00553 0.00074 -0.0612 0.6202 0.6387
0.000 0.2676 0.00557 0.00076 -0.0609 0.5983 0.6629
0.250 0.2944 0.00564 0.00079 -0.0607 0.5759 0.6826
0.500 0.3212 0.00572 0.00083 -0.0605 0.5537 0.6997
0.750 0.3481 0.00581 0.00087 -0.0602 0.5311 0.7144
1.000 0.3749 0.00592 0.00093 -0.0600 0.5082 0.7282
1.250 0.4016 0.00602 0.00098 -0.0598 0.4838 0.7416
1.500 0.4282 0.00615 0.00105 -0.0595 0.4586 0.7556
1.750 0.4548 0.00627 0.00113 -0.0592 0.4343 0.7695
2.000 0.4812 0.00641 0.00122 -0.0590 0.4100 0.7840
2.250 0.5075 0.00655 0.00132 -0.0586 0.3846 0.7999
2.500 0.5337 0.00669 0.00142 -0.0583 0.3598 0.8152
2.750 0.5596 0.00687 0.00153 -0.0580 0.3331 0.8281
3.000 0.5854 0.00707 0.00167 -0.0576 0.3048 0.8399
3.250 0.6114 0.00723 0.00179 -0.0572 0.2837 0.8522
3.500 0.6368 0.00743 0.00194 -0.0568 0.2582 0.8657
3.750 0.6621 0.00760 0.00209 -0.0563 0.2370 0.8810
4.000 0.6865 0.00783 0.00225 -0.0556 0.2107 0.8991
4.250 0.7095 0.00808 0.00245 -0.0546 0.1810 0.9209
4.500 0.7332 0.00829 0.00263 -0.0537 0.1580 0.9521
4.750 0.7654 0.00863 0.00286 -0.0549 0.1285 1.0000
5.000 0.7905 0.00900 0.00310 -0.0546 0.1036 1.0000
5.250 0.8153 0.00938 0.00337 -0.0541 0.0806 1.0000
5.500 0.8406 0.00972 0.00365 -0.0538 0.0642 1.0000
5.750 0.8661 0.01003 0.00391 -0.0535 0.0533 1.0000
6.000 0.8909 0.01041 0.00422 -0.0530 0.0395 1.0000
6.250 0.9158 0.01078 0.00454 -0.0526 0.0296 1.0000
6.500 0.9406 0.01115 0.00486 -0.0522 0.0215 1.0000
6.750 0.9649 0.01157 0.00526 -0.0517 0.0139 1.0000
7.000 0.9887 0.01204 0.00569 -0.0511 0.0078 1.0000
7.250 1.0130 0.01246 0.00611 -0.0506 0.0056 1.0000
7.500 1.0372 0.01288 0.00657 -0.0500 0.0045 1.0000
7.750 1.0616 0.01327 0.00700 -0.0495 0.0042 1.0000
8.000 1.0856 0.01368 0.00747 -0.0489 0.0040 1.0000
8.250 1.1091 0.01414 0.00800 -0.0483 0.0038 1.0000
8.500 1.1323 0.01462 0.00854 -0.0477 0.0036 1.0000
8.750 1.1550 0.01515 0.00913 -0.0469 0.0033 1.0000
9.000 1.1773 0.01569 0.00972 -0.0462 0.0031 1.0000
9.250 1.1987 0.01632 0.01042 -0.0453 0.0029 1.0000
9.500 1.2189 0.01707 0.01125 -0.0442 0.0026 1.0000
9.750 1.2372 0.01799 0.01229 -0.0428 0.0024 1.0000
10.000 1.2533 0.01911 0.01356 -0.0411 0.0023 1.0000
10.250 1.2726 0.01981 0.01435 -0.0400 0.0023 1.0000
10.500 1.2907 0.02059 0.01522 -0.0388 0.0023 1.0000
10.750 1.3080 0.02140 0.01612 -0.0374 0.0022 1.0000
11.000 1.3239 0.02229 0.01711 -0.0358 0.0022 1.0000
11.250 1.3382 0.02323 0.01817 -0.0341 0.0021 1.0000
11.500 1.3510 0.02420 0.01924 -0.0322 0.0021 1.0000
11.750 1.3589 0.02524 0.02040 -0.0294 0.0021 1.0000
12.000 1.3636 0.02644 0.02173 -0.0263 0.0020 1.0000
12.250 1.3718 0.02742 0.02280 -0.0240 0.0019 1.0000
12.500 1.3755 0.02873 0.02424 -0.0213 0.0019 1.0000
12.750 1.3754 0.03038 0.02603 -0.0185 0.0019 1.0000
13.000 1.3792 0.03182 0.02760 -0.0165 0.0018 1.0000
13.250 1.3770 0.03386 0.02978 -0.0144 0.0018 1.0000
13.500 1.3727 0.03626 0.03233 -0.0128 0.0018 1.0000
13.750 1.3710 0.03862 0.03482 -0.0118 0.0017 1.0000
14.000 1.3613 0.04208 0.03844 -0.0112 0.0017 1.0000
14.250 1.3615 0.04472 0.04118 -0.0113 0.0016 1.0000
14.500 1.3416 0.05020 0.04688 -0.0125 0.0017 1.0000
14.750 1.3385 0.05391 0.05069 -0.0138 0.0016 1.0000
15.000 1.3229 0.05984 0.05679 -0.0165 0.0017 1.0000
15.250 1.3071 0.06634 0.06345 -0.0199 0.0017 1.0000
15.500 1.2893 0.07367 0.07093 -0.0241 0.0016 1.0000
15.750 1.2685 0.08208 0.07950 -0.0290 0.0016 1.0000
16.000 1.2374 0.09304 0.09064 -0.0354 0.0017 1.0000
16.250 1.2091 0.10398 0.10174 -0.0418 0.0017 1.0000
16.500 1.1907 0.11305 0.11092 -0.0470 0.0017 1.0000
16.750 1.1599 0.12537 0.12338 -0.0541 0.0017 1.0000
17.000 1.1353 0.13656 0.13468 -0.0605 0.0018 1.0000
17.250 1.1094 0.14858 0.14680 -0.0674 0.0018 1.0000
17.500 1.0813 0.16176 0.16009 -0.0750 0.0019 1.0000
17.750 1.0575 0.17450 0.17293 -0.0822 0.0019 1.0000
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Polar data table (+)
Polar graphs
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